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A real turbojet with a mass flow rate of 17kg/s has been tested on the sea level. The compressor delivery pressure is 300kPa and
A real turbojet with a mass flow rate of 17kg/s has been tested on the sea level. The compressor delivery pressure is 300kPa and the ideal fuel air ratio is 0.0182. It is fuelled by kerosene. The component efficiencies are assumed to be the following: Compressor Polytropic efficiency: 0.85 Turbine Polytropic efficiency: 0.9 Isentropic efficiency of intake 0.95 Isentropic efficiency of each propelling nozzle 0.95 Mechanical efficiency of each spool: 0.99 Combustion chamber loss: 6% compressor delivery Combustion efficiency: 0.99 Find the Turbine Inlet temperature, propelling nozzle jet velocity and thrust. (Approximate answers: TIT = 1100K, C= 525m/s, F = 8.9kN)
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Elements Of Chemical Reaction Engineering
Authors: H. Fogler
6th Edition
013548622X, 978-0135486221
