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EUROPEAN STANDARD
NORME EUROPÉENNE
EUROPÄISCHE NORM
DRAFT prEN 13001-3-1
July 2010
ICS 53.020.20
English Version
Cranes - General Design - Part 3-1: Limit States and proof competence of steel structure
Appareils de levage à charge suspendue - Conception générale - Partie 3-1: Etats limites et vérification d'aptitude
des structures en acier
Krane - Konstruktion allgemein - Teil 3-1: Grenzzustände und Sicherheitsnachweis von Stahltragwerken
This draft European Standard is submitted to CEN members for second enquiry. It has been drawn up by the Technical Committee CEN/TC 147. If this draft becomes a European Standard, CEN members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. This draft European Standard was established by CEN in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to the CEN Management Centre has the same status as the official versions. CEN members are the national standards bodies of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland and United Kingdom. Recipients of this draft are invited to submit, with their comments, notification of any relevant patent rights of which they are aware and to provide supporting documentation. Warning : This document is not a European Standard. It is distributed for review and comments. It is subject to change without notice and shall not be referred to as a European Standard.
EUROPEAN COMMITTEE FOR STANDARDIZATION C O M I T É E U R O P É E N D E N O R M A LI S A T I O N EUR OP ÄIS C HES KOM ITEE FÜR NOR M UNG
Management Centre: Avenue Marnix 17, B-1000 Brussels
© 2010 CEN All rights of exploitation in any form and by any means reserved worldwide for CEN national Members.
Ref. No. prEN 13001-3-1:2010: E
prEN 13001-3-1:2010 (E)
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Contents Page
Foreword ..............................................................................................................................................................4
Introduction .........................................................................................................................................................5
1 Scope ......................................................................................................................................................5
2 Normative references ............................................................................................................................5
3 Terms and definitions ...........................................................................................................................7
4 General ................................................................................................................................................. 104.1 Documentation .................................................................................................................................... 104.2 Materials for structural members ...................................................................................................... 114.2.1 Grades and qualities .......................................................................................................................... 114.2.2 Impact toughness ............................................................................................................................... 134.3 Bolted connections............................................................................................................................. 144.3.1 Bolt materials ...................................................................................................................................... 144.3.2 General ................................................................................................................................................. 144.3.3 Shear and bearing connections ........................................................................................................ 154.3.4 Friction grip type (slip resistant) connections ................................................................................ 154.3.5 Connections loaded in tension ......................................................................................................... 154.4 Pinned connections ............................................................................................................................ 154.5 Welded connections ........................................................................................................................... 154.6 Proof of competence for structural members and connections .................................................... 16
5 Proof of static strength ...................................................................................................................... 165.1 General ................................................................................................................................................. 165.2 Limit design stresses and forces ...................................................................................................... 175.2.1 General ................................................................................................................................................. 175.2.2 Limit design stress in structural members ...................................................................................... 175.2.3 Limit design forces in bolted connections ...................................................................................... 185.2.4 Limit design forces in pinned connections ..................................................................................... 265.2.5 Limit design stresses in welded connections ................................................................................. 305.3 Execution of the proof ........................................................................................................................ 325.3.1 Proof for structural members ............................................................................................................ 325.3.2 Proof for bolted connections ............................................................................................................. 325.3.3 Proof for pinned connections ............................................................................................................ 335.3.4 Proof for welded connections ........................................................................................................... 33
6 Proof of fatigue strength .................................................................................................................... 346.1 General ................................................................................................................................................. 346.2 Limit design stresses ......................................................................................................................... 356.2.1 Characteristic fatigue strength .......................................................................................................... 356.2.2 Weld quality ......................................................................................................................................... 376.2.3 Requirements for fatigue testing ...................................................................................................... 386.3 Stress histories ................................................................................................................................... 386.3.1 General ................................................................................................................................................. 386.3.2 Frequency of occurence of stress cycles ........................................................................................ 396.3.3 Stress history parameter ................................................................................................................... 396.3.4 Stress history classes S .................................................................................................................... 406.4 Execution of the proof ........................................................................................................................ 416.5 Determination of the limit design stress range ............................................................................... 426.5.1 Applicable methods ............................................................................................................................ 426.5.2 Direct use of stress history parameter ............................................................................................. 426.5.3 Use of class S ...................................................................................................................................... 42
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6.5.4 Independent concurrent normal and/or shear stresses .................................................................. 44
7 Proof of static strength of hollow section girder joints .................................................................. 44
8 Proof of elastic stability ...................................................................................................................... 448.1 General ................................................................................................................................................. 448.2 Lateral buckling of members loaded in compression ..................................................................... 458.2.1 Critical buckling load .......................................................................................................................... 458.2.2 Limit compressive design force ........................................................................................................ 468.3 Buckling of plate fields subjected to compressive and shear stresses ........................................ 488.3.1 General ................................................................................................................................................. 488.3.2 Limit design stress with respect to longitudinal stress xσ ............................................................ 498.3.3 Limit design stress with respect to transverse stress yσ .............................................................. 51
8.3.4 Limit design stress with respect to shear stress ττττ ......................................................................... 538.4 Execution of the proof ........................................................................................................................ 548.4.1 Members loaded in compression ...................................................................................................... 548.4.2 Plate fields ............................................................................................................................................ 54
Annex A (informative) Limit design shear force Fv,Rd per fit bolt and per shear plane for multiple shear plane connections .................................................................................................................... 56
Annex B (informative) Preloaded bolts ........................................................................................................... 57
Annex C (normative) Design weld stress σσσσW,Sd and ττττW,Sd ............................................................................. 59C.1 Butt joint ............................................................................................................................................... 59C.2 Fillet weld ............................................................................................................................................. 60C.3 T-joint with full and partial penetration ............................................................................................. 61C.4 Effective distribution length under concentrated load .................................................................... 61
Annex D (normative) Values of slope constant m and characteristic fatigue strength ∆∆∆∆σσσσc, ∆∆∆∆ττττc .............. 63
Annex E (normative) Calculated values of limit design stress range ∆∆∆∆σσσσRd ................................................. 82
Annex F (informative) Evaluation of stress cycles (example) ..................................................................... 84
Annex G (informative) Calculation of stiffnesses for connections loaded in tension ............................... 86
Annex H (informative) Hollow Sections ......................................................................................................... 89
Annex I (informative) Selection of a suitable set of crane standards for a given application ............... 101
Annex ZA (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 98/37/EC .......................................................................................... 102
Annex ZB (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 2006/42/EC ...................................................................................... 103
Bibliography .................................................................................................................................................... 104Selection of literature that contains information about Hot Spot Stress Method: .................................. 104
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Foreword
This document (prEN 13001-3-1:2010) has been prepared by Technical Committee CEN/TC 147 “Cranes - Safety”, the secretariat of which is held by BSI.
This document is currently submitted to the second CEN Enquiry.
This document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association, and supports essential requirements of EU Directive(s).
For relationship with EU Directive(s), see informative Annex ZA and ZB, which is an integral part of this document.
Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN shall not be held responsible for identifying any or all such patent rights.
This European Standard is one Part of EN 13001 Cranes – General Design. The other parts are as follows:
Part 1: General principles and requirements
Part 2: Load actions
Part 3-2: Limit states and proof of competence of wire ropes in reeving systems
Part 3-3: Limit states and proof of competence of wheel/rail contacts
Part 3-4: Limit states and proof of competence of machinery
Part 3-5: Limit states and proof of competence of forged hooks
Annexes C, D and E are normative.
Annexes A, B, F, G, H and I are informative.
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Introduction
This European Standard has been prepared to be a harmonized standard to provide one means for the mechanical design and theoretical verification of cranes to conform with the essential health and safety requirements of the Machinery Directive, as amended. This standard also establishes interfaces between the user (purchaser) and the designer, as well as between the designer and the component manufacturer, in order to form a basis for selecting cranes and components.
This European Standard is a type C standard as stated in EN ISO 12100-1.
The machinery concerned and the extent to which hazards, hazardous situations and events are covered are indicated in the scope of this standard.
When provisions of this type C standard are different from those which are stated in type A or B standards, the provisions of this type C standard take precedence over the provisions of the other standards, for machines that have been designed and built according to the provisions of this type C standard.
1 Scope
This European Standard is to be used together with EN 13001 – 1 and EN 13001 – 2 and as such they specify general conditions, requirements and methods to prevent mechanical hazards of cranes by design and theoretical verification.
NOTE Specific requirements for particular types of crane are given in the appropriate European Standard for the particular crane type.
The following is a list of significant hazardous situations and hazardous events that could result in risks to persons during intended use and reasonably foreseeable misuse. Clauses 4 to 8 of this standard are necessary to reduce or eliminate risks associated with the following hazards:
a) Exceeding the limits of strength (yield, ultimate, fatigue);
b) Exceeding temperature limits of material or components;
c) Elastic instability of the crane or its parts (buckling, bulging).
This European Standard is not applicable to cranes which are manufactured before the date of its publication as EN and serves as reference base for the European Standards for particular crane types (see Annex I).
NOTE EN 13001-3-1 deals only with limit state method in accordance with EN 13001-1.
2 Normative references
The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies.
EN 1990:2002, Eurocode — Basis of structural design
EN 1993-1-8:2005, Eurocode 3: Design of steel structures – Part 1-8: Design of joints
EN 10045-1:1989, Metallic materials; Charpy impact test — Part 1: Test method
EN 10025-1:2004, Hot rolled products of structural steels — Part 1: General technical delivery conditions
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EN 10025-2:2004, Hot rolled products of structural steels — Part 2: Technical delivery conditions for non-alloy structural steels
EN 10025-3:2004, Hot rolled products of structural steels — Part 3: Technical delivery conditions for normalized/normalized rolled weldable fine grain structural steels
EN 10025-4:2004, Hot rolled products of structural steels — Part 4: Technical delivery conditions for thermomechanical rolled weldable fine grain structural steels
EN 10025-6:2004, Hot rolled products of structural steels — Part 6: Technical delivery conditions for flat products of high yield strength structural steels in the quenched and tempered condition
EN 10029:1991, Hot rolled steel plates 3 mm thick or above - Tolerances on dimensions, shape and mass
EN 10149-1:1995, Hot-rolled flat products made of high yield strength steels for cold forming — Part 1: General delivery conditions
EN 10149-2:1995, Hot-rolled flat products made of high yield strength steels for cold forming — Part 2: Delivery conditions for thermomechanically rolled steels
EN 10149-3:1995, Hot-rolled flat products made of high yield strength steels for cold forming — Part 3: Delivery conditions for normalized or normalized rolled steels
EN 10163-1:2004, Delivery requirements for surface conditions of hot-rolles steel plates, wide flats and sections – Part 1: General requirements
EN 10163-2:2004, Delivery requirements for surface conditions of hot-rolles steel plates, wide flats and sections – Part 2: Plate and wide flats
EN 10163-3:2004, Delivery requirements for surface conditions of hot-rolles steel plates, wide flats and sections – Part 3: Sections
EN 10164:2004, Steel products with improved deformation properties perpendicular to the surface of the product — Technical delivery conditions
EN 13001-1, Cranes — General Design — Part 1: General principles and requirements
EN 13001-2, Cranes — General Design — Part 2: Load actions
EN 20273:1991, Fasteners — Clearance holes for bolts and screws (ISO 273:1979)
prEN ISO 898-1:2006, Mechanical properties of fasteners made of carbon steel and alloy steel — Part 1: Bolts, screws and studs (ISO/DIS 898-1:2006)
EN ISO 5817:2008, Welding — Fusion-welded joints in steel, nickel, titanium and their alloys (beam welding excluded) — Quality levels for imperfections (ISO 5817:2003, corrected version 2005, including Technical Corrigendum 1:2006))
EN ISO 9013:2002, Thermal cutting — Classification of thermal cuts — Geometrical specification and quality tolerances (ISO 9013:2002)
EN ISO 12100-1:2003, Safety of machinery — Basic concepts, general principles for design — Part 1: Basic terminology, methodology (ISO 12100-1:2003)
EN ISO 12100-2:2003, Safety of machinery — Basic concepts, general principles for design — Part 2: Technical principles (ISO 12100-2:2003)
EN ISO 17659:2004, Welding — Multilingual terms for welded joints with illustrations (ISO 17659:2002)
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ISO 286-2:1990, ISO system of limits and fits — Part 2: Tables of standard tolerance grades and limit deviations for holes and shafts
ISO 4306-1:2007, Cranes — Vocabulary — Part 1: General
3 Terms and definitions
3.1 Terms and definitions For the purposes of this European Standard, the terms and definitions given in EN ISO 12100-1 and EN ISO 12100-2 and the basic list of definitions as provided in EN 1990-1 apply. For the definitions of loads, Clause 6 of ISO 4306-1:1990 applies.
3.2 Symbols and abbreviations The symbols and abbreviations used in this Part of the EN 13001 are given in Table 1.
Table 1 — Symbols and abbreviations
Symbols, abbreviations
Description
A cross section
An net cross section
AS stress area of a bolt
a length of plate
ar relevant weld thickness
b width of plate
c edge stress ratio factor (buckling)
Do, Di outer, inner diameter of hollow pin
d diameter (shank of bolt, pin)
do diameter of hole
e1, e2 edge distances
Fb tensile force in bolt
Fd limit force
FK characteristic value (force)
Fp preloading force in bolt
FRd,σ limit design force for normal stresses
FRd,τ limit design force for shear stresses
Fe external force (on bolted connection)
Fb, Rd limit design bearing force
Fb, Sd; Fbi, Sd design bearing force
Fcs, Rd limit design tensile force
Fp, d design preloading force
Fcr reduction in compression force due to external tension
Fs, Rd limit design slip force per bolt and friction interface
Ft, Rd limit design tensile force in bolt
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Table 1 – (continued)
Symbols, abbreviations
Description
Fv, Rd limit design shear force per bolt/pin and shear plane
Fv, Sd design shear force per bolt/pin and shear plane
Fσ,τ acting normal/shear force
f maximum imperfection
fd limit stress
fK characteristic value (stress)
fRd limit design stress
fu ultimate strength of material
fub ultimate strength of bolts
fw, Rd limit design weld stress
fy yield stress of material
fyb yield stress of bolts
fyk yield stress (minimum value) of base material or member
fyp yield stress of pins
Gt mass of the moving crane parts during a representative working cycle
H distance between weld and contact area of acting load
kσ, kτ buckling factors
Kb stiffness of bolt
Kc stiffness of flanges
K* specific spectrum ratio factor
km stress spectrum factor based on m of the detail under consideration
K3 stress spectrum factor based on m = 3
lm gauge length
lr relevant weld length
lW weld length
MRd limit design bending moment
MSd design bending moment
m slope constant of log ∆σ/log N-curve
NC notch class
Nref reference number of cycles
min σ, max σ extreme values of stresses
PS probability of survival
p1, p2 distances between bolt centers
Q mass of the maximum hoist load
q impact toughness parameter
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Table 1 – (continued)
Symbols, abbreviations
Description
Rd design resistance
r radius of wheel
Sd design stresses or forces
s(m) stress history parameter
T Temperature
t Thickness
Wel elastic section modulus
α side ratio (plate field buckling)
α cross section parameter (lateral buckling)
αb characteristic factor for bearing connection
αL load introduction factor (buckling)
αw characteristic factor for limit weld stress
γm general resistance factor
γMf fatigue strength specific resistance factor
γp partial safety factor
γR resulting resistance factor
γS specific resistance factor
γRb resulting resistance factor of bolt
γsb specific resistance factor of bolt
γRm resulting resistance factor of members
γsm specific resistance factor of members
γRp resulting resistance factor of pins
γsp specific resistance factor of pins
γRs resulting resistance factor of slip-resistance connection
γss specific resistance factor of slip-resistance connection
γRc resulting resistance factor for tension on section with holes
γst specific resistance factor for tension on section with holes
γRw resulting resistance factor of welding connection
γsw specific resistance factor of welding connection
δp elongation from preloading
φ2 dynamic factor
κ dispersion angle (wheel pressure)
κ, κx, κy, κτ reduction factors (buckling)
λ width of contact area in weld direction
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Table 1 – (continued)
Symbols, abbreviations
Description
λx, λy, λτ non-dimensional plate slenderness (buckling)
Ψ edge stress ratio (buckling)
∆Fb additional force
∆δ additional elongation
µ slip factor
ν relative total number of stress cycles (normalized)
νD ratio of diameters
∆σc characteristic value of stress range (normal stress)
∆τc characteristic value of stress range (shear stress)
σe reference stress (buckling)
σSd design stress (normal)
τSd design stress (shear)
σw, Sd
τw, Sd
∆σRd
design weld stress (normal)
design weld stress (shear)
permissible (limit) stress range (normal)
∆σRd,1 limit design stress range for k* = 1
∆τRd permissible (limit) stress range (shear)
∆σSd design stress range (normal)
∆τSd design stress range (shear)
4 General
4.1 Documentation
The documentation of the proof of competence shall include:
design assumptions including calculation models,
applicable loads and load combinations,
material grades and qualities,
weld quality classes, in accordance with EN ISO 5817,
materials of connecting elements,
relevant limit states
results of the proof of competence calculation. and tests when applicable.
