A turbojet engine flying under cruise conditions at a Mach number 0.78 has a pressure ratio of 26 (i.e. p03/p02 using th

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A turbojet engine flying under cruise conditions at a Mach
number 0.78 has a pressure ratio of 26 (i.e. p03/p02 using the
numbering system given below) and a maximum temperature of 1300 K
(i.e. T04). The ambient pressure and temperature are 20.0 kPa and
218.5 K. There are no mechanical transmission losses along the
shaft that connects the compressor and the turbine and no pressure
losses across the burner (i.e. p04 = p03). The Lower Calorific
Value of the fuel is 45,000 kJ/kg and the nozzle exit pressure is
equal to atmospheric.
The component efficiencies are:
Assuming all the flow processes are adiabatic, calculate:
(a) The stagnation temperature just before the compressor
T02
(b) The stagnation pressure just before the compressor
P02
(c) The stagnation temperature just after the compressor
T03
(d) Calculate f, the ratio of the mass flow rate of fuel
to the mass flow rate of air, stating any assumptions you make.
(e) Calculate the stagnation temperature just after the
turbine T05
(f) Calculate the stagnation pressure just after the turbine P05