a turbojet aircraft is travelling at a speed of 925 kilometres per hour in atmospheric conditions of 0.45 bars and -26 degree centigrade. the compression ratio used is 8 and the air mass flow rate is 45 kg/sec and the allowable maximum cycle temperature is 827 degree centigrade. the entry duct, compressor, gas turbine and jet pipe stagnation isentropic efficiency are 0.9, 0.85, 0.89 and 0.9. the mechanical efficiency of the drive is 0.98 and the combustion efficiency is 0.99. assuming a convergent propeller nozzle a loss of stagnation pressure in the combustion chamber is 0.2 bars and fuel of cv 43.3 mj/kg is used. calculate:- i) required nozzle area ii) net thrust developed iii) specific fuel consumption for gases in turbine and nozzle take υ = 1.333, cp = 1.15 kj/kg-k and for combustion process take equivalent cp = 1.15 kj/kg-k.
a turbojet aircraft is travelling at a speed of 925 kilometres per hour in atmospheric conditions of 0.45 bars and -26 degree centigrade. the compression ratio used is 8 and the air mass flow rate is 45 kg/sec and the allowable maximum cycle temperature is 827 degree centigrade. the entry duct, compressor, gas turbine and jet pipe stagnation isentropic efficiency are 0.9, 0.85, 0.89 and 0.9. the
Step by step
Solved in 2 steps with 1 images