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4.2 Materials for structural members
4.2.1 Grades and qualities
European Standards specify materials and specific values. This standard gives a preferred selection.
For structural members, steel according to following European Standards should be used:
Non-alloy structural steels EN 10025-2.
Weldable fine grain structural steels in conditions:
normalized (N) EN 10025-3;
thermomechanical (M) EN 10025-4.
High yield strength structural steels in the quenched and tempered condition EN 10025-6.
High yield strength steels for cold forming in conditions:
thermomechanical (M) EN 10149-2;
normalized (N) EN 10149-3.
Table 2 shows specific values for the nominal value of strength fu, fy and limit design stress fRd (see 5.2). The values given are applicable for temperatures up to 150°C. For more information see the specific European Standard.
Tolerance class A, B or C of EN 10029 shall be specified for the plates to allow the use of nominal values of plate thicknesses in the proof calculations. Otherwise the minimum value of thickness shall be used.
Grades and qualities other than those mentioned in the above standards and in Table 2 may be used if the mechanical properties and the chemical composition are specified and conform to a relevant European Standard. If necessary, weldability shall be demonstrated.
Table 2 — Specific values of steels for structural members
Steel Standard Thickness t mm
Nominal strength Limit design stress (γγγγRm=1,1) fy
yield N/mm2
fu ultimate N/mm2
fRdσσσσ, normal N/mm2
fRdττττ, shear N/mm2
S235
EN 10025-2
t ≤ 16 16 < t ≤ 40
40 < t ≤ 100 100 < t ≤ 150
235 225 215 195
340
214 205 195 177
123 118 113 102
S275
t ≤ 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80
80 < t ≤ 100 100 < t ≤ 150
275 265 255 245 235 225
430
250 241 232 223 214 205
144 139 134 129 123 118
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Table 2 – (continued)
Steel Standard Thickness t mm
Nominal strength Limit design stress (γγγγRm=1,1) fy
yield N/mm2
fu ultimate N/mm2
fRdσσσσ, normal N/mm2
fRdττττ, shear N/mm2
S355 EN 10025-2
t ≤ 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80
80 < t ≤ 100 100 < t ≤ 150
355 345 335 325 315 295
490
323 314 305 296 287 268
186 181 176 171 166 155
S355
EN 10025-3 (N)
EN 10025-4 (M)
t < 16 16 < t ≤ 40 40 < t ≤ 63
63 < t ≤ 80 (N) 80 < t ≤ 100 (N)
100 < t ≤ 150 (N)
355 345 335 325 315 295
450
323 314 305 295 286 268
186 181 176 171 165 155
S420
t < 16 16 < t ≤ 40 40 < t ≤ 63
63 < t ≤ 80 (N) 80 < t ≤ 100 (N)
100 < t ≤ 150 (N)
420 400 390 370 360 340
500
382 364 355 336 327 309
220 210 205 194 189 178
S460
t < 16 16 < t ≤ 40 40 < t ≤ 63
63 < t ≤ 80 (N) 80 < t ≤ 100 (N)
460 440 430 410 400
530
418 400 391 373 364
241 231 226 215 210
S460
EN 10025-6
3 < t ≤ 50 50 < t ≤ 100
460 440
550 418 400
241 231
S500 3 < t ≤ 50
50 < t ≤ 100 500 480
590 455 436
262 252
S550 3 < t ≤ 50
50 < t ≤ 100 550 530
640 500 482
289 278
S620 3 < t ≤ 50
50 < t ≤ 100 620 580
700 564 527
325 304
S690 3 < t ≤ 50
50 < t ≤ 100 690 650
770 760
627 591
362 341
S890 3 < t ≤ 50
50 < t ≤ 100 890 830
940 880
809 755
467 436
S960 3 < t ≤ 50 960 980 873 504
S315
EN 10149–2 (M)
EN 10149-3 (N)
all t
315 390 286 165
S355 355 430 323 186
S420 420 480 382 220
S460 (M) 460 520 418 241
S500 (M) 500
550 455 262
S550 (M) 550
600 500 289
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Table 2 – (continued)
Steel Standard Thickness t mm
Nominal strength Limit design stress (γγγγRm=1,1)
fy yield
N/mm2
fu ultimate N/mm2
fRdσσσσ, normal N/mm2
fRdττττ, shear N/mm2
S600 (M) EN 10149–2
(M)
EN 10149-3 (N)
all t 600 650 545 315
S650 (M) t ≤ 8
t > 8
650
630 700
591
573
341
331
S700 (M) t ≤ 8
t > 8
700
680 750
636
618
367
357
4.2.2 Impact toughness
When selecting grade and quality of the steel for tensile members, the sum of impact toughness parameters qi shall be taken into account. Table 3 gives the impact toughness parameters qi for various influences. Table 4 gives the required steel quality and impact energy/test temperature in dependence of Σqi. Grades and qualities of steel other than mentioned in Table 4 may be used, if an impact energy/temperature is tested in accordance with EN 10045-1 and specified.
Table 3 — Impact toughness parameters qi
i Influence qi
1
Operating temperature T (°C)
0 ≤ T 0
-10 ≤ T < 0 1
-20 ≤ T < -10 2
-30 ≤ T < -20 3
-40 ≤ T < -30 4
-50 ≤ T < -40 6
2
Yield stress fy (N/mm2)
fy ≤ 300 0
300 < fy ≤ 460 1
460 < fy ≤ 700 2
700 <fy ≤ 1000 3
1000 <fy ≤ 1300 4
3 Material thickness t (mm) Equivalent thickness t for solid bars:
8,1dt = for 8,1<
hb
: 8,1
bt =
t ≤ 10 0
10 < t ≤ 20 1
20 < t ≤ 40 2
40 < t ≤ 60 3
60 < t ≤ 80 4
80 < t ≤ 100 5
100 < t ≤ 125 6
125 < t ≤ 150 7
4
Stress concentration and notch class ∆σc (N/mm2) (see Annex D and Annex H)
∆σc > 125 0
80 < ∆σc ≤ 125 1
56< ∆σc ≤ 80 2
40≤ ∆σc ≤ 56 3
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Table 4 — Impact toughness requirement and corresponding steel quality for ∑qi
∑∑∑∑qi ≤≤≤≤ 5 6 ≤≤≤≤ ∑∑∑∑qi ≤≤≤≤ 8 9 ≤≤≤≤ ∑∑∑∑qi ≤≤≤≤ 11 12 ≤≤≤≤ ∑∑∑∑qi ≤≤≤≤ 14
Impact energy/ test temperature requirement
27 J / +20°C 27 J / 0°C 27 J / -20°C 27 J / -40°C
EN 10025-2 JR J0 J2 a)
EN 10025-3 N N N NL
EN 10025-4 M M M ML
EN 10025-6 Q Q Q QL
EN 10149-1 NC, MC NC, MC NC, MC a)
a) May be used if the impact toughness is at least 27 J at – 40°C, tested in accordance with EN 10045-1 and specified ,
4.3 Bolted connections
4.3.1 Bolt materials
For bolted connections bolts of the property classes (bolt grades) 4.6, 5.6, 8.8, 10.9 or 12.9 in accordance with prEN ISO 898-1 shall be used. Table 5 shows nominal values of the strengths:
Table 5 — Property classes (bolt grades)
Property class (Bolt grade)
4.6 5.6 8.8 10.9 12.9
ybf (N/mm2) 240 300 640 900 1 080
ubf (N/mm2) 400 500 800 1 000 1 200
NOTE The designer should ask the bolt supplier to demonstrate compliance with the requirements regarding the protection against hydrogen brittleness, for the property classes (bolt grades) 10.9 and 12.9. Technical requirements can be found in EN ISO 15330, EN ISO 4042 and ISO 9587.
4.3.2 General
For the purpose of this standard bolted connections are connections between members and/or components utilizing bolts.
In general bolted connections are tensioned wrench tight.
Where slippage (e.g. caused by vibrations or fluctuations in loading) causes deleterious changes in geometry bolts shall be tightened to avoid slippage sufficiently or the joint surfaces shall be secured against rotation (e. g. by using multiple bolts);
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4.3.3 Shear and bearing connections
For the purpose of this standard shear and bearing connections are those connections where the loads act perpendicular to the bolt axis and cause shear and bearing stresses in the bolts and bearing stresses in the connected parts, and where
clearance between bolt and hole shall conform to ISO 286-2 tolerances h13 and H11 or closer, when bolts are exposed to load reversal or where slippage may cause deleterious changes in geometry;
in other cases wider clearances in accordance with EN 20273 may be used;
special surface treatment of the contact surfaces is not needed.
4.3.4 Friction grip type (slip resistant) connections
For the purpose of this standard friction grip connections are those connections where the loads are transmitted by friction between the joint surfaces, and where
high strength bolts of property classes (bolt grades) 8.8, 10.9 or 12.9 shall be used;
bolts shall be tightened by a controlled method to a specified preloading state;
the surface condition of the contact surfaces shall be specified and taken into account accordingly;
in addition to standard holes oversized and slotted holes may be used.
4.3.5 Connections loaded in tension
For the purpose of this standard connections loaded in tension are those connections where
the loads act in the direction of the bolt axis and cause axial stresses in the bolts,
high strength bolts of property classes (bolt grades) 8.8, 10.9 or 12.9 are used and tightened by a controlled method to a specified preloading state;
NOTE Bolts in tension that are not preloaded are treated as structural members.
4.4 Pinned connections
For the purpose of this standard pinned connections are connections that do not constrain rotation between connected parts. Only round pins are considered.
The requirements herein apply to pinned connections designed to carry loads, i. e., they do not apply to connections made only as a convenient means of attachment.
Clearance between pin and hole shall be in accordance with ISO 286-2 tolerances h13 and H13 or closer. In case of loads with changing directions closer tolerances shall be applied.
All pins shall be furnished with retaining means to prevent the pins from becoming displaced from the hole.
In order to inhibit local out-of-plane distortion (dishing), consideration shall be given to the stiffness of the connected parts.
4.5 Welded connections
For the purposes of this standard welded connections are joints between members and/or components which utilize fusion welding processes, and where connected parts are 3 mm or larger in thickness.
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Quality levels of EN ISO 5817 shall be applied , and appropriate methods of non-destructive testing shall be used to verify compliance with quality level requirements.
In general, load carrying welds shall be at least of quality level C.. Quality level D may be applied only in joints where local failure of the weld will not result in failure of the structure or falling of loads.
Terms for welded joints are as given in EN ISO 17659.
Although the distribution of stresses along the length of the weld may be non-uniform, such distributions can, in general, be considered uniform.
Residual stresses and stresses not participating in the transfer of forces need not to be considered in the design of weld subjected to static actions. This applies specifically to the normal stress parallel to the axis of the weld which is accommodated by the base material.
4.6 Proof of competence for structural members and connections
The object of the proof of competence is to demonstrate that the design stresses or forces dS do not exceed
the design resistances dR :
dd RS ≤ (1)
The design stresses or forces dS shall be determined by applying the relevant loads, load combinations and partial safety factors in accordance with EN 13001-2.
In the following clauses, the design resistances dR are represented as limit stresses df or limit forces dF .
The following proofs for structural members and connections shall be demonstrated:
proof of static strength in accordance with clause 5;
proof of fatigue strength according to 6,
proof of strength of hollow section girder joints in accordance with clause 7;
proof of elastic stability in accordance with clause 8.
5 Proof of static strength
5.1 General
A proof of static strength by calculation is intended to prevent excessive deformations due to yielding of the material, sliding of friction-grip connections, elastic instability (see 8) and fracture of structural members or connections. Dynamic factors given in EN 13001-2 are used to produce equivalent static loads to simulate dynamic effects.
The use of the theory of plasticity for calculation of ultimate load bearing capacity is not considered acceptable within the terms of this standard.
The proof shall be carried out for structural members and connections whilst taking into account the most unfavourable load effects from the load combinations A, B or C in accordance with EN 13001-2 and applying the resistances according to 5.2.
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This standard is based on nominal stresses, i. e. stresses calculated using traditional elastic strength of materials theory. When alternative methods of stress calculation are used, such as finite element analysis, using those stresses for the proof given in this standard may yield inordinately conservative results.
5.2 Limit design stresses and forces
5.2.1 General
The limit design stresses and forces shall be calculated from:
Limit design stresses Rdf = function ( kf , Rγ ) or
(2) Limit design forces RdF = function ( kF , Rγ )
where
kf or kF are characteristic values (or nominal values)
Rγ is the total resistance factor smR γγγ ×=
mγ is the general resistance factor 1,1m =γ (see EN 13001-2)
sγ is the specific resistance factor applicable to specific structural components as given in the clauses below
NOTE Rdf and RdF are equivalent to m/ γR in EN 13001-1.
5.2.2 Limit design stress in structural members
The limit design stress Rdf , used for the design of structural members, shall be calculated from:
Rm
ykRdσ γ
ff = for normal stresses (3)
3Rm
ykRdτ γ
ff = for shear stresses (4)
with smmRm γγγ ×=
where
ykf is the minimum value of the yield stress of the material (see Table 2, column fy )
smγ is the specific resistance factor for material as follows:
For non-rolled material
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0,1sm =γ
For rolled materials (e. g. plates and profiles):
smγ = 1,0 for stresses in the plane of rolling
smγ = 1,0 for compressive and shear stresses
For tensile stresses perpendicular to the plane of rolling (see Figure 1):
Material shall be suitable for carrying perpendicular loads and be free of lamellar defects.
smγ = 1,0 for plate thicknesses less than 15mm or material in quality classes Z25 or Z35 in accordance with EN 10164
smγ = 1,16 for material in quality class Z15 in accordance with EN 10164
smγ = 1,50 without quality classification of through-thickness property
Key Figure shows a tensile load perpendicular to plane of rolling where 1 is the direction of the plane of rolling 2 is the direction of stress/load
Figure 1 — Tensile load perpendicular to plane of rolling
5.2.3 Limit design forces in bolted connections
5.2.3.1 Shear and bearing connections
5.2.3.1.1 General
The resistance of a connection shall be taken as the least value of the limit forces of the individual connection elements.
In addition to the bearing capacity of the connection elements other limit conditions at the most stressed sections shall be verified using the resistance factor of the base material.
Only the unthreaded part of the shank is considered effective in the bearing calculations;
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5.2.3.1.2 Bolt shear
The limit design shear force Rdv,F per bolt and for each shear plane shall be calculated from:
3Rb
ybRdv,
×
×=
γ
AfF (5)
with sbmbR γγγ ×=
where
ybf is the yield stress (nominal value) of the bolt material (see Table 5)
A is the cross-sectional area of the bolt shank at the shear plane
sbγ is the specific resistance factor for bolted connections
sbγ = 1,0 for multiple shear plane connections
sbγ = 1,3 for single shear plane connections
See Annex A for limit design shear forces of selected bolt sizes.
5.2.3.1.3 Bearing on bolts and connected parts
The limit design bearing force ,b RdF per bolt shall be calculated from:
Rb
yRdb, γ
tdfF
××= (6)
with sbmbR γγγ ×=
With the requirement
01 5,1 de ×≥ (7)
and with the following recommendations for the plate
02 5,1 de ×≥
01 0,3 dp ×≥
02 0,3 dp ×≥
where
ubf is the ultimate strength (nominal value) of the bolt (Table 5)
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uf is the ultimate strength (nominal value) of the basic material (Table 2)
yf is the minimum value of yield stresses of the basic materials and bolt (Table 2)
d is the shank diameter of the bolt
0d is the diameter of the hole
t is the thickness of the connected part in contact with the unthreaded part of the bolt
sbγ is the specific resistance factor for bolt connections
sbγ = 0,7 for multiple shear plane connections
sbγ = 0,9 for single shear plane connections
1p , 2p , 1e , 2e are distances (see Figure 2)
Key
1p , 2p , 1e , 2e are distances used in Equation (2) Arrow shows the direction of force
Figure 2 — Illustration for Equation (7)
5.2.3.1.4 Tension in connected parts
The limit design tensile force per connected member with respect to yielding, Rdcs,F , on the net cross-section shall be calculated from:
Rc
nyRdcs, γ
AfF
×= (8)
with
stmRc γγγ ×=
where
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nA is the net cross-sectional area at bolt or pin holes (see Figure 2)
stγ is the specific resistance factor for tension on sections with holes
2,1st =γ
5.2.3.2 Friction grip type connections
The resistance of a connection shall be determined by summing the limit forces of the individual connecting elements.
