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GE Gas Turbine Performance Characteristics

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GE Gas Turbine Performance Characteristics ( ge-gas-turbine-performance-characteristics )

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GE Gas Turbine Performance Characteristics Mechanical Drive Gas Turbine Ratings Model Year ISO Rating Continuous (kW) ISO Rating Continuous (hp) Heat Rate (Btu/shp-hr) Heat Rate (kJ/kWh) Mass Flow (lb/sec) Mass Flow (kg/sec) Exhaust Temp (degrees F) Exhaust Temp (degrees C) M3142 (J) 1952 11,290 15,140 9,500 13,440 117 53 1,008 542 M3142R (J) 1952 10,830 14,520 7,390 10,450 117 53 698 370 M5261 (RA) 1958 19,690 26,400 9,380 13,270 205 92 988 531 M5322R (B) 1972 23,870 32,000 7,070 10,000 253 114 666 352 M5352 (B) 1972 26,110 35,000 8,830 12,490 273 123 915 491 M5352R (C) 1987 26,550 35,600 6,990 9,890 267 121 693 367 M5382 (C) 1987 28,340 38,000 8,700 12,310 278 126 960 515 M6581 (B) 1978 38,290 51,340 7,820 11,060 295 134 1,013 545 Table 2. GE gas turbine performance characteristics - Mechanical drive gas turbine ratings GT25385A MS7000 PG 7 12 1 (EA) Application M - Mech Drive PG - Pkgd Gen Series Frame 3,5,7 6,9 Power Number of Shafts Model R - Regen Blank - SC Approx Output Power in Hundreds, Thousands, or 10 Thousands of Horsepower 1 or 2 Figure 1. Heavy-duty gas turbine model designation Thermodynamic Principles A schematic diagram for a simple-cycle, single- shaft gas turbine is shown in Figure 2. Air enters the axial flow compressor at point 1 at ambient conditions. Since these conditions vary from day to day and from location to location, it is convenient to consider some standard condi- tions for comparative purposes. The standard conditions used by the gas turbine industry are 59 F/15 C, 14.7 psia/1.013 bar and 60% relative humidity, which are established by the International Standards Organization (ISO) and frequently referred to as ISO conditions. GT23054A Air entering the compressor at point 1 is com- pressed to some higher pressure. No heat is added; however, compression raises the air temperature so that the air at the discharge of the compressor is at a higher temperature and pressure. Upon leaving the compressor, air enters the combustion system at point 2, where fuel is injected and combustion occurs. The combus- tion process occurs at essentially constant pres- sure. Although high local temperatures are reached within the primary combustion zone (approaching stoichiometric conditions), the GE Power Systems ■ GER-3567H ■ (10/00) 2

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