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GE Gas Turbine Performance Characteristics - NCAD

GE Power SystemsGE Gas TurbinePerformanceCharacteristicsFrank J. BrooksGE Power SystemsSchenectady, NYGER-3567 HContentsIntroduction.. 1 Thermodynamic Principles.. 2 The Brayton Cycle.. 3 Thermodynamic Analysis.. 6 Combined Cycle.. 7 Factors Affecting Gas Turbine Performance .. 8 Air Temperature and Site Elevation .. 8 Humidity .. 8 Inlet and Exhaust Losses .. 9 Fuels.. 10 Fuel Heating .. 11 Diluent Injection .. 12 Air Extraction .. 12 Performance Enhancements .. 12 Inlet Cooling .. 13 Steam and Water Injection for Power Augmentation .. 14 Peak Rating .. 14 Performance Degradation.. 14 Verifying Gas Turbine Performance .. 15 Summary.. 15 List of Figures .. 16 List of Tables .. 16GE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)iGE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)iiIntroductionGE offers both heavy-duty and aircraft-derivativegas turbines for power generation and industri-al applications.

GE Power Systems GE Gas Turbine Performance Characteristics Frank J. Brooks GE Power Systems Schenectady, NY GER-3567H

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Transcription of GE Gas Turbine Performance Characteristics - NCAD

1 GE Power SystemsGE Gas TurbinePerformanceCharacteristicsFrank J. BrooksGE Power SystemsSchenectady, NYGER-3567 HContentsIntroduction.. 1 Thermodynamic Principles.. 2 The Brayton Cycle.. 3 Thermodynamic Analysis.. 6 Combined Cycle.. 7 Factors Affecting Gas Turbine Performance .. 8 Air Temperature and Site Elevation .. 8 Humidity .. 8 Inlet and Exhaust Losses .. 9 Fuels.. 10 Fuel Heating .. 11 Diluent Injection .. 12 Air Extraction .. 12 Performance Enhancements .. 12 Inlet Cooling .. 13 Steam and Water Injection for Power Augmentation .. 14 Peak Rating .. 14 Performance Degradation.. 14 Verifying Gas Turbine Performance .. 15 Summary.. 15 List of Figures .. 16 List of Tables .. 16GE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)iGE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)iiIntroductionGE offers both heavy-duty and aircraft-derivativegas turbines for power generation and industri-al applications.

2 The heavy-duty product line con-sists of five different model series: MS3002,MS5000, MS6001, MS7001 and MS5000 is designed in both single- andtwo-shaft configurations for both generatorand mechanical-drive applications. TheMS5000 and MS6001 are gear-driven units thatcan be applied in 50 Hz and 60 Hz markets. All units larger than the Frame 6 are direct-drive units. The MS7000 series units that areused for 60 Hz applications have rotationalspeeds of 3600 rpm. The MS9000 series unitsused for 50 Hz applications have a rotationalspeed of 3000 rpm. In generator-drive applica-tions the product line covers a range fromapproximately 35,800 hp to 345,600 hp (26,000kW to 255,600 kW).Table 1provides a complete listing of the avail-able outputs and heat rates of the GE heavy-dutygas turbines. Table 2lists the ratings of mechani-cal-drive units, which range from 14,520 hp to108,990 hp (10,828 kW to 80,685 kW).

3 The complete model number designation foreach heavy-duty product line machine is pro-vided in both Tables 1 and 2. An explanation ofthe model number is given in Figure paper reviews some of the basic thermo-dynamic principles of gas Turbine operationand explains some of the factors that affect Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)1 Table gas Turbine Performance Characteristics - Generator drive gas Turbine ratingsGE Generator Drive Product LineModelFuelISO BaseHeatHeatExhaustExhaustExhaustExhaust PressureRatingRateRateFlowFlowTempTempRa tio(kW)(Btu/kWh)(kJ/kWh)(lb/hr)(kg/hr)(d egrees F)(degrees C)x10-3x10-3PG5371 (PA)Gas26, , , , , , (B)Gas42, , , , , , (FA)Gas69, , , , , , (EA)Gas84, , , , , , (FA)Gas171, , , , , , (FB)Gas184, , , , , , (E)Gas122, , , , , , (EC)Gas169, , , , , , (FA)Gas255, , , , , , PrinciplesA schematic diagram for a simple-cycle, single-shaft gas Turbine is shown in Figure 2.

4 Air entersthe axial flow compressor at point 1 at ambientconditions. Since these conditions vary fromday to day and from location to location, it isconvenient to consider some standard condi-tions for comparative purposes. The standardconditions used by the gas Turbine industry are59 F/15 C, bar and 60% relativehumidity, which are established by theInternational Standards Organization (ISO)and frequently referred to as ISO entering the compressor at point 1 is com-pressed to some higher pressure. No heat isadded; however, compression raises the airtemperature so that the air at the discharge ofthe compressor is at a higher temperature leaving the compressor, air enters thecombustion system at point 2, where fuel isinjected and combustion occurs. The combus-tion process occurs at essentially constant pres-sure.