For friction grip type connections the limit design slip force Rds,F per bolt and per friction interface shall be calculated from:
Rs
crdp,Rds,
)(γ
µ FFF
−×= (9)
with ssmRs γγγ ×=
where
µ is the friction coefficient
50,0=µ for surfaces blasted metallic bright with steel grit or sand, no unevenness
50,0=µ for surfaces blasted with steel grit or sand and aluminized
50,0=µ for surfaces blasted with steel grit or sand and metallized with a product based on zinc
40,0=µ for surfaces blasted with steel grit or sand and alkali-zinc-silicate coating of 50 µm to 80 µm thickness
40,0=µ for surfaces hot dip galvanized and lightly blasted
30,0=µ for surfaces cleaned metallic bright by wire brushing
25,0=µ for surfaces cleaned and treated with etch primer
20,0=µ for surfaces cleaned of loose rust, oil and dirt (minimum requirement)
dp,F is the design preloading force
crF is the reduction in the compression force due to external tension on connection (for
simplification ecr FF = may be used).
The applied preloading force shall be greater than or equal to the design preloading force.
ssγ is the specific resistance factor for friction grip type connections (see Table 6)
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Table 6 — Specific resistance factor γss for friction grip connections
Type of holes
Effect of connection slippage
Standard holes a
Oversized b and short-
slotted c holes
Long-slotte
d holes
c
Long-slotte
d holes
d
a hazard is created 1,14 1,34 1,63 2,00
a hazard is not created 1,00 1,14 1,41 1,63 a Holes with clearances in accordance with the medium series of EN 20273:1991. b Holes with clearances in accordance with the coarse series of EN 20273:1991. c Slotted holes with slots perpendicular to the direction of force. d Slotted holes with slots parallel to the direction of force.
Short slotted hole: length of hole is smaller than or equal to 1.25 times the diameter of the bolt.
Long slotted hole: length of hole is larger than 1.25 times the diameter of the bolt. In order to reduce pressure under bolt or nut appropriate washers shall be used.
Table B.2 gives limit design slip forces using the specific resistance factor value 14,1ss =γ and a design preloading force of
sybdp, 7,0 AfF ××= ,
where
ybf is the yield stress (nominal value) of the bolt material (Table 5)
sA is the stress area of the bolt (Table B.2).
5.2.3.3 Connections loaded in tension
This clause specifies the limit state for a bolt in the connection. The connected parts and their welds shall be calculated with the general rules for structural members, where the preload in the bolt is considered as one loading component.
The proof calculation shall be done for the bolt under maximum external force in a connection, with due consideration to the force distribution in a multi-bolt connection and the prying effects (i. e. leverage).
Proof of competence calculations of a preloaded connection shall take into account the stiffness of the bolt and the connected parts, see Figure 3. In addition to that, the effect of different load paths of the external compression force, depending upon the joint construction, shall be taken into account, see Figure 4.
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Key Fp Preloading force in bolt δp Bolt elongation due to preloading Fe,t External tensile force Fe,c External compression force ∆δt Additional elongation, due to external tensile
force Fb Tensile force in bolt ∆Fb,t Additional force in bolt, due to external tensile
force ∆Fb,c Additional force in bolt, due to external
compression force Kb Stiffness of bolt Kc Stiffness of connected parts
Figure 3 — Force-elongation-diagram
a) External compression force does not interfere with the compression zone under the bolt
b) External compression force is transferred through the compression zone under the bolt
For simplicity, a symmetric loading with the bolt in the middle is assumed in the figure.
Figure 4 — Load path alternatives for the external compression force
Two separate design limits shall be considered for the external tensile bolt force:
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1) the resulting bolt force from the external force and the maximum design preload shall not exceed the bolt yield load, Equation (10)
2) the connection shall not open (gap) under the resulting bolt force from the external force and the minimum design preload, Equation (11).
For connections loaded in tension it shall be proven that the external tensile design force in the bolt Fe,t , does not exceed either of the two limit design forces Ft1,Rd or Ft2,Rd , see also 5.3.2.
The limit design tensile force per bolt for the bolt yield criteria is calculated from:
Φγ p,maxRby
Rdt1,/ FF
F−
= (10)
with
cb
bKK
K+
=Φ
and
sbmRb γγγ ×= and syby AfF ×=
where
Fy is the bolt yield force,
Fp,max is the maximum value of the preload,
fyb is the yield stress of the bolt material,
As is the stress area of the threaded part of the bolt,
Φ is the stiffness ratio factor of the connection, see also Annex G,
sbγ is the specific resistance factor for connections loaded in tension,
sbγ = 0,91
NOTE: A load introduction factor αL may be taken into account when calculating the factor Φ, see Annex G.
The limit design tensile force per bolt for the opening criteria of the connection is calculated from:
( )Φγ −⋅=
1Rb
p,minRdt2,
FF (11)
where
Fp,min is the minimum value of the preload.
The variation of preload due to scatter is taken into account by the maximum and minimum values of the preload as follows:
( ) dp,maxp, 1 FsF ×+= and (12)
( ) dp,minp, 1 FsF ×−= (13)
where
Fp,d is the nominal value of the design preload,
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Fp,max is the maximum value of the preload,
Fp,min is the minimum value of the preload,
s is the preload scatter,
s = 0,23 controlled tightening, rotation angle or tightening torque is measured
s = 0,09 controlled tightening, force in bolt or elongation is measured.
The nominal value of the design preload Fp,d value shall not exceed the values given in Table 7. Otherwise, any value for the preload may be chosen for a particular connection.
Table 7 — Upper limits of preload levels according to method of preloading
Type of preloading method Upper limit of preload level
Methods, where the bolt is subjected to torque 0,7 Fy
Methods, where only direct tension is applied to the bolt NOTE For direct tensioning method, the nominal preload is the residual preload achieved after a possible loss of the applied preload during the tensioning operation.
0,9 Fy
See Table B.1 for information on tightening torques.
For the calculation of the additional force in bolt, the load path of the external compression force shall be considered, see Figure 4. In a general format the additional force in bolt is calculated as follows:
( )ce,te,b FFF +×= Φ∆ (14)
where
bF∆ is the additional force in bolt
Φ is the stiffness ratio factor
te,F is the external tensile force
ce,F is the external compression force. This shall be omitted (i. e. Fe,c is set to zero in the equation) in cases, where the external compression force does not interfere with the compression zone under the bolt, case a) in Figure 4.
The additional force in bolt ∆Fb shall be used in the proof of fatigue strength of the bolt in accordance with clause 6.
5.2.3.4 Bearing type connections loaded in combined shear and tension
When bolts in a bearing type connection are subjected to both tensile and shear forces, the applied forces shall be limited as follows:
12
Rdv,
Sdv,2
Rdt,
Sdt, ≤
+
FF
FF
(15)
where
Sdt,F is the external tensile force per bolt
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Rdt,F is the limit tensile force per bolt (see 5.2.3.3)
Sdv,F is the design shear force per bolt per shear plane
Rdv,F is the limit shear force per bolt per shear plane (see 5.2.3.1.2)
5.2.4 Limit design forces in pinned connections
5.2.4.1 Pins, limit design bending moment
The limit design bending moment is calculated from
Rp
ypelRd γ
fWM
×= (16)
with spmRp γγγ ×=
where
elW is the elastic section modulus of the pin
ypf is the yield stress (minimum value) of the pin material
spγ is the specific resistance factor for pinned connections bending moment 0,1sp =γ
5.2.4.2 Pins, limit design shear force
The limit design shear force per shear plane for pins is calculated from
Rp
ypRdv,
31
γ×
××=
fAu
F (17)
with spmRp γγγ ×=
where
u is the shape factor
34=u for solid pins
2D
2DD
11
34
vvvu
+
++×= for hollow pins
where O
iD D
D=ν ,
iD is the inner diameter of pin
oD is the outer diameter of pin
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A is the cross-sectional area of the pin
spγ is the specific resistance factor for shear force in pinned connections
0,1sp =γ for multiple shear plane connections
3,1sp =γ for single shear plane connections
5.2.4.3 Pins and connected parts, limit design bearing force
The limit design bearing force is calculated from
γα
Rp
yRdb,
=
ftdF b ×××
(18)
with spmRp γγγ ×=
where
=
0,1Min y
yp
ff
α b
yf is the yield stress (minimum value) of the material of the connected parts
ypf is the yield stress (minimum value) of the pin material
d is the diameter of the pin
t is the lesser value of the thicknesses of the connected parts, i. e. 21 tt + or 3t in Figure 5
spγ is the specific resistance factor for the bearing force in pinned connections
6,0sp =γ when connected parts in multiple shear plane connections are held firmly together by retaining means such as external nuts on the pin ends
9,0sp =γ for single shear plane connections or when connected parts in multiple shear plane connections are not held firmly together
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Figure 5 — Pinned connections
In case of significant movement between the pin and the bearing surface, consideration should be given to reducing the limit bearing force in order to reduce wear.
In case of reversing load consideration should be given to the avoidance of plastic deformation.
5.2.4.4 Connected parts, limit design force with respect to shear
The limit design force in a failure mode, where a piece of material is torn out, shall be based upon shear stress in a critical section. In general, a uniform shear stress distribution throughout the section is assumed.
The limit design shear force is calculated as follows:
3,
⋅
×=
m
ysRdv
fAF
γ (19)
with
( ) tssAs ×+= 21 in general and
tsAs ××= 2 for a symmetric construction as in Figure 6 a) and c),
where
yf is the yield stress of the material of the structural member in question
As is the shear area of the tear-out section
s,s1,s2 are shear lengths of the tear-out section. For constructions in accordance with Figure 6 the tear-out section is A-A and shear lengths are determined through a 40 degree rule as indicated.
t is the thickness of the member.
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Figure 6 — Connected parts
5.2.4.5 Connected parts, limit design force with respect to tensile stress
Design shall be based upon the maximum tensile stress at inner surface of the pin hole. Stress concentration due to geometry of the pin hole shall be considered.
The limit design force for the construction in accordance with Figure 6 a) is determined as follows:
spm
yRdv k
ftbF
γγ ×××××
=2
, (20)
with
ksp 95,0=γ
where
yf is the yield stress of the material of the structural member in question,
spγ is the specific resistance factor for tension at pinned connections,
k is the stress concentration factor, i.e. ratio between the maximum stress and the average stress in the section.For a construction with the geometric proportions as 1≤ c/b ≤2 and 0.5 ≤ b/d ≤1 (see Figure 6), the stress concentration factor k is taken from the Figure 7. The clearance between the hole and the pin are assumed to conform ISO 286-2 tolerances H11/h11 or closer. In case of a larger clearance, higher values of k shall be used.
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Figure 7 — Stress concentration factors for a specific type of pinned connection
NOTE Tensile loads or tensile parts of reversing loads only need to be considered within this clause. However, reversing load situations may require additional considerations where this may result in unacceptable plastic deformations or affect functionality of the connection (see 5.2.4.3).
5.2.5 Limit design stresses in welded connections
The limit design weld stress Rdw,f used for the design of a welded connection depends on:
the base material to be welded and the weld material used;
the type of the weld;
the type of stress evaluated in accordance with Annex C;
the weld quality.
Depending on the equation number given in Table 8, the limit design weld stress Rdw,f shall be calculated either by:
m
ykwRdw, γ
α ff
×= (21)
or by
m
uwwRdw, γ
α ff
×= (22)
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where
wα is a factor given in Table 8 in dependence on the type of weld, the type of stress and the material
ykf is the minimum value of the yield strength of the connected member under consideration
uwf is the ultimate tensile strength of the weld material (all weld metal)
Table 8 — Factor for limit weld stress
Direction of stress
Type of weld Type of stress Equation number
wα
960yk <f
N/mm² 960yk ≥f
N/mm²
Stress normal to the weld direction
Full penetration weld, matching weld material
Tension 21 1,0 0,93
Compression 21 1,0 0,93
Full penetration weld, undermatching weld materials
Tension 22 0,80 0,80
Compression 22 0,80 0,80
Partial penetration weld, matching weld materiala
Tension or compression
21 0,70 0,65
Partial penetration weld, undermatching weld materiala
Tension or compression
22 0,56 0,,56
All welds, matching weld material Shear 21 0,70 0,65
All welds, undermatching weld material
Shear 22 0,54 0,54
Stress parallel to the weld direction
All welds Tension or Compression
21 1,0 0,93
All welds, matching weld material Shear 21 0,60 0,55
Full penetration welds, undermatching weld material
Shear 22 0,50 0,50
Partial penetration weld, undermatching weld material
Shear 22 0,50 0,50
The values of wα are valid for welds in quality classes B and C of EN ISO 5817.
In case of connected members from different materials, the proof shall be made for each member separately.
Undermatching weld material: weld material with strength properties less than those of connected members aNote : An asymmetric weld is not recommended. However, if used connected members shall be supported so as to avoid the effect of load eccentricity on the weld.
The welds joining parts of built-up members, e.g. flange-to-web connections, may be designed without regard to normal stress parallel to the axis of the weld, provided the welds are proportioned to accommodate the shear forces developed between those parts.
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5.3 Execution of the proof
5.3.1 Proof for structural members
For the structural member to be designed it shall be proven that:
RdσSd f≤σ and τfRdSd ≤τ (23)
where
SdSd,τσ are the design stresses. The von Mises equivalent stress may be used as the design stress instead.
τff RdRdσ, are the corresponding limit design stresses in accordance with clause 5.2.2. In case von
Mises is used, Rdσf is the limit design stress.
In case of plane states of stresses when von Mises stresses are not used it shall additionally be proven that:
12
Sd
,,
ySd,xSd,2
,
ySd,2
,
xSd, ≤
+
××
−
+
RdτyRdxRdσyRdσxRdσ fffffτσσσσ
σ (24)
where
x, y indicate the orthogonal directions of stress components.
Spatial states of stresses may be reduced to the most unfavourable plane state of stress.
5.3.2 Proof for bolted connections
For each mode of failure of a connection it shall be proven for the most highly loaded member that:
RdSd FF ≤ (25)
where
SdF is the design force of the element, depending on the type of connection, e. g.
te,F for connections loaded in tension (see 5.2.3.3)
RdF is the limit design force in accordance with clause 5.2.3, depending on the type of the connection, i. e.
Rdv,F limit design shear force
Rdb,F limit design bearing force
Rds,F limit design slip force
Rdt,F limit design tensile force
NOTE Care should be taken in apportioning the total load into individual components of the connection.
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5.3.3 Proof for pinned connections
For pins, it shall be proven that:
Rdb,Sdbi,
Rdv,Sdv,
RdSd
FFFFMM
≤≤≤
(26)
where
SdM is the design value of the bending moment in the pin
RdM is the limit design bending moment in accordance with clause 5.2.4
Sdv,F is the design value of the shear force in the pin
Rdv,F is the limit design shear force in accordance with clause 5.2.4.2
Sdbi,F is the most unfavourable design value of the bearing force in the joining plate i of the pin connection
Rdb,F is the limit design bearing force in accordance with clause 5.2.4
NOTE In multi – pin connections care should be taken in apportioning the total load into individual components of the connection.
As a conservative assumption in the absence of a more detailed analysis the following equation may be used.
3bSd 4FlM ⋅= (27)
where
l is the distance between 1bF and b2F
b3F is the sum of b1F and b2F (see Figure 5)
5.3.4 Proof for welded connections
For the weld to be designed it shall be proven that:
sdw,σ and Rdw,Sdw, f≤τ (28)
where
Sdw,Sdw, , στ are the design weld stresses (see Annex C)
Rdw,f is the corresponding limit design weld stress in accordance with clause 5.2.5
In case of plane states of stresses (with orthogonal stress components ySd,w,xSd,w,Sdw, ,, σστ ) in welded connections it shall additionally be proven that:
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1,12
Rdw,
Sdw,
yRd,w,xRd,w,
ySd,w,xSd,w,2
yRd,w,
ySd,w,2
xRd,w,
xSd,w, ≤
+
××
−
+
fτ
ffffσσσσ
(29)
where
x, y indicate the orthogonal directions of stress components.
