1) A jet propelled aircraft flying at a mach number 0.6 at an altitude of 5.0 km inducts air at a rate of 20 kg/s. The diffuser recovery is 0.9. The compressor pressure ratio is 5.0 and the maximum total temperature in the cycle is 1300 K. The gases expand in the nozzle to a pressure of 0.7 bar. The isentropic efficiencies of the compressor, turbine and nozzle are 0.8, 0.85 and 0.92 respectively. The calorific value of the fuel is 44 MJ/kg. Assume that the products of combustion have the same properties as that of air. Calculate (i) Air-fuel ratio (ii) Power output of turbine (iii) Exhaust jet velocity (iv) Engine thrust and (v) Overall efficiency.
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1) A jet propelled aircraft flying at a mach number 0.6 at an altitude of 5.0 km inducts air at a rate of 20 kg/s. The diffuser recovery is 0.9. The compressor pressure ratio is 5.0 and the maximum total temperature in the cycle is 1300 K. The gases expand in the nozzle to a pressure of 0.7 bar. The isentropic efficiencies of the compressor, turbine and nozzle are 0.8, 0.85 and 0.92 respectively. The calorific value of the fuel is 44 MJ/kg. Assume that the products of combustion have the same properties as that of air. Calculate (i) Air-fuel ratio (ii) Power output of turbine (iii) Exhaust jet velocity (iv) Engine thrust and (v) Overall efficiency.
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