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है”ह”ह

IS 15666-1 (2006): Gas turbines - Procurements, Part 1:General Introduction and definitions [ETD 15: RotatingMachinery]

IS 15666 (Part 1): 20061s0 3977-1:1997

indian Standard

GAS TURBINES — PROCUREMENTPART 1 GENERAL INTRODUCTION AND DEFINITIONS

IC!3 27.040

0 BIS 2006

BUREAU OF INDIAN STANDARDSMANAK BHAVAN, 9 BAHADUR SHAH ZAFAR MARG

NEW DELHI 110002

A@/ 2006 Price Group 6

Rotating Machinery Sectional Committee, ET 15

NATIONAL FOREWORD

This Indian-Standard (Part 1) which is identical with ISO 3977-1:1997 ‘Gas turbines — Procurement —Part 1 : General introduction and definitions’ issued by the International Organization for Standardization(ISO) was adopted by the Bureau of Indian Standards on the recommendation of the Rotating MachinerySectional Committee and approval of the Electrotechnical Division Council.

The text of the ISO Standard has been approved as suitable for publication as an Indian Standardwithout deviations. Certain conventions are, however, not identical to those used in Indian Standards.Attention is particularly drawn to the following:

a) Wherever the words ‘International Standard’ appear referring to this standard, they should beread as ‘Indian Standard’.

b) Comma ( , ) has been used as a decimal marker while in Indian Standards, the current practiceis to use a point ( . ) as the decimal marker.

For the purpose of deciding whether a particular requirement of this standard is complied with, thefinal value, observed or calculated expressing the result of a test or analysis, shall be rounded off .inaccordance with IS 2:1960 ‘Rules for roundin off numerical values (revLsec$’.The number of significant

%places retained in the rounded off value sho d be the same as that of the specified value in thisstandard.

IS 15666 (Part 1): 20061s0 3977-1:1997

Indian Standard

GAS TURBINES — PROCUREMENTPART 1 GENERAL INTRODUCTION AND DEFINITIONS

1 Scope

This part of ISO 3977 groups together the terms and definitionsprocurement of gas tutilne systems, -and defines additional terms.

2 Definitions

given in ISO 11086 that are relevant to the

For the purposes of all parts of ISO 3977, the following definitions apply.

2.1gas turbineMachine which converts thermal energy into mechanical worlc it consists of one or several rotating compressors, athermal device(s) which heats the working fluid, one or several turbines, a control system and essential auxiliaryequipment. Any heat exchangers (excluding waste exhaust heat recovery exchangers) in the main working fluidcircuit are considered to be part of the gas turbine.

NOTE — Examples of gas turbinesystems are shown in figures 1 to 9..,, ,

2.2gas turbine power plantGas turbine engine and all essential equipment necessary for the production of power in a useful form (e.g.electrical, mechanical or thermal). [ISO 11086]

2.3open cycleThermodynamic cycle in w+ich the workhg fluid enters the gas turbine from the atmosphere and is discharged intothe atmosphere. [ISO 11086]

2.4closed cycleThermodynamic cycle having a recirculating worfdng fluid independent of the atmosphere. [ISO 11086]

2.5semiclosed cycleThermodynamic cycle utilizing combustion in a working fluid that is partially recirculated and partialty exchangedwith atmospheric air. [}S0 11086]

2.6simple cycleThermodynamic cycle consisting only of successive compression, combustion and expansion. [ISO 11086]

2.7regenerative cycleThermodynamic cycle employing exhaust heat recovery, consisting of successive compression, regenerativeheating, combustion, expansion and regenerative cooling (heat transfer from the exhaust to the compressordischarge fluid) of the working fluid. [ISO 11086]

IS 15666 (Part 1) :20061s03977-1 :1997

2.8intercooled cycleThermodynamic cycle employing cooling of the working fluid between stages of successive compression.[1s011086]

,2.9reheat cycleThermodynamic cycle employing the addition of thermal energy to the working fluid between stages of expansion.

2.10combined cycleThermodynamic cycle employing the combination of a gas turbine cycle with a steam or other fluid Rankine cycle.

NOTES

1 in-a commonexample, the gas turbineexhaust heat is used to generate steam for the Rankine cycle.

2 The superiorthermal performance of this cycle is due to a combinationof the best thermodynamicattributesof each cycle,namely the addition of thermal energy at higher temperatures in the gas turbhe cycle and the rejection of thermal energy atlowertemperatures in the Rankine cycle.