6 Proof of fatigue strength
6.1 General
A proof of fatigue strength is intended to prevent risk of failure due to formation and propagation of critical cracks in structural members or connections under cyclic loading. Where the design stress always is purely compressive in a uniaxial stress state, and hence crack propagation cannot occur, a proof of fatigue strength is not required.
In general, the proof shall be executed by applying the load combinations A in accordance with EN 13001-2, multiplied by the dynamic factors iφ , setting all partial safety factors γp = 1, and applying the resistances (i. e. limit design stresses) according to 6.2. In some applications a load from load combinations B (occasional loads) can occur frequently enough to require inclusion in the fatigue assessment. The stresses from these occasional loads shall be handled in the same way as those from the regular loads.
The stresses are calculated in accordance with the nominal stress concept. This document deals only with the nominal stress method. A nominal stress is a stress in the base material adjacent to a potential crack location, calculated in accordance with simple elastic strength of materials theory, excluding local stress concentration effects. The constructional details in Annex D and Annex H contain the influences illustrated in the figures and thus the characteristic fatigue strength values include the effects of:
local stress concentrations due to the shape of the joint and the weld geometry;
size and shape of acceptable discontinuities;
the stress direction;
residual stresses;
metallurgical conditions;
in some cases, the welding process and post-weld improvement procedures.
The effect of other geometric stress concentrations than those listed above (global stress concentrations) shall be included in the nominal stress by means of relevant stress concentration factors.
NOTE This standard does not use other methods like Hot Spot Stress Method. The bibliography gives information on literature about Hot Spot Stress Method.
For the execution of the proof of fatigue strength the cumulative damages caused by variable stress cycles shall be calculated. In this standard Palmgren-Miner's rule of cumulative damage is reflected by use of the stress history parameters (see Clause 6.3).
Mean-stress influence, as presented in EN 13001-1, in structures in as-welded condition (without stress relieving) can be considered but is negligible. Therefore the stress history parameter s is independent of the mean-stress and the fatigue strength is based on the stress range only.
In non-welded details or stress relieved welded details, the effective stress range to be used in the fatigue
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assessment may be determined by adding the tensile portion of the stress range and 60 % of the compressive portion of the stress range or by special investigation (see 6.5).
The fatigue strength specific resistance factor mfγ (given in Table 9) is used to account for the uncertainty of fatigue strength values and the possible consequences of fatigue damage.
Table 9 — Fatigue strength specific resistance factor gmf
mfγ
Accessibility Fail-safe components
Non fail-safe components
without hazards for persons
with hazards for persons
Accessible joint detail 1,0 1,10 1,20
Joint detail with poor accessibility 1,05 1,15 1,25
„Fail-safe“ structural components are those with reduced consequences of failure, such that the local failure of one component does not result in failure of the structure or falling of loads.
Non „fail-safe“ structural components are those where local failure of one component leads rapidly to failure of the structure or falling of loads.
6.2 Limit design stresses
6.2.1 Characteristic fatigue strength
The limit design stress of a constructional detail is characterized by the value of cσ∆ , the characteristic fatigue strength. cσ∆ represents the fatigue strength at 62 10× cycles under constant stress range loading and with a probability of survival equal to %7,97s =P (mean value minus two standard deviations obtained by normal distribution and single sided test), see Figure 8.
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Key a) principle b) simplification using one value for m (see EN 13001-1) 1 Constant stress range fatigue limit m is the slope constant of the fatigue strength curve. The curves have slopes of m/1− in the log/log representation.
NOTE This standard is based on the use of stress history parameter s which requires the use of the one slope simplification of the Nloglog −σ∆ curve as shown in Figure 8 b).
Figure 8 — Illustration of ∆∆∆∆σσσσ -N curve and ∆∆∆∆σσσσc
In the first column of Annex E the values of cσ∆ are arranged in a sequence of notch classes (NC) and with the constant ratio of 1,125 between the classes.
For shear stresses cσ∆ is replaced by cτ∆ .
The values of characteristic fatigue strength cσ∆ or cτ∆ and the related slope constants m of the Nloglog −σ∆ -curve are given in Annex D (normative) and Annex H (informative) for:
Table D.1: Basic material of structural members;
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Table D.2: Elements of non-welded connections;
Table D.3: Welded members;
Table H.1: Values of slope constant m of the Nloglog −σ∆ -curve and limit design stress range cσ∆ for connections and joints of hollow section girders;
Table H.2: Values of slope constant m of the Nloglog −σ∆ -curve and limit design stress range cσ∆ for lattice type connections of hollow section girders.
The given values apply for the defined basic conditions. For deviating conditions an appropriate notch class (NC) shall be selected one or more notch classes above (+ 1 NC, + 2NC, ...) to increase the resistance or below (- 1 NC, - 2 NC, ...) the basic notch class to decrease the resistance according to Annex D. The effects of several deviating conditions shall be added up.
6.2.2 Weld quality
cσ∆ -values in Annex D and Annex H depend on the quality level of the weld. Quality classes B, C, D shall be in accordance with EN ISO 5817. In Annex H class C is assumed. Lower quality than level D shall not be used. For the purpose of this standard an additional quality level B* can be used. The requirements in addition to those of level B given hereafter define quality level B*.
Additional requirements for quality level B*:
For the purpose of this standard 100 % NDT (non destructive testing) means inspection of the whole length of the weld with an appropriate method to ensure that the specified quality requirements are met.
For butt welds:
full penetration without initial (start and stop) points;
both surfaces machined or flush ground down to plate surface; grinding in stress direction;
the weld toe post-treated by grinding, remelting by TIG, plasma welding or by needle peening so that any undercut and slag inclusions are removed;
eccentricity of the joining plates less than 5 % of the greater thickness of the two plates;
sum of lengths of concavities of weld less than 5 % of the total length of the weld;
100 % NDT.
For parallel and lap joints:
transition angle of the weld to the plate surface shall not exceed 25°;
the weld toe post-treated by grinding, remelting by TIG, plasma welding or by needle peening;
100 % NDT.
All other joints:
full penetration;
transition angle of the weld to the web surface shall not exceed 25°;
the weld toe post-treated by grinding, remelting by TIG, plasma welding or by needle peening;
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100 % NDT;
eccentricity less than 10 % of the greater thickness of the two plates.
If TIG dressing is used as a post treatment of the potential crack initialization zone of a welded joint in order to increase the fatigue strength, welds of quality class C for design purposes may be upgraded to quality class B for any joint configuration.
6.2.3 Requirements for fatigue testing
Details not given in Annex D and Annex H or consideration of mean stress influence require special investigation into cσ∆ and m by tests.
Requirements for such tests are:
test specimen in actual size (1:1);
test specimen produced under workshop conditions;
the stress cycles shall be completely in the tensile range;
at least 7 tests per stress range level.
Requirements for determination of m and cσ∆ are:
cσ∆ shall be determined from numbers of cycles based on mean value minus two standard deviations in a log–log presentation;
at least one stress range level that results in a mean number of stress cycles to failure of less than 2x104 cycles shall be used;
at least one stress range level that results in a mean number of stress cycles to failure between 1,5x106 and 2,5x106 cycles shall be used.
A simplified method for the determination of m and cσ∆ may be used:
m shall be set to m = 3;
a stress range level that results in a mean number of stress cycles to failure of less than 1x105 cycles shall be used.
6.3 Stress histories
6.3.1 General
The stress history is a numerical presentation of all stress variations that are significant for fatigue. Using the established rules of metal fatigue the large number of variable magnitude stress cycles are condensed to one or two parameters. Stress histories shall be determined either through stress calculations or measurements, in both cases simulating the specified crane use.
Stress histories shall be represented in terms of maximum stress amplitudes and frequencies of occurrence of stress amplitudes.
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6.3.2 Frequency of occurence of stress cycles
For the proof of fatigue strength, stress histories are expressed as single-parameter representations of frequencies of occurrence of stress ranges by using methods such as the hysteresis counting method (Rainflow or Reservoir method) with the influence of mean stress neglected.
Each of the stress ranges is sufficiently described by its upper and lower extreme value.
bu σσσ∆ −= (30)
where
uσ is the upper extreme value of a stress range;
oσ is the lower extreme value of a stress range;
σ∆ is the stress range.
6.3.3 Stress history parameter
Stress history parameter s is calculated as follows, based on a one-parameter presentation of stress histories during the design life of the crane:
mm ks ×= ν (31)
where
t
iim ˆ N
nkm
i×
=∑ σ∆σ∆ (32)
ref
tNN
=ν (33)
where
ν is the relative total number of occurrences of stress ranges;
mk is the stress spectrum factor dependant on m;
iσ∆ is the stress range;
σ∆ ˆ the maximum stress range;
in is the number of occurrences of stress range i ;
∑=i
nN it is the total number of occurrences of stress ranges during the design life of the crane;
6ref 102 ×=N is the reference number of cycles;
m is the slope constant of the Nloglog −σ∆ -curve of the component under consideration.
Stress history parameter sm has a specific value for each structural detail. The value is related to crane duty and decisively depends on:
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the number of working cycles;
the net load spectrum;
crane configuration;
the effect of the crane motions on stress variations (traverse, slewing, luffing etc).
For thermally stress relieved or non-welded structural members the compressive portion of the stress range may be reduced to 60 %.
Stress histories characterized by the same value of sm may be assumed to be equivalent in respect to the damage in similar materials, details or components.
Proof of competence for fatigue may be omitted for structural members in cases, where the value of the stress history parameter is lower than 0,001 and the yield stress is 500 N/mm2 or lower.
NOTE An example for the determination of stress histories by simulation is given in an Annex F.
6.3.4 Stress history classes S
Members of crane structures may be arranged into classes S of the stress history parameter sm. The classification is based upon m = 3 and is specified in the Table 10 and illustrated in the Figure 9.
Where a class S is referred to in the proof of fatigue strength of a member, the value of stress history parameter s3 shall be taken in accordance with the Table 11.
Where a single stress history class S is used for the calculation of the whole structure, the most severe class occurring within the structure shall be used.
Table 10 — Classes S of stress history parameter s3
Class Stress history parameter
S02 0,001 < s3 ≤ 0,002
S01 0,002 < s3 ≤ 0,004
S0 0,004 < s3 ≤ 0,008
S1 0,008 < s3 ≤ 0,016
S2 0,016 < s3 ≤ 0,032
S3 0,032 < s3 ≤ 0,063
S4 0,063 < s3 ≤ 0,125
S5 0,125 < s3 ≤ 0,250
S6 0,250 < s3 ≤ 0,500
S7 0,500 < s3 ≤ 1,000
S8 1,000 < s3 ≤ 2,000
S9 2,000 < s3 ≤ 4,000 NOTE The classes S01 and S02 do not exist in EN 13001-1 but may be used.
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Key 1 fatigue assessment might not be required
3k is the stress spectrum factor based on m = 3
ν is the relative total number of occurrences of stress range
Figure 9 — Illustration of the classification of stress history parameter s for
A given stress history falls into specific class S , independent of the slope constant m of the relevant Nlog/log σ∆ -curve. The diagonal lines for the class limits represent the 3k to ν relationship for constant=s
in a log/log scale diagram.
6.4 Execution of the proof
For the detail under consideration it shall be proven that:
RdSd σ∆σ∆ ≤ (34)
σσσ∆ minmaxSd −= (35)
where
Sdσ∆ is the maximum range of design stresses, the same value that is used for σ∆ ˆ in 6.3.3.
maxσ, minσ are the extreme values of design stresses (compression stresses with negative sign).
Rdσ∆ is the limit design stress range
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Shear stresses τ are treated similarly.
For each stress component xσ , yσ and τ the proof shall be executed separately (where x,y indicate the orthogonal directions of stresses), In case of non welded details, if the normal and shear stresses induced by the same loading event vary simultaneously, or if the plane of the maximum principal stress does not change significantly in the course of a loading event, only the maximum principal stress range may be used.
6.5 Determination of the limit design stress range
6.5.1 Applicable methods
The limit design stress ranges Rdσ∆ for the detail under consideration shall be determined either by direct use of stress history parameter ms or by simplified method based on the use of class S .
6.5.2 Direct use of stress history parameter
The limit design stress range shall be calculated from:
m mmf
cRd
s×=
γσ∆σ∆ (36)
where
Rdσ∆ is the limit design stress range
cσ∆ is the characteristic fatigue strength (see Annex D and Annex H)
m is the slope constant of the Nloglog −σ∆ curve (see Annex D and Annex H)
mfγ is the fatigue strength specific resistance factor (see Table 9)
ms is the stress history parameter
6.5.3 Use of class S
6.5.3.1 Slope constant m
When the detail under consideration is related to a class S according to 6.3, the simplified determination of the limit design stress range is dependent on the (negative inverse) slope constant m of the log ∆σ –log N-curve.
6.5.3.2 Slope constant m = 3
Values of stress history parameter s corresponding to individual stress history classes S are selected according to Table 11.
Table 11 — Values of s3 for stress history classes S
Class S02 S01 S0 S1 S2 S3 S4 S5 S6 S7 S8 S9
3s 0,002 0,004 0,008 0,016 0,032 0,063 0,125 0,25 0,5 1,0 2,0 4,0 NOTE Values of stress history parameter s3 shown above are the upper limit values of ranges shown in Table 10.
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The limit design stress range shall be calculated from:
3 3mf
cRd
s×=
γσ∆σ∆ (37)
where
Rdσ∆ is the limit design stress range;
cσ∆ is the characteristic fatigue strength of details with m = 3 (see Annex D);
s3 is the classified stress history parameter (see Table 11);
mfγ is the fatigue strength specific resistance factor (see Table 9).
For mfγ = 1,25 Annex E gives the values of Rdσ∆ in dependence on the class S and cσ∆ .
6.5.3.3 Slope constant m ≠≠≠≠ 3
If the slope constant m of the Nloglog −σ∆ curve is not equal to 3, the limit design stress range is dependent on the class S and the stress spectrum factor km (see 4.4.4 of EN 13001-1).
The limit design stress range Rdσ∆ shall be calculated from:
*1,RdRd k×= σ∆σ∆ (38)
m 3mf
cRd,1
s×=
γσ∆σ∆ (39)
1*m
3 ≥= mkkk (40)
where
Rdσ∆ is the limit design stress range
Rd,1σ is the limit design stress range for k* = 1
*k is the specific spectrum ratio factor
cσ∆ , m are the characteristic values of stress range and the respective inverse slope of the
log ∆σ - log N-curve (see Annex D and Annex H)
3s is the classified stress history parameter (see Table 11)
mfγ is the fatigue strength specific resistance factor (see Table 9)
3k is the stress spectrum factor based on m = 3
mk is the stress spectrum factor based on m of the detail under consideration
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3k and mk shall be based on the same stress spectrum that is derived either from calculation or simulation
For mfγ = 1,25 and m = 5. Annex E gives the values of Rd,1σ∆ in dependence on the class S and cσ∆ .
6.5.3.4 Simplified method for slope constants m ≠≠≠≠ 3
k* = 1 covers the most unfavourable stress spectra for cases with m > 3 and sm < 1, and Rd,1σ∆ may then be used as limit design stress range. The value of k* may be calculated for k3 and km from the stress spectrum estimated by experience.
6.5.4 Independent concurrent normal and/or shear stresses
In addition to the separate proof for σ and τ (see 6.4), the action of independently varying ranges of normal and shear stresses shall be considered by:
0,1mτc
Sdmfym,
yc,
ySd,mfxm,
xc,
xSd,mfτyx
≤⋅
×+×
×+×
×sss
mmm
τ∆τ∆γ
σ∆σ∆γ
σ∆σ∆γ
(41)
where
Sdσ∆ , Sdτ∆ are the calculated maximum ranges of design stresses
cσ∆ , cτ∆ are the characteristic fatigue strengths
mfγ is the fatigue strength specific resistance factor (see Table 9)
ms is the stress history parameter
m is the slope constant of Nloglog −σ∆ curve
x , y indicate the orthogonal directions of normal stresses
τ indicates the respective shear stress
7 Proof of static strength of hollow section girder joints
The proof shall be executed in accordance with Clause 7 of EN 1993-1-8:2005, if not otherwise given in Clause 8 of EN 13001-3.1.