5 Although high local temperatures arereached within the primary combustion zone(approaching stoichiometric conditions), theGE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)2 Mechanical Drive Gas Turbine RatingsModelYearISO RatingISO RatingHeatHeatMassMassExhaustExhaustCont inuousContinuousRateRateFlowFlowTempTemp (kW)(hp)(Btu/shp-hr)(kJ/kWh)(lb/sec)(kg/ sec)(degrees F)(degrees C)M3142 (J)195211,29015,1409,50013,440117531,008 542M3142R (J)195210,83014,5207,39010,4501175369837 0M5261 (RA)195819,69026,4009,38013,270205929885 31M5322R (B)197223,87032,0007,07010,0002531146663 52M5352 (B)197226,11035,0008,83012,4902731239154 91M5352R (C)198726,55035,6006,9909,89026712169336 7M5382 (C)198728,34038,0008,70012,3102781269605 15M6581 (B)197838,29051,3407,82011,0602951341,01 3545 Table gas Turbine Performance Characteristics - Mechanical drive gas Turbine ratingsMS7000(EA)12 PGModelNumberofShaftsPowerSeriesApplicat ionApproxOutputPower inHundreds,Thousands, or10 Thousandsof HorsepowerR - RegenBlank - SC1 or 2 Frame3,5,76,9 MechDrivePkgdGenM -PG -17 Figure gas Turbine model designationGT25385 AGT23054 Acombustion system is designed to provide mix-ing, burning, dilution and cooling.

6 Thus, by thetime the combustion mixture leaves the com-bustion system and enters the Turbine at point3, it is at a mixed average temperature. In the Turbine section of the gas Turbine , theenergy of the hot gases is converted into conversion actually takes place in twosteps. In the nozzle section of the Turbine , thehot gases are expanded and a portion of thethermal energy is converted into kinetic the subsequent bucket section of the Turbine ,a portion of the kinetic energy is transferred tothe rotating buckets and converted to of the work developed by the Turbine isused to drive the compressor, and the remain-der is available for useful work at the outputflange of the gas Turbine . Typically, more than50% of the work developed by the Turbine sec-tions is used to power the axial flow shown in Figure 2, single-shaft gas turbinesare configured in one continuous shaft and,therefore, all stages operate at the same units are typically used for generator-drive applications where significant speed varia-tion is not schematic diagram for a simple-cycle, two-shaft gas Turbine is shown in Figure 3.

7 The low-pressure or power Turbine rotor is mechani-cally separate from the high-pressure turbineand compressor rotor. The low pressure rotoris said to be aerodynamically coupled. Thisunique feature allows the power Turbine to beoperated at a range of speeds and makes two-shaft gas turbines ideally suited for variable-speed of the work developed by the power turbineis available to drive the load equipment sincethe work developed by the high-pressure tur-bine supplies all the necessary energy to drivethe compressor. On two-shaft machines thestarting requirements for the gas Turbine loadtrain are reduced because the load equipmentis mechanically separate from the Brayton CycleThe thermodynamic cycle upon which all gasturbines operate is called the Brayton 4shows the classical pressure-volume(PV) and temperature-entropy (TS) diagramsfor this cycle.

8 The numbers on this diagram cor-GE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)3 CompressorInlet Air1 CombustorFuel24 Exhaust3 TurbineGeneratorFigure , single-shaft gas turbineGT08922 Arespond to the numbers also used in Figure 1 to 2 represents the compression occur-ring in the compressor, path 2 to 3 representsthe constant-pressure addition of heat in thecombustion systems, and path 3 to 4 representsthe expansion occurring in the path from 4 back to 1 on the Brayton cyclediagrams indicates a constant-pressure coolingprocess. In the gas Turbine , this cooling is doneby the atmosphere, which provides fresh, coolair at point 1 on a continuous basis in exchangefor the hot gases exhausted to the atmosphereat point 4. The actual cycle is an open ratherthan closed cycle, as Brayton cycle can be characterized by twosignificant parameters: pressure ratio and firingtemperature.

9 The pressure ratio of the cycle isthe pressure at point 2 (compressor dischargepressure) divided by the pressure at point 1(compressor inlet pressure). In an ideal cycle,GE Gas Turbine Performance CharacteristicsGE Power Systems GER-3567H (10/00)4 ExhaustLoadLPCompressorInlet AirCombustorFuelHPTurbineFigure , two-shaft gas turbine121212344433 FuelPTSVF igure cycleGT08923 CGT23055 Athis pressure ratio is also equal to the pressureat point 3 divided by the pressure at point , in an actual cycle there is some slightpressure loss in the combustion system and,hence, the pressure at point 3 is slightly lessthan at point 2. The other significant parameter, firing temper-ature, is thought to be the highest temperaturereached in the cycle. GE defines firing temper-ature as the mass-flow mean total temperatureat the stage 1 nozzle trailing edge all first stage nozzles are cooled tokeep the temperatures within the operating lim-its of the materials being used.

10 The two types ofcooling currently employed by GE are air andsteam. Air cooling has been used for more than 30years and has been extensively developed in air-craft engine technology, as well as the latest fam-ily of large power generation machines. Airused for cooling the first stage nozzle enters thehot gas stream after cooling down the nozzleand reduces the total temperature immediatelydownstream. GE uses this temperature since it ismore indicative of the cycle temperature repre-sented as firing temperature by point 3 in Figure4. Steam-cooled first stage nozzles do not reducethe temperature of the gas directly throughmixing because the steam is in a closed shown in Figure 5, the firing temperature ona Turbine with steam-cooled nozzles (GE s cur-rent H design) has an increase of 200degrees without increasing the combustionexit alternate method of determining firing tem-perature is defined in ISO document 2314, GasTurbines Acceptance Tests.


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