[1s0 1-1086]

2.11single-shaft gas turbineGas turbine in which the compressor and turbine rotors are mechanically coupled and the power output is takeneither directly or through gearing.

2.12multi-shaft gas turbineGas turtrine combination including at least two turbines working on independent shafts.

NOTE — The term includescases referredto as compoundand split-shaftgas turbines.,,, ,

2.13bled gas turbineGas turbine which has, for external use, extraction of compressed air between compressor stages and/or at thedischarge of the compressor, or extraction of hot gas at the inlet of the turbhe and/or between turbine stages.

2.14gas generatorAssembly of gas turbine components that produces heated pressurized gas to a process or to a power turbine.

NOTE — It consistsof one or more rotatingcompressor(s),thermal device(s) associated with the working fluid, and one ormore compressor-drivingtuhine(s), a controlsystem and-essentialauxiliaryequipment.

[1s01 1086]

2.15compressorThat component of a gas turbine which increases the pressure of the working fluid.

2.16turbineTerm which when used alone refera to the turbine action only. It is that component of the gas turbine whichproduces power from expansion of the working fluid.

2.17power turbineTurbine having a separate shaft from which output is derived.

2.18combustion chamber (primary or reheat)Heat source in which the fuel reacts to increase directly the temperature of the working fluid.

2

IS 15666 (Part 1) :20061s0 3977-1:1997

2.19working fluid (gas or air) heaterHeat source in which the temperature of the workhg fluid is increased indirectly.

2.20> regenerator/recuperator

Different types of heat-exchanger, transferring heat from the exhaust gas to the working fluid before it enters the

combustion chamber.

2.21precoolerHeat-exchanger or evaporative cooler which reduces the temperature of the working fluid prior to its initialcompression. [ISO 11086]

2.22intercoolerHeat-exchanger or evaporative cooler (spray intercooler) that reduces the temperature of the worldng fluid between

stages of compression. [1S0 11086]

2;23overspeed tripControl or trip element which immediately activates the overspeed protection system when the rotor speed reachesa preset value. [ISO 11086]

2.24control systemGeneral system used to control, protect, monitor and report the condition of the gas turbhe in all of its modes of

operation.

NOTE — This includes starting control systems, governor and fuel control systems, speed indicator(s), gauges,,electdcalsupply controlsand other controls nscessaty for the orderly stattup, stable operation, shutdown,trippingand/or shutdownforabnormalconditionsand standby operation.

[1s01 1086]

2.25governing systemControl elements and devices for the control of critical parameters such as speed, temperature, pressure, poweroutput, etc.

2.26fuel governor valveValve or any other device operating as a final fuel-metering element controlling the fuel input to the gas turbine.

NOTE — Other means of controllingthe fuel flow to the turbhe are possible.

2.27fuel stop valveDevice which, when actuated, shuts off all fuel flow to the combustion system.

2.28dead bandTotal range through which an input can be varied with no resulting measurable corrective action of the fuel flow

controller. In the case of speed, dead band is expressed in percent of rated speed.

2.29governor droopSteady-state speed changes produced by the change of output from zero to the rated output, expressed as a

percentage of the rated speed.

3

IS 15666 (Part 1) :20061s03977-1 :1997

2.30overtempersture detectorPrimary sensing element that is directly responsive to temperature and wh~h imrnedatefy activates, through

suitable amplifiers or mnvertefs, the overtemperature protection system when the temperature reaches a presetvalue. [ISO 11066]

2.31fuel specific energy (cslorific value)Gross specific energy is the total heat released per unit mass of fuel burned, expressed in kilojoules per kilogram.The net specif~ energy is the gross specific energy less the heat absorbed by the vaporized water formed during

mmbustion. It is expressed in kilojoules per kilogram.

2.32heat rateRatio of the net fuel energy supplied per unit time to the net power produced in kilojoules per kilowatt hour

[kJ/(kW.h)]. [ISO 11086]

NOTE — The rate is based on the net specifii energy of the fuel including the sensible heat above 15 “C (sss atsoISO 23141989, 8.2.3).

2.33specific fuef consumptionRatio of the mass flow of fuel to the net power output in kilograms per kilowatt hour [kg/(kW.h)] of the specified fuel.

[1s011088]

2.34thermal effkiencyRatio of the net power output to the heat consumption based on the net specifii energy of the fuel.

NOTE — See also ISO 23141969,8.2.2 and 8.3.3 e).

2.35reference turbine inlet temperatureMean temperature of the working fluid immediately upstream of the fimt stage stator vanes.