8 Proof of elastic stability
8.1 General
The proof of elastic stability is made to prove that ideally straight structural members or components will not lose their stability due to lateral deformation caused solely by compressive forces or compressive stresses. Deformations due to compressive forces or compressive stresses in combination with externally applied bending moments, or in combination with bending moments caused by initial geometric imperfections, shall be assessed by the theory of 2nd order as part of the proof of static strength. This chapter covers global buckling of members under compression and local buckling of plate fields subjected to compressive stresses.
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NOTE Further information may be found in the bibliography.
8.2 Lateral buckling of members loaded in compression
8.2.1 Critical buckling load
The critical buckling load Nk is the smallest bifurcation load according to elastic theory. For members with constant cross section, Nk is given in Table 12 for a selection of boundary conditions, also known as Euler’s buckling cases.
Table 12 — Critical buckling load Nk for Euler’s buckling cases.
Euler case no 1 2 3 4 5
Boundary conditions
Nk 2
2
4 LIE
×××π
2
2
LIE ××π
2
205,2L
IE ×××π 2
24L
IE ×××π 2
2
LIE ××π
E is the elastic modulus;
I is the moment of inertia of the member in the plane of the figure;
L is the length of the member.
For other boundary conditions or for members consisting of several parts i, with different cross sections, Nk may be computed from the differential equation, or system of differential equations, of the elastic deflection curve in its deformed state, which has the general solution:
iiiiii )sin()cos( DxCxkBxkAy +×+××+××= , i
i IENk×
= (42)
where:
x is the longitudinal coordinate;
y is the lateral coordinate in the weakest direction of the member;
E is the elastic modulus;
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Ii is the moment of inertia of part i in the weakest direction of the member;
N is the compressive force;
Ai, Bi, Ci, Di are constants to be found by applying appropriate boundary conditions;
The critical buckling load Nk is found as the smallest positive value N that satisfies Equation (42), or system of Equations (42), when solved with the appropriate boundary conditions applied.
8.2.2 Limit compressive design force
The limit compressive design force NRd for the member or its considered part is computed from the critical buckling load Nk by:
m
ykRd γ
κ AfN
××= (43)
where:
κ is a reduction factor;
fyk is the compressive yield stress;
A is the cross section area of the member.
The reduction factor κ is computed from the slenderness λ, which is given by:
k
yk
NAf ×
=λ (44)
where:
Nk is the critical buckling load according to 8.2.1.
Depending on the value of λ and the cross section parameter α, the reduction factor κ is given by:
λ ≤ 0,2: 0,1=κ
0,2 < λ ≤ 3,0: 22
1
λξξκ
−+= [ ]2)2,0(15,0 λλαξ +−×+×= (45)
λ > 3,0: )(
1αλλ
κ+×
=
Depending of the type of cross section, the parameter α is given in Table 13.
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Table 13 — Parameter αααα and acceptable bow imperfections for various cross sections.
Type of cross section
Buckling about axis
2mmN
y 460<f 2mm
Ny 460≥f
α Acceptable maximum
bow imperfectio
n
α Acceptable maximum
bow imperfectio
n
1 Hollow sections
Hot rolled zzyy
−−
0,21
300L 0,13 350L
Cold formed zzyy
−−
0,34 250L 0,3
4 250/L
2 Welded box sections
zzyy
−−
0,34 250L 0,3
4 250/L
Thick welds and
3030
zz
yy
<
<
thth zz
yy−−
0,49 200L 0,4
9 200L
3 Rolled sections
;2,1>bh
mm40≤t zzyy
−−
0,21
0,34
300L 250L
0,13
0,13
350L 350L
;2,1>bh mm80mm40 ≤< t
;2,1≤bh mm80≤t
zzyy
−−
0,34
0,49
250L 200L
0,21
0,21
300L 300L
mm80>t zzyy
−−
0,76 150L 0.4
9 200L
4 Welded I sections
mm40i ≤t zzyy
−−
0,34
0,49
250L 200L
0,34
0,49
250l 200l
mm40i >t zzyy
−−
0,49
0,76
200L 150L
0,49
0,76
200L 150L
5 Channels, L, T and solid sections
zzyy
−−
0,49 200L 0,4
9 200L
NOTE : L is the length of the member
In case of a member with varying cross section, the equations in 8.2.2 shall be applied to all parts of the member. The smallest resulting value of NRd shall be used, and in addition it shall be conform to the following:
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m
kRd 2,1 γ×
≤ NN (46)
NOTE Special consideration should be given to members with thin-walled cross sections which are susceptible to local buckling and possible reduction in their limit compressive design force NRd
8.3 Buckling of plate fields subjected to compressive and shear stresses
8.3.1 General
Plate fields are unstiffened plates that are supported only along their edges or plate panels between stiffeners.
It is assumed that:
geometric imperfections of the plate are less than the maximum values shown in Table 14,
stiffeners are designed with sufficient stiffness and strength to allow the required buckling resistance of the plate to be developed (i.e. buckling strength of stiffeners is greater than that of the plate field),
the plate field is supported along its edges as shown in Table 15.
there is no instability resulting from the interaction between the local buckling of the plate field and the global buckling of the member containing it, such case is not covered by this standard.
Table 14 — Maximum allowable imperfection f for plates and stiffeners
1 2 3 4
1
Unstiffened plates
General
250mlf =
bawhereblbawhereal
m
m2,2
2,>=
≤=
2 Subject to transverse
compression
250mlf =
abwherealabwherebl
m
m2,2
2,>=
≤=
3 Longitudinal stiffeners in plates with longitudinal
stiffening
400af =
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Table 14 - (continued)
4 Transverse stiffeners in plates with longitudinal
and transverse stiffening
400af =
400bf =
f shall be measured in the perpendicular plane.
ml is the gauge length.
Figure 10 shows a plate field with dimensions a and b (side ratio α = a/b). It is subjected to longitudinal stress varying between xσ ( maximum compressive stress) and xσψ . along its end edges, coexistent shear stressτ and with coexistent transverse stress yσ ,(e.g. from wheel load, see Annex C.4) applied on one side only.
Figure 10 — Stresses applied to plate field
8.3.2 Limit design stress with respect to longitudinal stress xσ
The limit design compressive stress fb,Rd,x is calculated from:
m
ykxRd,b, γ
κ ff x ×
= (47)
where:
κx is a reduction factor according to Equation (48);
fyk is the minimum yield stress of the plate material.
The reduction factor κ is given by:
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0,122,012 <
−×=xx
x cλλ
κ for 673,0>xλ (48)
0,1=xκ for 673,0≤xλ
with ψ×−= 12,025,1c , 25,1≤c
where:
λx is a non-dimensional plate slenderness according to Equation (49);
ψ is the edge stress ratio of the plate, relative to the maximum compressive stress.
The non-dimensional plate slenderness λx is given by:
eσ
yk
σλ
×=
kf
x (49)
where:
σe is a reference stress according to Equation (50);
kσ is a buckling factor given in Table 14.
The reference stress σe is given by:
2
2
2e
)1(12
×
−××=
btE
υπσ (50)
where:
Ε is the elastic modulus of the plate;
ν is the Poisson’s ratio of the plate;
t is the plate thickness;
b is the width of the plate field.
The buckling factor kσ depends on the edge stress ratio ψ, the side ratio α and the edge support conditions of the plate field. Table 15 gives values for the buckling factor kσ for plate fields supported along both transverse and longitudinal edges (Case 1) and plate fields supported along both transverse edges but only along one longitudinal edge (Case 2).
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Table 15 — Buckling factor kσσσσ
Case 1 Case 2
1 Type of support
Supported along all four edges
Supported along both loaded (end) edges and along only one longitudinal edge.
2 Stress distribution
3 1=ψ 4 0,43
4 01 >> ψ 05,1
2,8+ψ
34,0
578,0+ψ
207,021,057,0 ψψ +−
5 0=ψ 7,81 1,70 0,57
6 10 −>> ψ 278,929,681,7 ψψ +− 21,17570,1 ψψ +− 207,021,057,0 ψψ +−
7 1−=ψ 23,9 23,8 0,85
8 1−<ψ 5.98 x (1-ψ)2 23,8 207,021,057,0 ψψ +−
NOTE For Case 1 the values and equations for buckling factors σk given in Table 14 for plate fields supported along all four edges can give overly conservative results for plate fields with 0,1<α for rows 3 to 6 and 66,0<α for row 7. For Case 2 the results can be overly conservative for plate fields with 0,2<α . Further information regarding alternative values for short plate fields can be found in additional references, see bibliography.
8.3.3 Limit design stress with respect to transverse stress yσ
The limit design transversal normal stress shall be calculated from:
m
ykyyRdb
ff
γκ .
,, = (51)
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yκ is a reduction factor according to Equation (52);
ykf is the minimum yield stress of the plate material.
The reduction factor yκ is given by:
−×= 2
22,0113,1yy
yλλ
κ for 831,0>yλ (52)
0,1=yκ for 831,0≤yλ
The non-dimensional plate slenderness yλ is given by:
cak
fy
××=
eσ
yk
σλ (53)
where:
σe is a reference stress according to Equation (50);
kσ is a buckling factor determined using figure 10;
a is the plate field length
c is the width over which the transverse load is distributed ( 0=c , corresponds to a point load)
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Figure 11 — Buckling factor σk
8.3.4 Limit design stress with respect to shear stress ττττ
The limit design buckling shear stress is calculated from:
m
ykRdb
ff
γ
κττ
.3
.,, = (54)
where
τκ is a reduction factor given by:
ττ λ
κ 84,0= for 84,0≥τλ (55)
1=τκ for 84,0<τλ
where
3.. e
yk
k
f
σλ
ττ = (56)
ykf is the minimum yield strength of the plate material
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τk is a buckling factor calculated (for a plate field supported along all four edges) using equations given in table 16.
Table 16 — Buckling factor τk
α τk
α > 1 2434,5
ατ +=k
α ≤ 1 234,54
ατ +=k
8.4 Execution of the proof
8.4.1 Members loaded in compression
For the member under consideration, it shall be proven that:
RdSd NN ≤ (57)
where:
NSd is the design value of the compressive force;
NRd is the limit design compressive force according to 8.2.2.
8.4.2 Plate fields
8.4.2.1 Plate fields subjected to longitudinal or transverse compressive stress
For the plate field under consideration, it shall be proven that:
xRd,b,xSd, f≤σ and yRd,b,ySd, f≤σ (58)
where:
σSd,x , σSd,y are the design values of the compressive stresses xσ or yσ ;
fb,Rd,x , fb,Rd,y are the limit design compressive stresses in accordance with 8.3.2 and 8.3.3
8.4.2.2 Plate fields subjected to shear stress
For the plate field under consideration, it shall be proven that:
ττ Rd,b,Sd f≤ (59)
where:
Sdτ is the design value of the shear stress;
τRd,b,f is the limit design shear stress in accordance with 8.3.4.
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8.4.2.3 Plate fields subjected to coexistent normal and shear stresses
For the plate field subjected to coexistent normal (longitudinal and/or transverse) and shear stresses, apart from a separate proof carried out for each stress component in accordance with 8.4.2.1 and 8.4.2.2, it shall be additionally proven that:
1.
. 321
,,,,,,
,,
,,
,
,,
, ≤
+
×−
+
e
Rdb
Sd
yRdbxRdb
ySdxSde
yRdb
ySde
xRdb
xSd
fffV
ff τ
τσσσσ (60)
where 4
1 1 xe κ+= (61)
42 1 ye κ+= (62)
23 1 τκκκ ××+= yxe (63)
and with xκ calculated in accordance with 8.3.2, yκ in accordance with 8.3.3 and τκ in accordance with 8.3.4.
( )6yxV κκ ×= for 0,, >× ySdxSd σσ (64)
1−=V for 0,, <× ySdxSd σσ
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Annex A (informative)
Limit design shear force Fv,Rd per fit bolt and per shear plane for
multiple shear plane connections
Table A.1 — Limit design shear force Fv,Rd per fit bolt and per shear plane for multiple shear plane connections
Fit bolt Shank
diameter
mm
Fv,Rd
kN
Fit bolt material
for γγγγRb = 1,1
4.6 5.6 8.8 10.9 12.9
M12 13 16,7 20,9 44,6 62,8 75,4
M16 17 28,6 35,7 76,2 107,2 128,6
M20 21 43,5 54,4 116,2 163,2 196,1
M22 23 52,2 65,3 139,4 196,0 235,2
M24 25 61,8 77,3 164,9 231,9 278,3
M27 28 77,6 97,0 206,9 291,0 349,2
M30 31 95,1 111,8 253,6 356,6 428,0
Table A.2 — Limit design shear force Rdv,F in the shank per standard bolt and per shear plane for multiple shear plane connections
Rdv,F
kN
Bolt Shank
diameter
mm
Bolt material
for 1,1Rb =γ
4.6 5.6 8.8 10.9 12.9
M12 12 14,2 17,8 37,9 53,4 64,1
M16 16 25,3 31,6 67,5 94,9 113,9
M20 20 39,5 49,4 105,5 148,4 178,0
M22 22 47,8 59,8 127,6 179,5 215,4
M24 24 56,9 71,2 151,9 213,6 256,4
M27 27 72,1 90,1 192,3 270,4 324,5
M30 30 89,0 111,3 237,4 333,9 400,6
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Annex B (informative)
Preloaded bolts
Table B.1 — Tightening torques in Nm to achieve the maximum allowable preload level y7,0 F×
Bolt size Bolt material
8.8 10.9 12.9
M12 86 122 145
M14 136 190 230
M16 210 300 360
M18 290 410 495
M20 410 590 710
M22 560 790 950
M24 710 1 000 1 200
M27 1 040 1 460 1 750
M30 1 410 2 000 2 400
M33 1 910 2 700 3 250
M36 2 460 3 500 4 200
Note A friction coefficient µ = 0,14 is assumed in the calculations of the preceding tightening torques.
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Table B.2 — Limit design slip force FS,Rd per bolt and per friction interface using a design preloading force sybdp, 7,0 AfF ××=
Bolt stress area
AS
mm2
Design preloading force Fp,d in kN
Bolt material
Limit design slip force Fs,Rd in kN γγγγm = 1.1, γγγγss = 1.14
Bolt material
8.8
Slip factor ::::
10.9
Slip factor ::::
12.9
Slip factor ::::
8.8 10.9 12.9 0.50 0.40 0.30 0.20 0.50 0.40 0.30 0.20 0.50 0.40 0.30 0.20
M12 84,3 37,8 53,1 63,7 15,1 12,0 9,0 6,0 21,2 16,9 12,7 8,5 25,4 20,3 15,2 10,2
M14 115 51,5 72,5 86,9 20,5 16,4 12,3 8,2 28,9 23,1 17,3 11,6 34,7 27,7 20,8 13,9
M16 157 70,3 98,9 119 28,0 22,4 16,8 11,2 39,4 31,6 23,7 15,8 47,3 37,9 28,4 18,9
M18 192 86,0 121 145 34,3 27,4 20,6 13,7 48,2 38,6 28,9 19,3 57,9 46,3 34,7 23,2
M20 245 110 154 185 43,8 35,0 26,3 17,5 61,5 49,2 36,9 24,6 73,9 59,1 44,3 29,5
M22 303 136 191 229 54,1 43,3 32,5 21,6 76,1 60,9 45,7 30,4 91,3 73,1 54,8 36,5
M24 353 158 222 267 63,1 50,4 37,8 25,2 88,7 70,9 53,2 35,5 106 85,1 63,8 42,6
M27 459 206 289 347 82,0 65,6 49,2 32,8 115 92,2 69,2 46,1 138 111 83,0 55,3
M30 561 251 353 424 100 80,2 60,1 40,1 141 113 84,6 56,4 169 135 101 67,6
M33 694 311 437 525 124 99,2 74,4 49,6 174 139 105 69,7 209 167 126 83,7
M36 817 366 515 618 146 117 87,6 58,4 205 164 123 82,1 246 197 148 98,5
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Annex C (normative)
Design weld stress σσσσW,Sd and ττττW,Sd
C.1 Butt joint
Normal weld design stress Sd,Wσ and shear weld design stress Sd,Wτ are calculated from:
rr laF×
= σW,Sdσ ;
rr
τla
F×
=SdW,τ (C.1)
where
σF is the acting normal force (see Figure C.1);
τF is the acting shear force (see Figure C.1);
ra is the effective weld thickness;
rl is the effective weld length.
Figure C.1 — Butt weld
The effective weld thickness ra is calculated from:
( )21,min ttar ≤ for full penetration welds
i2 aar ×= for double sided symmetrical partial penetration welds
where
ia is the thickness of either welds
NOTE Single sided partial penetration butt welds with transverse loads are not covered by this standard.
