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Presented by Ali Rafiee
Demo Version of Gas Turbine TrainingPower PlantPower Plant
1
Evolution of the Gas Turbine
As early as 1791, John Barber’s patent for the steam turbine described other fluidst ti lor gases as potential energy sources.
In 1808 John Dumball envisioned a multi-stage turbine. Unfortunately his ideaconsisted only of moving blades without stationary airfoils to turn the flow into eachconsisted only of moving blades without stationary airfoils to turn the flow into eachsucceeding stage.
Not until 1872 did Dr. Franz Stolze combine the ideas of Barber and Dumball toNot until 1872 did Dr. Franz Stolze combine the ideas of Barber and Dumball todevelop the first axial compressor driven by an axial turbine.1 Due to a lack offunds, he did not build his machine until 1900.
In 1905, the first gas turbine and compressorunit built by Brown Boveri was installed (20 kilowatt).
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Oil And Gas Turbomachinery Applications
Turbomachinery ApplicationsApplications
Upstream Midstream Downstream
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Efficiency of Fossil-fired Power Plants
N t Effi i [%]
50
60Net Efficiency [%]
Combined cycleCombined cycle
40Diesel EnginesDiesel Engines
Combined cyclegas and steamturbines
Combined cyclegas and steamturbines
20
30
Coal‐firedSteam Power Plants
Coal‐firedSteam Power Plants
Heavy industrial natural gas‐fired turbine, simplecycle
Heavy industrial natural gas‐fired turbine, simplecycleBiomass firedBiomass fired
0
10
cyclecycleBiomass‐firedSteamPower PlantsBiomass‐firedSteamPower Plants
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1 2 200 1000 200010 20 100Maximum single unit output [MW]
4
Aero-Derivative and Heavy Industrial
In spite of their common background, there are variations between the aero‐derivative and heavy industrial gas turbines
The most obvious difference is in the physical size of the heavy industrial compared to the aero‐derivative gas turbines
and heavy industrial gas turbines.
Ob i I d i l C d T A D i i
the aero derivative gas turbines.
Observation Industrial Compared To Aero‐Derivative
Shaft speed slower
Air flow higher
Maintenance time longer
Maintenance lay‐down space larger
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Air Inlet System
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Consequences of Poor Inlet Filtration
Foreign Object Damage Erosion Fouling Cooling Passage Plugging
Foreign Object Damage
Particle Fusion Corrosion
Erosion
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STG600 Air intake system
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Air Inlet System
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Air Inlet System : (Evaporative Cooler)
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SGT600 Compressor Casing
The compressor casing, covering the whole compressor section, is horizontally split to facilitate maintenance.
The casing contains the three stator subassemblies front, central and rear stator casings.
These casings carry the guide vanes and the stator irings.
The stator casings form slots for bleeding air downstream the second (LP bleed) and the fifth stage (HP bleed)stage (HP bleed).
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Velocity Triangle for one Stage
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CCompressor
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Compressor curves
Design Point
Surge Line
atio
Efficiency Lines
Choke Line
Pressur
e Ra
Choke Line
Mass flow
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SGT600 compressor
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Compressor Water Washing System
REDUCTION OF OUTPUT AND EFFICIENCY
THROUGH COMPRESSOR SOILING AND AGING
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SGT-600 BV and IGV function
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Combustion Chambers Type
Can or Tubular
Burner Type Annular
Can‐annular
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SGT600 Combustion Chamber
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Combustion ChamberCombustion Chamber
Model V94.2Two vertical silo ‐ typecombustion chamberseach with 8 burners
Model V94.3Two horizontally opposed combustionchambers each with 8 burners
2.20 m
Flamecylinder
3.80 m
Model V94.3A Hybrid‐Burner‐Ring (HBR) Combustion ChamberOne annular combustor with 24 burners
2.20 m
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3.50 m
20
Combustion ChamberCombustion Chamber
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Axial Turbine Velocity Triangle
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Turbine
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Turbine
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Exhaust
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Turbocompressor Components And Layout
Main Equipmentq p
Inside the Package
Outside the Package
• Fuel system and spark igniter• Natural gas (control valves)• Liquid (pumps, valves)
• Bearing lube oil system
• Enclosure and fire protection system• Inlet system
• Air-filter (self-cleaning, barrier, inertial, demister, screen)
• Tank (overhead, integral)• Filter (simple, duplex)• Pumps (main, pre/post, backup)
• Accessory gear• Fire/gas detection system
• Silencer•Exhaust system
• Silencer• Stack• Fire/gas detection system
• Starter/helper drive• Pneumatic, hydraulic, variable speed alternating current (AC) motor
• Controls and instrumentation (on-skid, off-skid)
• Lube oil cooler (water, air)• Fuel filter/control valve skid• Motor control center• Switchgear, neutral ground resistor
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Controls and instrumentation (on skid, off skid)• Seal gas/oil system (compressors) • Inlet fogger/cooler
Lubrication System
Primary Purposes of a Lubrication System :
Reduces Friction Cushions Cools Cleans Seals
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Thrust Bearing Position Monitoring
Thi i lifi d d i h dd t This simplified drawing shows an eddy‐current transducer mounted to one of the thrust pads and observing the thrust collar, so that it can measure the thickness of the lubricating oil film between ththem.
