A turbo-jet aircraft is flying with the velocity 800 km/h

A turbo-jet aircraft is flying with the velocity 800 km/h at 10700 m, where pressure and temperature are 0.24 bar and -50oC respectively. The compressor pressure ratio is 10/1 and maximum cycle temperature is 820oC. Calculate the thrust developed and the specific fuel consumption using the following information;

ɳentery-duct = 90%  ɳc = 90%  ɳcombustion = 98%   ɳT = 92%   ɳm = 98%       ɳN = 92%

Stagnation pressure loss in the combustion chamber = 0.14 bar

Cvfuel = 43300 kJ/kg   A2 = 0.08 m2

For Compressor & Diffuser – [CP = 1.005 kJ/kg   and   γ=1.4] – For air

 For Combustion & Expansion – [CP = 1.15 kJ/kg   and   γ=1.333] – For product gases

Assume: Nozzle is converging nozzle

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