In general, the effective weld length lr is given by:
rr all ×−= 2W (for continuous welds)
unless measures are taken to ensure that the whole weld length is effective, in which case Wllr =
prEN 13001-3-1:2010 (E)
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where
Wl is the weld length (see Figure C.1);
ra is the effective weld thickness.
1t , 2t thicknesses of the plates.
C.2 Fillet weld
Normal weld design stress dSW,σ and shear weld design stress SdW,τ are calculated from:
r2r2r1r1
σW,Sd lala
F×+×
=σ , r2r2r1r1
SdW, lalaFτ
×+×=τ (C.2)
where
σF is the acting normal force (see Figure C.2);
τF is the acting shear force (see Figure C.2);
ria are the effective weld thicknesses (see Figure C.2);
with iri aa =
ril are the effective weld lengths.
Figure C.2 — Joint dimensions
The effective weld thickness ar is limited to:
),min(7,0 21r tta ×≤ .
For the effective weld lengths see C.1.
Single sided welds may be used loaded with forces as shown in Figure C.2.
For single sided welds, Sd,Wσ and Sd,Wτ are calculated in an analogous manner using the relevant weld parameters.
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C.3 T-joint with full and partial penetration
Normal weld design stress SdW,σ and shear weld design stress SdW,τ are calculated from:
r2r2r1r1
σSdW, lala
F×+×
=σ , r2r2r1r1
SdW, lalaFτ
×+×=τ (C.3)
where
σF is the acting normal force (see Figure C.3);
τF is the acting shear force (see Figure C.3);
ria are the effective weld thicknesses (see Figure C.3);
with hiiri aaa +=
ril are the effective weld lengths.
Figure C.3 — Joint dimensions
The effective weld thickness ra is limited to:
),min(7,0 21r tta ⋅≤ .
For the effective weld lengths see C.1.
Single sided welds may be used loaded with forces as shown in Figure C.3.
For single sided welds, SdW,σ and SdW,τ are calculated in an analogous manner using the relevant weld parameters.
C.4 Effective distribution length under concentrated load
For simplification the normal design stresses in the weld and parent material under concentrated load may be calculated using the effective distribution length as follows
λκ +××= tan2 dhlr (C.4)
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where
rl is the effective distribution length ;
dh is the distance between the section under consideration and contact level of acting load ;
λ is the length of the contact area.
For wheels λ may be set to: r×= 2,0λ with mm 50max =λ
where
r is the radius of wheel;
κ is the dispersion angle. κ shall be set to °≤ 45κ .
Figure C.4 — Concentrated load
Other calculations for the determination of the design stresses may be used, however the values for cσ∆ and cτ∆ in Annex D are based on the calculation presented herein.
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Annex D (normative)
Values of slope constant m
and characteristic fatigue strength ∆∆∆∆σσσσc, ∆∆∆∆ττττc
Notch classes (NC) refer to the first column of Annex E (see 6.2.1).
Table D.1 — Basic material of structural members
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
1.1
m = 5
Plates, flat bars, rolled profiles under normal stresses
General requirements: Rolled surfaces No geometrical notch
effects (e.g. cut outs) Surface roughness
values before surface treatment such as shot blasting
140 Independent of fy
- Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed)
140 180 ≤ fy ≤ 220 - Surface condition in accordance with EN10163 classes A3 or C3
- Surface roughness Rz ≤ 100µm
- Edges rolled or machined or no free edges
- Any burrs and flashes removed from rolled edges
- Surface roughness Rz ≤ 60 µm +1 NC
160 220 < fy ≤ 320
180 320 < fy ≤ 500
200 500 < fy
180 180 ≤ fy ≤ 220 - Surface condition in accordance with EN10163 classes A3 or D3
- Surface roughness Rz ≤ 20µm
- Edges machined or no free edges
200 220 < fy ≤ 320
225 320 < fy ≤ 500
250 500 < fy ≤ 650
280 650 < fy ≤ 900
315 900 < fy
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Table D.1 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
1.2 m = 5
Edges in plates, flat bars, rolled profiles under normal stresses
- General requirements: - Rolled surfaces - Thermal cut edges - No geometrical notch effects
(e. g. cutouts) - Surface roughness values
before surface treatment such as shot blasting
140 Independent of fy
- Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed)
- Edge quality in accordance with Table 5 Range 3 of EN ISO 9013
140 180 ≤ fy ≤ 220 - Edge quality in accordance
with Table 5 Range 3 of EN ISO 9013
- Surface condition in accordance with EN10163 classes A3 or C3
- Surface roughness Rz ≤ 100µm
- Mill scale removed before cutting
- Machine controlled cutting - Plate surface roughness Rz
≤60µm and edge quality in accordance with Table 5 Range 2 of EN ISO 9013 +1NC
160 220 < fy ≤ 500
180 500 < fy
160 180 ≤ fy ≤ 220 - Edge quality in accordance with Table 5 Range 1 of EN ISO 9013
- Surface condition in accordance with EN10163 classes A3 or C3
- Plate surface roughness Rz ≤20µm
- Mill scale removed before cutting
- Machine controlled cutting
180 220 < fy ≤ 320
200 320 < fy ≤ 500
225 500 < fy ≤ 650
250 650 < fy ≤ 900
280 900 < fy
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Table D.1 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
1.3
m = 5
Hole edges in a plate under normal stresses
General requirements: - Nominal stress calculated for the
net cross-section - Holes not flame cut, - Bolts may be present as long as
these are stressed to no more than 20 % of their strength in shear/ bearing connections or to no more than 100 % of their strength in slip-resistant connections
80 Independent of fy - Holes may be punched
100 180 < fy ≤ 220 - Holes machines or thermal cut to a quality in accordance with Table 5 Range 3 of EN ISO 9013
- Holes not punched - Burr on hole edges removed - Rolled surface condition in
accordance with EN 10163 classes A3 or C3
- Plate surface roughness Rz ≤100µm
112 220 < fy ≤ 320
125 320 < fy ≤ 500
140 500 < fy ≤ 650
160 650 < fy
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Table D.1 - Concluded
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
1.4
m = 5
Plates, flat bars, rolled profiles under shear stress
- General requirements: - Rolled surfaces - No geometrical notch effects (e.g.
cut outs) - Surface roughness values before
surface treatment such as shot blasting
90 Independent of fy - Surface condition in accordance
with EN10163 classes A1 or C1 (repair welding allowed)
90 180 ≤ fy ≤ 220 - Surface condition in accordance with EN10163 classes A3 or C3
- Surface roughness Rz ≤ 100µm
- Edges rolled or machined or no free edges
- Any burrs and flashes removed from rolled edges
- Surface roughness Rz ≤ 60 µm +1 NC
100 220 < fy ≤ 320
112 320 < fy ≤ 500
125 500 < fy
112 180 ≤ fy ≤ 220 - Surface condition in accordance with EN10163 classes A3 or D3
- Surface roughness Rz ≤ 20µm
- Edges machined or no free edges
125 220 < fy ≤ 320
140 320 < fy ≤ 500
160 500 < fy ≤ 650
180 650 < fy ≤ 900
200 900 < fy
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Table D.2 —Elements of non-welded connections
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
2.1
m = 5
Double shear
The proof of fatigue strength is not
required for bolts of friction grip type
bolted connections
Nominal stress calculated for the net
cross-section
Supported single-shear
(example)
Single-shear
Perforated parts in slip-resistant bolted connections under normal stresses
160 275y ≤f
180 y275 f<
2.2 m = 5
Perforated parts in shear/bearing connections under normal stresses
double-shear and supported single-shear
Nominal stress calculated for the net cross-section
180 Normal stress
2.3 m = 5
Perforated parts in shear/bearing connections under normal stresses
single-shear joints, not supported
Nominal stress calculated for the net cross-section
125 Normal stress
2.4
m = 5 Fit bolts in double-shear or supported single-shear joints Uniform distribution of stresses is assumed
125 Shear stress (∆τc)
355 Bearing stress (∆σc)
2.5
m = 5 Fit bolts in single-shear joints, not supported Uniform distribution of stresses is assumed
100 Shear stress (∆τc)
250 Bearing stress (∆σc)
2.6
m=3 Threaded bolts loaded in tension (bolt grade 8.8 or better) ∆σ calculated for the stress-area of the bolt, using bF∆
(see 5.2.3.3)
50 Machined thread
63 Rolled thread above M30
71 Rolled thread for M30 or smaller
NOTE Pinned connections are considered in the proof of fatigue strength as structural members.
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Table D.3 — Welded members
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.1
m = 3
Symmetric butt joint, normal stress across the
weld
Basic conditions:
symmetric plate arrangement
fully penetrated weld
Components with usual residual stresses
Angular misalignment < 1°
t1 = t2
or
slope <1:3
Special conditions:
Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
140 Butt weld, quality level B*
-2 NC
125 Butt weld, quality level B
-4 NC
112 Butt weld, quality level C
- 4 NC
3.2 m = 3
Symmetric butt joint, normal stress across the
weld
Basic conditions:
symmetric plate arrangement
fully penetrated weld
Components with usual residual stresses
Angular misalignment < 1°
Special conditions:
Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
80 Butt weld on remaining backing, quality level C
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.3
m = 3
Unsymmetrical supported butt joint, normal stress across the butt weld
Basic conditions:
fully penetrated weld
Supported parallel to butt weld:
e < 2⋅t2 + 10mm
Supported vertical to butt weld:
e < 12⋅t2
Components with usual residual stresses
slope ≤ 1:3
t2 - t1 ≤ 4 mm
Special conditions:
Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
Influence of slope and thickness t2-t1:
thickness 12 tt −
slope ≤4 ≤ 10 ≤ 50 > 50 ≤1:3 – -1NC -1NC -2NC ≤1:2 -1NC -1NC -2NC -2NC ≤1:1 -1NC -2NC -2NC -3NC >1:1 - -2NC -2NC -3NC -3NC
125 Butt weld, quality level B*
112 Butt weld, quality level B
100 Butt weld, quality level C
3.4 m = 3
Unsymmetrical supported butt joint, normal stress across the butt weld
Basic conditions:
fully penetrated weld
supported parallel to butt weld: e < 2⋅t2 + 10mm
supported vertical to butt weld:
e < 12⋅t2
components with usual residual stresses
t2 - t1 ≤ 10 mm
Special conditions:
components with considerable residual stresses (e. g. joint of components with
restraint of shrinkage) -1 NC
t2 - t1 > 10 mm -1 NC
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
80 Butt weld on remaining backing, quality level C
3.5
m = 3
Unsymmetrical unsupported butt joint, stress
across the butt weld
Basic conditions:
fully penetrated weld
components with usual residual stresses
t1/t2 > 0,84
slope ≤ 1:1
slope in weld or base material
Special conditions:
components with considerable residual stresses (e. g. joint of components with restraint of shrinkage)
-1 NC
-2 NC
100 Butt weld, quality level B* t1/t2 > 0,74 -1 NC
t1/t2 > 0,63 -2 NC
t1/t2 > 0,50 -3 NC
t1/t2 > 0,40 -4 NC
90 Butt weld, quality level B
80 Butt weld quality level C
3.6
m = 3
Butt joint with crossing welds, stress across the
butt weld
Basic conditions:
components with usual residual stresses
125 Butt weld, quality level B*
100 Butt weld, quality level B
90 Butt weld, quality level C
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.7
m = 3
Normal stress in weld direction
Special conditions:
no irregularities from start-stop-points in quality level C + 1 NC
welding with restraint of shrinkage - 1 NC
180 Continuous weld, quality level B
140 Continuous weld, quality level C
80 Intermittent weld, quality level C
3.8
m = 3
Cross or T-Joint, groove weld, normal stress across the weld
Basic conditions:
continuous weld
Special conditions:
automatic welding, no initial points + 1 NC
welding with restraint of shrinkage - 1 NC
112 K-weld, quality level B*
100 K-weld, quality level B
80 K-weld, quality level C
71 V-weld with full penetration and backing, quality level C
3.9 m = 3
Cross or T-Joint, symmetric double fillet weld
Basic conditions:
continuous weld
Special conditions:
automatic welding, no initial points + 1 NC
welding with restraint of shrinkage - 1 NC
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
45 Stress in weld throat )2/(w laF ××=σ
see Annex C
71 Quality level B Stress in the loaded plate at weld toe 63 Quality level C
3.10
m = 3
T-Joint, stresses from bending
45 Stress in weld throat Stress calculated with the applied bending moment and weld joint geometry taken into account
80 Stresses in plate at weld toe, Quality level B
71 Stresses in plate at weld toe, Quality level C
3.11
m = 3
Full penetration weld (double sided) with transverse compressive load
(e. g. wheel)
112 Quality level B
100 Quality level C
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.12 m=3
Full penetration weld (with backing) with transverse compressive load (e. g. wheel)
80 Quality level C
3.13 m = 3
Double fillet weld with transverse compressive load, (e. g. wheel), stress calculated in the plate
tat ⋅≤≤⋅ 7,05,0
71 Quality level C
3.14 m = 3
Partial penetration weld with transverse compressive load (e. g. wheel), stress calculated in the plate
tat ⋅≤≤⋅ 7,05,0
with a according to Annex C
p=1mm for t≤6mm
4tp ≥ for t>6mm
71 Quality level C
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.15 m = 3
Partial penetration weld with transverse load (e. g. underslung crab), stress calculated in the plate
tat ×≤≤× 7,05,0
with a according to Annex C
p=1mm for t ≤ 6mm
4tp ≥ for t > 6mm
63 Quality level C
3.16
m = 3
Continuous component with a welded cover plate
Basic conditions:
quality level C
continuous weld
distance c between the weld toe and rim of continuous component greater than 10 mm
Special conditions:
quality level B* +2 NC
quality level B +1 NC
quality level D - 1 NC
c < 10 mm - 1 NC
80 l ≤ 50 mm
71 50 mm < l ≤ 100 mm
63 l > 100 mm
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.17
m = 3
Continuous component with load carrying flange plate, stress in continuous component at end of connection
Basic conditions:
continuous fillet or groove weld
112 Flange plate with end chamfer ≤ 1:3; edge weld and end of flank weld in weld quality level B*
100 Flange plate with end chamfer ≤ 1:2; edge weld and end of flank
weld in weld quality level B*
3.18 m = 3
Continuous component with load carrying flange plate, stress in continuous component at end of connection
Basic conditions:
continuous fillet or groove weld
to ≤ 1,5 tu
80 Edge weld and end of flank weld in weld quality level B*
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.19
m = 3
Continuous component with load carrying flange plate, stress in continuous component at end of connection
Basic conditions:
continuous fillet or groove weld
63 Quality level B
56 Quality level C
3.20
m = 3
Overlapped welded joint, main plate
Basic conditions:
stressed area to be calculated from:
rs ltA ×=
),min( Lmr lbbl +=
see also detail 3.32
80 Quality level B*
71 Quality level B
63 Quality level C
3.21
m = 3
50
Overlapped welded joint, lap plates
Basic conditions:
stressed area to be calculated from:
)( 2L1LLs ttbA +×=
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.22
m = 3
Continuous component with longitudinally mounted parts, Parts rounded or chamfered
Basic conditions:
R ≥ 50 mm; α ≤ 60° for quality levels B or C
R ≥ 150 mm; α ≤ 45° for quality level B*
groove weld or allround fillet weld
Special conditions:
end welds in a zone of at least 5 t fully penetrated +1 NC
90 Quality level B*
80 Quality level B
71 Quality level C
3.23
m = 3
Continuous component with parts ending perpendicularly
Basis conditions:
allround fillet weld
quality level B, C
Special conditions:
single fillet weld -1 NC
weld quality level D -1 NC
80 l ≤ 50 mm
71 50 mm < l ≤ 100 mm
63 100 mm < l ≤ 300 mm
56 l > 300 mm
3.24 m = 3
Continuous component with longitudinally mounted parts, welded to edge
Basic conditions:
R ≥ 50 mm or α ≤ 60°
t2 ≤ t1
butt weld or all-round fillet weld
Special conditions:
R ≥ 150 mm or α ≤ 45° +1 NC
R < 50mm or α > 60° -2 NC
end welds in a zone of at least 5 t2 fully penetrated with quality level B* +1 NC
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
80 Quality level B
71 Quality level C
3.25
m = 3
Continuous component with overlapping parts
Basic conditions
c ≥ 10 mm
quality level C
Special conditions:
b ≤ 50 mm and quality level B +1 NC
quality level D -1 NC
c < 10 mm -1 NC
80 b ≤ 50 mm
71 50 mm < b ≤ 100 mm
63 b > 100 mm
3.26
m = 3
Continuous component to which parts are welded transversally
Basic conditions:
plate thickness t ≤ 12 mm
c ≥ 10 mm
quality level D not allowed for K-weld
Special conditions:
plate thickness t > 12 mm (Double fillet welds only) -1 NC
c < 10 mm -1 NC
K-weld instead of double fillet weld + 1 NC
quality level D instead of C-1 NC
112 Double fillet weld, quality level B*
100 Double fillet weld, quality level B
90 Double fillet weld, quality level C
71 Single fillet weld, quality level B, C
71 Partial penetration V-weld on remaining backing, quality level B, C
3.27 m = 3
Continuous component to which stiffeners are welded transversally
Basic conditions:
plate thickness t ≤ 12 mm
c ≥ 10 mm
Special conditions:
plate thickness t > 12 mm (double fillets only) -1 NC
c < 10 mm -1 NC K-weld instead of double
fillet weld +1 NC
quality level D instead of C -1 NC
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
112 Double fillet weld, quality level B*
100 Double fillet weld, quality level B
90 Double fillet weld, quality level C
71 Single fillet weld, quality level B, C
71 Partial penetration V-weld on remaining backing, quality level B, C
3.28
m = 3
Continuous component to which transverse parts or stiffeners are welded intermittently
63 Quality level C
50 Quality level D
3.29 m = 3
Continuous component with longitudinally mounted parts, parts through hole
For parts rounded or chamfered:
Basic conditions:
R ≥ 50 mm, α ≤ 60°
Special conditions:
R ≥ 100 mm, α ≤ 45° +1 NC
end welds in the zone of at least 5 t fully penetrated +2 NC
80 Parts rounded or chamfered
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
56 Parts ending perpendicularly
3.30
m = 3
Tubes under axial and bending loads, normal stresses calculated in the tube
Basic conditions:
quality level C
groove weld fully penetrated
fillet weld thickness a > 0,7 tube thickness
flange thickness greater than two times tube thickness (for middle figure)
Special conditions:
quality B +1 NC
quality B* +2 NC
80 Butt weld, cylindrical tube (case a)
63 Groove weld, cylindrical tube (case b)
56 Groove weld, rectangular tube (case b)
45 Double fillet weld, cylindrical tube (case c)
40 Double fillet weld, rectangular tube (case c)
3.31
m = 5
Continuous groove weld, single or double fillet weld under uniform shear flow
Basic conditions:
quality level C
components with usual residual stresses
Special conditions:
components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
no initial points +1 NC
112 With full penetration
90 Partial penetration
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Table D.3 - Continued
Detail
No.