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Thrust Bearing Collar
30 microns
120 ‐200
This diagram shows the mutual positioning of thrust bearing pads relative to the
This plot shows variations in measured oil film thickness across the surface of a thrust of thrust bearing pads relative to the
supported thrust collar. Note: The angle of the thrust pads is highly exaggerated for clarity.
film thickness across the surface of a thrust bearing pad in a running machine. Darker shading represents largest film thickness, while lighter shading represents smallest thickness
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thickness.
Labyrinth Seal
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Fuel gas Supply
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SGT600 Ignition gas system
Shut off valve
Control valve (needle type)OrificeSafety valve
Shut off valve(Burner 6)
Shut‐off valve (Spring closing type)
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Pressure reducing valve Bypass valve Three‐way shut‐off valve
System Operating :Start-Up Sequence
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SGT600 Starter motor system
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Gas Turbine Control Modes:
In part load we have 3 different control mode:
air fuelIGV = constant M = constant M = variable
air fuel
air fuelTET = constant M = variable M = vari
TIT = constant M = variable M = variab
able
le
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Gas Turbine Control Modes: Sample
IGV fix TET fix TIT fix
600
650
)
500
550
mas
s flo
w(k
g/se
c)
400
450
Com
pres
sor a
ir m
300
350
0 5 0 55 0 6 0 65 0 7 0 75 0 8 0 85 0 9 0 95 1
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0.5 0.55 0.6 0.65 0.7 0.75 0.8 0.85 0.9 0.95 1
GT load/full load
36
SGT-600 Industrial Gas Turbine
Efficiency Vs. Inlet Filter Pressure Loss34 0
Inlet Filter Pressure Loss
Efficiency
33.8
34.0
=33.6
c ef
f [%
]
1 mbar 0.025 % 33.4
lant
gro
ss e
lec
33 0
33.2
Pl
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0 10 20 30 4033.0
Inlet filter pressure loss [millibar]
37
What is API?
American Petroleum Institute (API):US P l I d P i T d A i i US Petroleum Industry Primary Trade Association
400 Member Companies Covers all Aspects of Oil & Gas Industry Accredited by ANSI (American National Standards Organization) Accredited by ANSI (American National Standards Organization) Started Developing Standards in 1924 Maintains about 500 Standards
API Specifications Typically LagPhilosophy:
Improve Safety Improve Environmental Performance
API Specifications Typically LagTechnology Developments!
Reduce Engineering Costs Improve Equipment Interchangeability Improve Product Quality Lower Equipment Cost
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Lower Equipment Cost Allows for Exceptions for Reason
38
API 616 code
1. Scope (and alternative designs)2. References (more or less everything is referenced)( y g )3. Definitions
ISO rating, normal operating point, maximum continuous speed, trip speed, etc. Note: Some basic requirements are hidden here (e.g. MCS)
4. Basic Design P ti t d i b i / l b l i i t t i l l b i ti Pressure ratings, rotordynamics, bearings/ seals, balancing requirements, materials, lubrication
Covers quality and mechanical integrity issues Primarily core engine
5. Accessories Starters, inlet/ exhaust, mounting, fuel, gears, enclosures, fire protection, tools, , g, , g , , p , Mostly on-skid package items
6. Inspection, Testing, and Preparation for Shipment Required and optional tests: hydrostatic, mechanical run, package, PTC 22 Long term and short term shipping
Mi i l t t i t Minimal test requirements 7. Vendor Data
Drawings, performance data, calculations, quality documentation References, Appendix B list.
8. Appendix
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pp A. Data sheets B. Vendor drawing and data requirements C. Procedure to determine residual unbalance
(balancing) D. Lateral and torsional logic diagrams E. Gas turbine nomenclature
39
API 616 code : Basic Design
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API 616 code
4.8—Bearings: applies to all gas turbine bearings. 4 8 1 1—Hydrodynamic radial and thrust bearings are preferred These should be thrust-4.8.1.1 Hydrodynamic radial and thrust bearings are preferred. These should be thrust
tilt pad, radial-tilt pad, or sleeve bearings. 4.8.2.5—If rolling element bearings are used they must meet 50,000 hours of continuous
operation. Few industrial gas turbines utilize rolling element bearings and aeroderivativeengines are not applicable to API 616 (1998).
