Air enters a gas-turbine engine (see Fig. 8.11) at 305 K and 1.05 bar and is compressed to 7.5 bar. The fuel is methane at 300 K and 7.5 bar; compressor and turbine efficiencies are each 80%. For one of the turbine inlet temperatures T_C given below, determine: the molar fuel to-air ratio, the net mechanical power delivered per mole of fuel, and the turbine exhaust temperature T_D. Assume complete combustion of the methane and expansion in the turbine to 1(atm).
(a) T_C = 1000 K 

(b) T_C = 1250 K 

(c) T_C = 1500 K

Figure 8.11

Transcribed Image Text:

Compressor Combustion gases Turbine Air D Work B Combustion chamber + Fuel Figure 8.11: Gas-turbine engine.