∆∆∆∆σσσσc ∆∆∆∆ττττc
N/mm2 Constructional detail Requirements
3.32 m = 5
Weld in lap joint, shear with stress concentration
Basic conditions:
load is assumed to be transferred by longitudinal welds only
71 Quality level B
63 Quality level C
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Annex E (normative)
Calculated values of limit design stress range ∆∆∆∆σσσσRd
One row is representing a notch class (NC) for basic conditions. +1 NC is one line above, -1 NC is one line below.
Table E.1 — Details with 3=m and 25,1mf =γ
NC, ∆σ∆σ∆σ∆σc
N/mm2
∆σ∆σ∆σ∆σRd
N/mm2
S02 S01 S0 S1 S2 S3 S4 S5 S6 S7 S8 S9
355 2254,1 1789,1 1420,0 1127,1 894,5 713,7 568,0 450,8 357,8 284,0 225,4 178,9
315 2000,1 1587,5 1260,0 1000,1 793,8 633,3 504,0 400,0 317,5 252,0 200,0 158,8
280 1777,9 1411,1 1120,0 888,9 705,6 562,9 448,0 355,6 282,2 224,0 177,8 141,1
250 1587,4 1259,9 1000,0 793,7 630,0 502,6 400,0 317,5 252,0 200,0 158,7 126,0
225 1428,7 1133,9 900,0 714,3 567,0 452,4 360,0 285,7 226,8 180,0 142,9 113,4
200 1269,9 1007,9 800,0 635,0 504,0 402,1 320,0 254,0 201,6 160,0 127,0 100,8
180 1142,9 907,1 720,0 571,5 453,6 361,9 288,0 228,6 181,4 144,0 114,3 90,7
160 1015,9 806,3 640,0 508,0 403,2 321,7 256,0 203,2 161,3 128,0 101,6 80,6
140 888,9 705,6 560,0 444,5 352,8 281,5 224,0 177,8 141,1 112,0 88,9 70,6
125 793,7 630,0 500,0 396,9 315,0 251,3 200,0 158,7 126,0 100,0 79,4 63,0
112 711,2 564,4 448,0 355,6 282,2 225,2 179,2 142,2 112,9 89,6 71,1 56,4
100 635,0 504,0 400,0 317,5 252,0 201,1 160,0 127,0 100,8 80,0 63,5 50,4
90 571,5 453,6 360,0 285,7 226,8 180,9 144,0 114,3 90,7 72,0 57,1 45,4
80 508,0 403,2 320,0 254,0 201,6 160,8 128,0 101,6 80,6 64,0 50,8 40,3
71 450,8 357,8 284,0 225,4 178,9 142,7 113,6 90,2 71,6 56,8 45,1 35,8
63 400,0 317,5 252,0 200,0 158,8 126,7 100,8 80,0 63,5 50,4 40,0 31,8
56 355,6 282,2 224,0 177,8 141,1 112,6 89,6 71,1 56,4 44,8 35,6 28,2
50 317,5 252,0 200,0 158,7 126,0 100,5 80,0 63,5 50,4 40,0 31,7 25,2
45 285,7 226,8 180,0 142,9 113,4 90,5 72,0 57,1 45,4 36,0 28,6 22,7
40 254,0 201,6 160,0 127,0 100,8 80,4 64,0 50,8 40,3 32,0 25,4 20,2
36 228,6 181,4 144,0 114,3 90,7 72,4 57,6 45,7 36,3 28,8 22,9 18,1
32 203,2 161,3 128,0 101,6 80,6 64,3 51,2 40,6 32,3 25,6 20,3 16,1
28 177,8 141,1 112,0 88,9 70,6 56,3 44,8 35,6 28,2 22,4 17,8 14,1
25 158,7 126,0 100,0 79,4 63,0 50,3 40,0 31,7 25,2 20,0 15,9 12,6
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Table E.2 — Details with 5=m and 25,1mf =γ
NC, ∆∆∆∆σσσσc
N/mm2
∆σ∆σ∆σ∆σRd,1,1,1,1
N/mm2
S02 S01 S0 S1 S2 S3 S4 S5 S6 S7 S8 S9
355 984,3 856,9 745,9 649,4 565,3 493,7 430,5 374,7 326,2 284,0 247,2 215,2
315 873,4 760,3 661,9 576,2 501,6 438,1 382,0 332,5 289,5 252,0 219,4 191,0
280 776,3 675,8 588,3 512,2 445,9 389,4 339,5 295,6 257,3 224,0 195,0 169,8
250 693,1 603,4 525,3 457,3 398,1 347,7 303,1 263,9 229,7 200,0 174,1 151,6
225 623,8 543,1 472,8 411,6 358,3 312,9 272,8 237,5 206,8 180,0 156,7 136,4
200 554,5 482,7 420,2 365,8 318,5 278,1 242,5 211,1 183,8 160,0 139,3 121,3
180 499,1 434,5 378,2 329,3 286,6 250,3 218,3 190,0 165,4 144,0 125,4 109,1
160 443,6 386,2 336,2 292,7 254,8 222,5 194,0 168,9 147,0 128,0 111,4 97,0
140 388,2 337,9 294,2 256,1 222,9 194,7 169,8 147,8 128,7 112,0 97,5 84,9
125 346,6 301,7 262,7 228,7 199,1 173,8 151,6 132,0 114,9 100,0 87,1 75,8
112 310,5 270,3 235,3 204,9 178,4 155,8 135,8 118,2 102,9 89,6 78,0 67,9
100 277,3 241,4 210,1 182,9 159,2 139,1 121,3 105,6 91,9 80,0 69,6 60,6
90 249,5 217,2 189,1 164,6 143,3 125,2 109,1 95,0 82,7 72,0 62,7 54,6
80 221,8 193,1 168,1 146,3 127,4 111,3 97,0 84,4 73,5 64,0 55,7 48,5
71 196,9 171,4 149,2 129,9 113,1 98,7 86,1 74,9 65,2 56,8 49,4 43,0
63 174,7 152,1 132,4 115,2 100,3 87,6 76,4 66,5 57,9 50,4 43,9 38,2
56 155,3 135,2 117,7 102,4 89,2 77,9 67,9 59,1 51,5 44,8 39,0 34,0
50 138,6 120,7 105,1 91,5 79,6 69,5 60,6 52,8 45,9 40,0 34,8 30,3
45 124,8 108,6 94,6 82,3 71,7 62,6 54,6 47,5 41,4 36,0 31,3 27,3
40 110,9 96,5 84,0 73,2 63,7 55,6 48,5 42,2 36,8 32,0 27,9 24,3
36 99,8 86,9 75,6 65,9 57,3 50,1 43,7 38,0 33,1 28,8 25,1 21,8
32 88,7 77,2 67,2 58,5 51,0 44,5 38,8 33,8 29,4 25,6 22,3 19,4
28 77,6 67,6 58,8 51,2 44,6 38,9 34,0 29,6 25,7 22,4 19,5 17,0
25 69,3 60,3 52,5 45,7 39,8 34,8 30,3 26,4 23,0 20,0 17,4 15,2
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Annex F (informative)
Evaluation of stress cycles (example)
The stress histories at a selected point of the structure depend on the loads, their direction and position during the use of the crane, as well as on the crane configuration.
The total number of working cycles of a crane during its useful life can be divided into several typical tasks with the numbers of working cycles corresponding to them.
A task can be characterized by a specific combinations of crane configuration and sequence of intended movements.
Before the sequence of stress peaks occurring during the performance of any task can be evaluated, the corresponding series of loadings has to be determined first, i.e. the magnitude, position and direction of all loads.
Key A System B Influence lines for bending at selected point j C Influence lines for shear at selected point j D Sequences of movements
E Extreme values of bending Mj and shear Qj (φ 2= 1) during sequences of movements
Figure F.1 — Example of load and moment variations due to load movements for tasks on a ship unloader
The unloader handles bulk material from ship to hopper or stockpile, the ranges of points to be served are given by the arrangement of the ship (points 12, 1 and 11), hopper (point 2) and stockpile (points 31 and 32).
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Figure F.1 shows the different sequences of movements of an unloader for two tasks considered, moving load from ship (point 11) to hopper (point 2) and moving load from stockpile (point 31) to hopper (point 2).
In the encoded description of each task, the point labels are:
linked by the sign “+” for working movements (with load) and “-“ for dead movements (without load);
underlined when the grab (load lifting attachment) is grounded.
The influence lines (representing the influences of loading and its position) for bending moment Mj and shear force Qj at the selected point j are shown for different loads (T for trolley, P for payload, A for lifting attachment, i.e. grab).
The description of salient points of the bending moment and shear load variations can be found in Table F.1.
Table F.1 – Description of salient points in bending moment and shear load variations
Point Trolley position Grab position Acting loads
a 11 Grounded T
b 11 Lifted T,A,P
c 2 Lifted T,A,P and T,A when load dropped
d 11 Lifted T,A
e 11 Grounded T
f 31 Grounded T
g 31 Lifted T,A,P
h 2 Lifted T,A,P and T,A when load dropped
i 31 Lifted T,A
j 31 Grounded T
The sequences of stresses arising from the bending moment Mj ( )(tσ = global bending stress) and the shear force Qj ( )(tτ = global shear stress) can be determined directly from the influence lines.
Stress cycles can be identified from the resulting sequences of stress peaks using one of the established stress cycle counting methods, such as the Rainflow counting method or the Reservoir method.
The complete stress history is obtained by summating the individual stress histories taken from the sequences of movements of all different tasks.
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Annex G (informative)
Calculation of stiffnesses for connections loaded in tension
The determination of stiffnesses of elements for the calculation of bolt joints in tension presented in this annex applies in the ideal cases shown in Figure G.1 assuming no more than 5 contact surfaces in practical joints. Adjacent bolts and/or the way of introduction of external forces into the system have great influence on the additional bolt force and should be considered in actual design.
Figure G.1 — Types of connections loaded in tension
The stiffnesses for connections in tension can be calculated as follows:
The stiffness of the connected parts is calculated from
eqK
c AlEK ×= (G.1)
where
cK is the stiffness (slope) of flanges
E is the modulus of elasticity
Kl is the effective clamped length (including all clamped components)
with 21K lll +=
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eqA is the equivalent area for calculation
The calculation of eqA is in dependence of AD (see Figure G.1):
for WA dD < :
)(4
2h
2Aeq dDA −×= π (G.2)
for KWAW ldDd +≤≤ :
−
+××−××+−×= 11)(
8)(
4
2
3 2A
WKWAW
2h
2Weq
DdldDdddA ππ (G.3)
for AKW Dld <+
−
+
+××××+−×= 11
)(8)(
4
2
3 2WK
WKWK
2h
2Weq
dldldlddA ππ (G.4)
where
AD is the diameter of the available cylinder of clamped material
wd is the diameter of the contact area under the bolt head
eqA is the equivalent area for calculation
hd is the diameter of the hole
Kl is the effective clamped length
The stiffness of the bolt is calculated from
×++×
××+××=r
22
1
b
5,0)4,02(411A
dld
dlEK π
(G.5)
where
bK is the stiffness (slope) of bolt
E is the modulus of elasticity
1l is the effective length for tension without thread
2l is the effective length for tension with thread
d is the shank diameter
rA is the root area of the bolt
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According to the shape of the connected parts, the external load is introduced to the bolt near its end (Figure G.2, case a), between the bolt end and the connection plane (case b) or close to the connection plane (case c). This may be considered in calculation of the stiffness ratio factor as follows:
cb
bL KK
K+
×= αΦ (G.6)
where
Φ is the stiffness ratio factor
Kb is the stiffness of bolt
Kc is the stiffness of connected parts
αL is the load introduction factor, see Figure G.2.
a) αL = 0,9 ...1 b) αL = 0,6 c) αL = 0,3
Figure G.2 — Values for the load introduction factor ααααL as a function of the connection shape
Case a) is typical for bolted connections in cranes. More precise values can be found in the literature. In cases where load introduction cannot be reliably specified, a conservative assumption αL = 1 should be used. In cases where the stiffness ratio factor Φ is determined by finite element analysis of the complete joint, the load introduction factor αL will become an in-built part of the analysis and the value αL = 1 shall be used with the Equation G.6.
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Annex H (informative)
Hollow Sections
Table H.1 — Values of inverse slope of ∆∆∆∆σσσσ –N-curve m and limit design stress range ∆∆∆∆σσσσc for connections and joints of hollow sections girders, m = 5
For site welding the given values of ∆σc should be multiplied by the factor 0,9.
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm
Constructional detail Requirements
1 90 2 < t0 ≤ 25 Butt joint with I- or V-weld
with weld backing
without backing weld
The admissible mismatch of the sections due to a change of the plate thickness is ≤ t0/3, but not more than max. 2 mm. In case of a higher mismatch, especially for a transverse plate butt of rectangular hollow section girders of different dimensions, ∆σc is reduced to 80 % of the given values.