4.8.3.3—The bearing shells shall be horizontally split. Many original equipment manufacturers (OEMs) take exception to this requirement.
4.8.4.2—Hydrodynamic thrust bearings shall be selected at no more than 50 percent of the ultimate load rating at site power. This requirement should not be taken exception to.4 8 5 2 B i h i R l bl l b i h b ff l i d L l 4.8.5.2—Bearing housings: Replaceable labyrinth type buffer seal required. Lip-seals are not acceptable—this cannot be met by some manufacturers.
Replaceable labyrinth
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Lip‐seals
API Datasheet
Forms technical basis of proposal
Define Customer Site, Operating, and Equipment Minimum Requirements
Most important technical contractual document
Must always be filled out:
•API 616 Appendix A & B (Gas Turbine)API 614 A di D (L b Oil S )•API 614 Appendix D (Lube Oil System)
•API 670 Appendix A (Machinery Protection)
When filling out the API Data Sheets :
• Read all the notes: Some critical requirements are often hidden here.
• Fill out as much info as is available: Even partially
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Fill out as much info as is available: Even partially filled out sheet is better than no sheet.
API Datasheet
By Purchaser
By ManufacturerBy Manufacturer
By ManufacturerBy Manufacturerif not by Purchaser
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Note: API 616 does not apply to Aero-Derivative Gas Turbines – Only Industrial!
Technical Bid Evaluation Guidelines
3. Decide the best type Aero derivative or Heavy Duty:H D / I d i l T H C i M i iff h f i i h j l b i1. Heavy Duty / Industrial Type: Heavy Casing, Massive stiff shafting with journal bearing, requires pre-post lube, cheap but excessive lube, less frequent maintenance.
2. Aero derivative: Light Casing, Rotor shafting is 2 or more shaft, Each with its own bearing, Expensive but less lube (aero type), Higher efficiency but very rapid decrease after washing, Quick overhaul
4. Evaluate Efficiency, performance and loss update process calculation:1 Effi i 30% 70% f t ti l d d i i d t d i i1. Efficiency 30% means 70% of rotational energy produced is required to drive air
compressor in order to maintain sufficient air flow for combustion.2. Evaluate Performance and Loss3. Fuel Type: In the case of Dual fuel that is liquid hotter and less efficiency than gas, yp q y g
Engine efficiency liquid 1.3% lower.4. Heat Rate: amount of heat energy to produce output5. Inlet Loss: P drops through inlet filters6 E h t L P d th h t k il WHR (b th t thi ill t
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6. Exhaust Loss: P drops through stack, silencer, WHR (be aware that this will create backpressure)
44
Factory Performance Tests
Full speed, full load test for four hours Typically against a water break or generator/load cells Determines maximum output power, specific fuel consumption, and efficiency
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Start-Up or Shutdown Control Loops
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Start up sequence
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Protective System
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VIBRATION
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Protective Systems
Most gas turbines are protected against the following:
Low lube oil pressure High vibrationg Turbine overspeed High lube oil temperature Exhaust temperature Exhaust temperature Blade path temperature High acceleration. High thrust pad temperature Low or high gas turbine inlet vacuum High turbine exhaust pressure
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g p
50
Failure Diagnostics
Combustor Analysis
The measured parameters in the combustors are pressure of the fuel and evenness of combustion noise. The inlet temperature to the turbine is not normally measured due to the very high temperatures in the combustors.
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Table above shows how some problems affect the various parameters of the compressor.
51
Calculation of Equivalent Operating Hours
tequ = a1 x n1 + a2 x n2 + ti + f x w x (b1 x t1 + b2 x t2)n
i=1
f = Fuel weighting factor w = Weighting factor for water/steam
injectiont1 = Operating hours at power settings up to
base loadb1 = 1 (weighting factor for base‐load duty)t2 = Operating hours for power settings
above base load (peak load)b2 = 4 (weighting factor for peak‐load duty)
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SGT-600 Maintenance Plan
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Loading/Unloading Capability of V94.2
1 Fuel stop valve opens2 Frequency converter off
3 Excitation on4 Synchronization
Speed120
PGT (ISO)
4 MW/minSpeedRPM
3000
80
100
% Peak loadBase load
4
30 MW/min
11 MW/min
4 MW/min
2000
100040
60
Normal loading
11 MW/min
1
1000
00 1 2 3 4 0 2 4 6 8 10 12 14 0 2 4 6 8 10 12 14 16
0
20
20 MW
g
and unloading
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0 1 2 3 4 0 2 4 6 8 10 12 14 0 2 4 6 8 10 12 14 16min.unloading Time
min.loading Time
min.Start‐up Time
54
Electricity Generation Costs, Without Emission Trading
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