NOTE — For methodof determination,see ISO 23141989,8.6.

2.36self-sustaining speedMinimum speed at which the gas turbine operates, without using the power of the starting device, under the most

unfavorable ambient conditions.

2.37idling speedSpeed designated by the manufacturer at which the turbine will run in a stable condition and from which loading or

shutdown may take place.

2.38maximum continuous speedUpper limit of the continuous operating speed of the gas turbine output shaft.

2.39rated speedSpeed of the gas turbine output shaft at which the rated power is developed.

2.40turbine trip speedSpeed at which the independent emergency overspeed device operates to shut off fuel to the gas tudine.[1s011086]

4

IS 15666 (Part 1): 20061s0 3977-1:1997

2.41steam anchorwater injectionSteam and/or water injected into the woddng fluid to increase the power output and/or to reduce the content ofoxides of nitrogen (NO=) in the exhaust.

.2.42mass-tqower ratio (mobileapplications)Ratio of the total dfy mass of the gas turbine elements (in accordance with 2.1) to the power of the gas turbine,

expressed in kilograms per kilowatt.

NOTE — Sse also ISO 397?-2.

2.43compressor surgeAn unstable condfiion characterized by low-frequency fluctuations in mass flow of the working fluid in the

compressor and in the connecting ducts.

1 3

Key

1 Compressor2 Combustion chamber3 Turbine4 Load

4

,,, ,

Figure 1 — Simple cycle, singleshaft gas turbine

IS 15666 (Part 1): 20061s03977-1 :1997

1 2

1, \

?

3 4 5Key

1

23

Regenerator or recuperator 4 TurbineCombustion chamber 5 LoadCompressor

Figure 2 — Regenerative cycle, single-shaft gas turbine,,, ,

11

Fi —I

II III IL --- ------ 4F--- ------ 4I1 I1

2 3 4 5-Key

1 Combustion chamber 4 Power turbine2 Compressor 5 Load3 Compressor turbine

NOTE — Alternativetwin-spoolarrangement is shown in dotted lines.

Figure 3 — Simple cycle, split-shaft gas turbine, i.e. with separate power turbine

6

IS 16666 (Part 1) :20061s0 3977-1:1997

4

Key

2 1 3

I

7 8’ 9

1

23456789

Combustion chamberH.P. compressorH.P. turbineIntercoolerCmlantReheat combustion chamberL.P. compressorL.P. tutt)ineLoad

Figure 4 — Intercoaled and reheat cycle (compound type), multi-shaft gas tutiinewith load coupled to low-pressure shaft

.,, ,

7

IS 15666 (Part 1): 20061s03977-1:1997

1 2 3A I

4 s 6

Key

1 Air bleed2 Combustion chamber3 Hot gas bleed4 Compressor5 Turbine6 Load

Figure 5 — Single-shaft gas turbine with air bleed and hot gas bleed

0

IS 15666 (Part 1) :20061s03977-1:1997

12 3/ \

1{

7“7’‘9 6 7 8

Key.,, ,

1 Coolant2 Precooler3 Working fluid heaters4 Heat source5 L.P. compressor6 H.P. compressor7 Turbine8 Load9 Intercmler

Figure 6 — Singieshaft ciosed-cycie gas turbine

Is 15666 (Part 1): 20061s03977-1 :1997

6 2 3 4 7 51

\ \ I \

I

I

1- 0 I 9-i

Key

1234567a9

Waste heat recovery tillerSteam turbineLoadCompressorTurbkeCondenserCombustion chamberSteam turbine sectionGas turbine section

Figure 7 — Single-shaft type, combined cycle

IS 15666 (Part 1): 20061s03977-1:1997

2 35 4 1

\

2 35 4

1-8

Key

Ib

I I

—

1

I

62

Y ,,,,7

9

1

23456789

Waste heat recovery boilerLoadCompressorTurbineCombustion chamberSteam turbineCondenserGas turbhe sectionSteam turbine section

Figure 8 — Multi-shaft type, combined cycle (Configuration with two gasturbines and one steam turbine)

11

IS 15666 (Part 1): 20061s0 3977-1:1997

2 3 4 1

“11P-I

5

Key

1 Waste heat recovety boiler2 Load

3 Compressor4 Turbine5 PFB combustor6 Steam turbine7 Condenser

I

I

62

.,, ,

Figure 9 — Combinetiycle gas turbine with pressurized fluidized bed (PFB) combustor

12

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Amendments Issued Since Publication

Amend No. Date of Issue Text Affected

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