Chapter 13 Gas Turbine Power Plants

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Cycle Pressure Ratio Figure 13.3 Effect of turbine inlet temperature on efficiency the previous section. Figure 13.4 depicts the variation of exhaust temperatures over the same range of pressure ratios at a turbine inlet temperature of 1300°K. It is noted that the temperatures of the exhaust gases are quite high, which leads one to think that efficiency could be increased, if some way were found to utilize the energy of the exhaust gases. Energy could be extracted from the gas in a waste heat boiler, for example; another way would be to use the exhaust to heat the air prior to combustion. The latter method is commonly used and is called regeneration, i.e., extracting energy from the exhaust gases by means of heat transfer in a heat exchanger used to preheat the compressed air before it is admitted to the combustor. A Brayton-cycle gas turbine with regeneration is depicted schematically in Figure 13.5. Air from the compressor enters the regenerator at temperature T 02 - and is heated to temperature T 05 ;
1200 1000 800 S I 0> c. 600 I 1a Turbine inlet temperature = 1300 deg K 400 200 8 10 12 Cycle Pressure Ratio 14 16 18 Figure 13.4 Turbine exhaust temperatures then it enters the combustor and leaves at T 03 . The energy added in the combustor is thus reduced to QA =c (T
Page 1 and 2: Chapter 13 Gas Turbine Power Plants
Page 3 and 4: in the cycle 1-2-3-4-1, the cycle i
Page 5 and 6: - r ^02 ~ -' and (13.8) which are d
Page 7: Q A =C p (T 03 -T 02 .) (13.14) whe
Page 11 and 12: Air In Regenerator •* — ——
Page 13 and 14: Air In + 06 Figure 13.7 Gas turbine
Page 15 and 16: actual compression in the first sta
Page 17 and 18: heated from T 08 -to T 09 , The fin
Page 19 and 20: 13.8 Combined Brayton and Rankine C
Page 21 and 22: Problems 13.1 Write the expression
Page 23 and 24: 13.12 A Brayton cycle with regenera
Page 25 and 26: fuel-air ratio, the net power devel
Page 27: the combine cycle, and the thermal

Chapter 13 Gas Turbine Power Plants

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