90 8 < t0 ≤ 25
71 2 < t0 ≤ 8
2 80 2 < t0 ≤ 25 Butt joint with I- or V-weld
with weld backing
without weld backing
Requirements analogous to No. 1
80 8 < t0 ≤ 25
63 2 < t0 ≤ 8
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
3
63 2 < t0 ≤ 25 Transverse plate butt with semi V-welds (tp ≥ 2 to )
with weld backing
without weld backing
Requirements analogous to No. 1
63 8 < t0 ≤ 25
56 2 < t0 ≤ 8
4
56 2 < t0 ≤ 25 Transverse plate butt with semi V-welds (tp ≥ 2 to )
with weld backing
without weld backing
Requirements analogous to No. 1
56 8 < t0 ≤ 25
50 2 < t0 ≤ 8
5 45 2 < t0 ≤ 8
Transverse plate butt with semi V-welds (tp ≥ 2 to )
Requirements analogous to No. 1
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
6 40 2 < t0 ≤ 8
Transverse plate butt with semi V-welds (tp ≥ 2 to )
Fillet weld thickness a = t0
7
80 l ≤ 50 Longitudinally welded outer fin not bearing transverse loading in y-direction (2 < t0 ≤ 25)
Fillet weld thickness a:
for
2 < t0 ≤ 3:a = 2
for
3 ≤ t0 ≤ 25:a = 0,7⋅t0
71 50 < l ≤ 100
56 l > 100
8
100 t ≤ 6
Transversally welded outer fin with projection, not bearing transverse loading in y-direction (2 < to ≤ 25), (b > b0)
Fillet weld thickness a:
for
2 < t0 ≤ 3:a = 2
for
3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0,
but not more than a = 10
90 6 < t ≤ 12
80 12 < t ≤ 25
9
80 t ≤ 6 Transversally welded outer fin with projection, not bearing transverse loading in y-direction (2 < t0 ≤ 25), (b > b0)
Fillet weld thickness a:
for
2 < t0 ≤ 3:a = 2
for
3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0,
but not more than a = 10
71 6 < t ≤ 12
63 12 < t ≤ 25
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
10
80 t ≤ 6
Transversally welded outer fin without projection, not bearing transverse loading in y-direction (2 < t0 ≤ 25), (b ≤ 0,8 d0)
Fillet weld thickness a:
for
2 < t0 ≤ 3:a = 2
for
3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0,
but not more than a = 10
71 6 < t ≤ 12
63 12 < t ≤ 25
11
100 t ≤ 6
Transversally welded outer fin without projections, not bearing transverse loading in y-direction (2 < t0 ≤ 25), (b ≤ 0,8 b0)
Fillet weld thickness a:
for
2 < t0 ≤ 3:a = 2
for
3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0,
but not more than a = 10
90 6 < t ≤ 12
80 6 < t ≤ 12
12 63 2 < t0 ≤ 8
Welded-on hollow section girder, not bearing transverse loading in y-direction (b,d ≤ b0,d0)
Fillet weld thickness
a = t0
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
13
10 t0/t = 1
(b,d)/d0 = 0,6 Welded-on hollow section girder, bearing transverse loading F in y-direction (b,d ≤ d0), (2 < t0 ≤ 8)
Fillet weld thickness
a = t0
36 t0/t = 1
(b,d)/d0 = 1
16 t0/t ≥ 1
(b,d)/d0 = 0,6
50 t0/t ≥ 1
(b,d)/d0 = 0,6
14
6 t0/t = 1
(b,d)/b0 = 0,6
Welded-on hollow section girder, bearing transverse loading F in y-direction (b,d ≤ b0), (2 < t0 ≤ 8)
Fillet weld thickness
a = t0
32 t0/t = 1
(b,d)/b0 = 1
12,5 t0/t ≥ 1
(b,d)/b0 = 0,6
40 t0/t ≥ 1
(b,d)/b0 = 0,6
15 80 2 < t0 ≤ 8
Single butt strap at chamfered end of tube (d0/t0 < 25)
Pinched end of tube
a = 2 t0
16 80 2 < t0 ≤ 8
Welded double butt strap ((b0,d0)/t0 < 25)
Hot-bended strap, rounded slot milled at end of tube
Fillet weld thickness
a = t0
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
17 71 2 < t0 ≤ 8
Inserted dovetail strap ((b0,d0)/t0 < 25)
Fillet weld thickness
a = t0
18 56 2 < t0 ≤ 8
End face strap (d0/t0 < 25), (tP ≥ 2.5 t0)
Fillet weld thickness for the hollow section girder:
a = t0
for the strap:
a = 0,7✕tL
19 45 2 < t0 ≤ 8
End face strap (b0/t0 < 25), (tP ≥ 2,5 t0)
Fillet weld thickness for the hollow section girder:
a = t0
for the strap:
a = 0,7✕tL
20 45 2 < t0 ≤ 8
Inserted rectangular strap [(b0,d0)/t0 < 25]
Fillet weld thickness
a = t0
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
21
56 8 < t0 ≤ 25
Mitre joint with I- or V-weld without weld backing, stressed by bending (d0/t0 < 25), (ϕ ≥ 90°)
Requirements analogous to No. 1
50 2 < t0 ≤ 8
22
50 8 < t0 ≤ 25
Mitre joint with I- or V- weld without weld backing, stressed by bending (b0/t0 < 25), (ϕ ≥ 90°)
Mitre joint with transverse plate and fillet welds, stressed by bending (d0/t0 < 25), (ϕ ≥ 90°), (tP ≥ 2,5 t0)
Requirements analogous to No. 1
45 2 < t0 ≤ 8
23
50 Weld thickness a:
2 < a ≤ 8
Requirements analogous to No. 1
45 8 < a ≤ 14
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Table H.1 — Continued
No. ∆∆∆∆σσσσc N/mm2
Dimensions mm Constructional detail Requirements
24
45 Weld
thickness a:
2 < a ≤ 8
Mitre joint with transverse plate and fillet welds, stressed by bending (b0/t0 < 25), (ϕ ≥ 90°), (tP ≥ 2,5 t0)
Requirements analogous to No. 1
40 8 < a ≤ 14
25
45 Weld
thickness a:
2 < a ≤ 8
Joint of column and transverse girder with fillet welds, stressed by bending (b0/t0 < 25), (b0 ≤ b + 3 r)
Fillet weld thickness a = t0
where t0 is the existing
minimum plate thickness
40 8 < a ≤ 14
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Table H.2 — Values of inverse slope of ∆∆∆∆σσσσ –N-curve m and limit design stress range ∆∆∆∆σσσσc for lattice type connections of hollow section girders, m = 5
Basic symbols for all items
with gap (e ≥ 0)
with overlapping (e < 0)
Basic requirements for all items
Bending in individual members should be included in the calculated nominal stress
0,0 db ≤ 120 mm. For 0,0 db > 120 mm, the given values of cσ∆ should be multiplied by the factor
),/(1204a oo dbf =
0t ≤ 12,5 mm
Weld thickness a = min t
Incline of the diagonal members: °≤≤° 5035 iΘ
25/)( 00,0 <tdb ; 1)/()(6,0;1/ 0,0ii,i,0 ≤≤≥ dbdbtt
Eccentricity
in the plane of the lattice work: 25,0)/(5,0 0,0 ≤≤− dhe
perpendicular to the plane of the lattice work: ≤ 0,02 )( 0,0 db
Welding under shop conditions. For site welding the given values of cσ∆ should be multiplied by the factor 0,9.
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Table H.2 (continued)
No.
∆∆∆∆σσσσc (N/mm2) Intermediate values by straight-line interpolation!
Requirements
1
K-gussett with direct strut joint
a) with gap:
1/ i0 =tt 2/ i0 ≥tt
03,0 dg ≤
i3/2 dg ≤
6,0/ 0i =dd 36 80
1/ 0i =dd 45 90
1/3,0 ≤≤ pq 1/ i0 =tt 2/ i0 ≥tt
6,0/ 0i =dd 50 80
1/ 0i =dd 56 90
a. with overlapping
2
K-T-gusset with direct strut joint
1/ i0 =tt 2/ i0 ≥tt
1/3,0 ≤≤ pq
6,0/ 0i =dd 36 71
1/ 0i =dd 35 80
3
N-gusset with direct strut joint
b) with gap:
1/ i0 =tt 2/ i0 ≥tt
03,0 dg ≤
i3/2 dg ≤
6,0/ 0i =dd 18 56
1/ 0i =dd 25 63
1/3,0 ≤≤ pq 1/ i0 =tt 2/0 ≥itt
6,0/ 0i =dd 45 80
1/ 0i =dd 50 90
b. with overlapping
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Table H.2 (continued)
No. ∆∆∆∆σσσσc (N/mm2) Intermediate values by straight-line interpolation! Requirements
4
T- and X-gusset with direct strut joint
1/ i0 =tt 2/ i0 ≥tt °≤Θ≤° 9060
6,0/ 0i =dd 10 16
Bending of boom member should be considered!
1/ 0i =dd 36 50
5
K-gusset with direct strut joint
c) with gap:
with overlapping
03,0 bg ≤
i3/2 bg ≤
1/ i0 =tt 2/ i0 ≥tt
6,0/ 0i =bb 32 63
1/3,0 ≤≤ pq
1/ 0i =bb 36 71
6
K-T-gusset with direct strut joint
1/ i0 =tt 2/ i0 ≥tt
1/3,0 ≤≤ pq 6,0/ 0i =bb 32 56
1/ 0i =bb 36 63
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Table H.2 (continued)
No. ∆∆∆∆σσσσc (N/mm2) Intermediate values by straight-line interpolation! Requirements
7
N-gusset with direct strut joint
d) with gap:
03,0 bg ≤
ibg 3/2≤
1/ i0 =tt 2/ i0 ≥tt
6,0/ 0i =bb 29 50
1/3,0 ≤≤ pq
1/ 0i =bb 36 56
c. with overlapping
8
T- and X-gusset with direct strut joint
1/ i0 =tt 2/ i0 ≥tt °≤Θ≤° 9060
6,0/ 0i =bb 6 12,5
Bending of boom member should be considered!
1/ 0i =bb 32 40
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Annex I (informative)
Selection of a suitable set of crane standards for a given application
Is there a product standard in the following list that suits the application?
EN 13000 Cranes — Mobile cranes
EN 14439 Cranes — Tower cranes
EN 14985 Cranes — Slewing jib cranes
prEN 15011 Cranes — Bridge and gantry cranes
EN 13852-1 Cranes — Offshore cranes — Part 1: General purpose offshore cranes
EN 13852-2 Cranes — Offshore cranes — Part 2: Floating cranes
EN 14492-1 Cranes — Power driven winches and hoists — Part 1: Power driven winches
EN 14492-2 Cranes — Power driven winches and hoists — Part 2: Power driven hoists
EN 12999 Cranes — Loader cranes
EN 13157 Cranes — Safety — Hand powered lifting equipment
EN 13155 Cranes — Non-fixed load lifting attachments
EN 14238 Cranes — Manually controlled load manipulating devices
EN 15056 Cranes — Requirements for container handling spreaders
YES
NO
Use it directly, plus the standards that are referred to
Use the following:
EN 13001-1 Cranes — General design — Part 1: General principles and requirements
EN 13001-2 Cranes — General design — Part 2: Load actions
prEN 13001-3.1 Cranes — General design — Part 3.1: Limit states and proof of competence of steel structures
CEN/TS 13001-3.2 Cranes — General design — Part 3.2: Limit states and proof of competence of wire ropes
CEN/TS 13001-3.3 Cranes — General design — Part 3.3: Limit states and proof of competence of wheel / rail contacts
CEN/TS 13001-3.5 Cranes — General design — Part 3.5: Limit states and proof of competence of forged hooks
EN 13135-1 Cranes — Equipment — Part 1: Electrotechnical equipment
EN 13135-2 Cranes — Equipment — Part 2: Non-electrotechnical equipment
EN 13557 Cranes — Controls and control stations
EN 12077-2 Cranes safety — Requirements for health and safety — Part 2: Limiting and indicating devices
EN 13586 Cranes — Access
EN 14502-1 Cranes — Equipment for the lifting of persons — Part 1: Suspended baskets
EN 14502-2 Cranes — Equipment for the lifting of persons — Part 2: Moveable cabins
EN 12644-1 Cranes — Information for use and testing — Part 1: Instructions
EN 12644-2 Cranes — Information for use and testing — Part 1: Marking
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Annex ZA (informative)
Relationship between this European Standard and the Essential
Requirements of EU Directive 98/37/EC
This European Standard has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association to provide a means of conforming to Essential Requirements of the New Approach Directive Machinery 98/37/EC, amended by 98/79/EC.
Once this standard is cited in the Official Journal of the European Union under that Directive and has been implemented as a national standard in at least one Member State, compliance with the normative clauses of this standard confers, within the limits of the scope of this standard, a presumption of conformity with the relevant Essential Requirements of that Directive and associated EFTA regulations.
WARNING — Other requirements and other EU Directives may be applicable to the product(s) falling within the scope of this standard.
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Annex ZB (informative)
Relationship between this European Standard and the Essential
Requirements of EU Directive 2006/42/EC
This European Standard has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association to provide a means of conforming to Essential Requirements of the New Approach Directive Machinery 2006/42/EC.
Once this standard is cited in the Official Journal of the European Union under that Directive and has been implemented as a national standard in at least one Member State, compliance with the normative clauses of this standard confers, within the limits of the scope of this standard, a presumption of conformity with the relevant Essential Requirements of that Directive and associated EFTA regulations.
WARNING — Other requirements and other EU Directives may be applicable to the product(s) falling within the scope of this standard.
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Bibliography
Selection of literature that contains information about Hot Spot Stress Method:
[1] EN 1993-1-1:2005, Eurocode 3: Design of steel structures — Part 1-1: General rules and rules for buildings
[2] prEN 1993-1-9: Eurocode 3: Design of steel structures — Part 1-9: Fatigue strength of steel structures
[3] EN 22553:1994, Welded, brazed and soldered joints — Symbolic representation on drawings (ISO 2553:1992)
[4] EN ISO 4042:1999, Fasteners — Electroplated coatings (ISO 4042:1999)
[5] EN ISO 17659:2004 Welding - Multilingual terms for welded joints with illustrations (ISO 17659:2002); Trilingual version
[6] EN ISO 15330:1999, Fasteners — Preloading test for the detection of hydrogen embrittlement — Parallel bearing surface method (ISO 15330:1999)
[7] ISO 9587:2007, Metallic and other inorganic coatings — Pre-treatment of iron or steel to reduce the risk of hydrogen embrittlement
[8] IIW International Institute of Welding. Subcommission XV-E-92-244: Recommended Fatigue Design Procedure for Welded Hollow Section Joints, 2nd edition, June 1999
[9] IIW – XV-E: Recommended Fatigue Design Procedure for Welded Hollow Section Joints
Part 1: Recommendations. 1999; Document XIII-1804-99
Part 2: Commentary, 1999, Document XV-1035-99
[10] I. HUTHER, H-P. LIEURADE, L. VELLUET, Contraintes admissibles dans les assemblages soudés, 1A4085/1A4087, rapport CETIM, avril 2000
[11] E. Niemi, W. Fricke, S.J. Maddox, Fatigue analysis if welded components; Designer's guide to the structural hot-spot stress approach, September 2006
[12] American Petroleum Institute – API RP 2A-WSD: Recommended practice for planning, designing and constructing fixed offshore platforms – Working Stress Design, December 1,2000
[13] Romeijn, A., Stress and strain concentration factors of welded multiplanar tubular joints, Delft University Press, Delft, 1994, ISBN 90-407-1057-0
Selection of literature that contains information about hollow sections:
[14] Zhao, X-L., Herion, S. Packer, J. A., Puthli, R. S., Sedlacek, G. Wardenier, J. Weymand, K., Wingerde, A. M., van, and Yeomans, N. F.: Design Guide for circular and rectangular hollow section welded joints under fatigue loading, CIDECT and Verlag TÜV Rheinland, Cologne, 2000, ISBN 3-8249-0565-5
[15] Wardenier, J., Dutta, D., Yeomans, N., Packer, J. A., and Bucak, O.: Design Guide for structural hollow sections in mechanical applications, CIDECT and Verlag TÜV Rheinland, Cologne, 1995, ISBN 3-8249-0302-4
[16] Zirn, R.: Schwingfestigkeitsverhalten geschweißter Rohrknotenpunkte und Rohrlaschenverbindungen, Techni. Wiss. Bericht MPA Stuttgart, 1975, Heft 75-01
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Selection of literature that contains information about elastic stability:
[17] DIN 18800-2, Stahlbauten — Stabilitätsfälle — Knicken von Stäben und Stabwerken
[18] “Eurocode 3 – Design of steel structures”, Part 1.5 : general rules : supplementary rules for planar plated structures without transverse loading (EN 1993-1-5:2007)
[19] Klöppel, K. and Scheer, J., “Beulwerte ausgesteifter Rechteckplatten“, W. Ernst und Sohn
[20] Klöppel, K. and Möller, K., “Beulwerte ausgesteifter Rechteckplatten, Band II“, W. Ernst und Sohn
[21] Protte, W. : Zum Scheiben und Beulproblem lângsversteifter Stegblechfelder bei örtlicher Lasteinleitung und bei Belastung aus Haupttragwirkung.Stahlbau 45 (1976), pages 251-252
