1. A turbojet engine is fitted to an aircraft flying at M = 0.65 in conditions...

1. A turbojet engine is fitted to an aircraft flying at M = 0.65 in conditions where the

ambient temperature is 216 K and the ambient pressure is 18.75 kPa. You are to assume

adiabatic flow.

The following data on the engine are known:

Intake efficiency ?? = 1.00 Intake maximum pressure ratio ?? ??? = 0.95 Compressor pressure ratio ?? = 12 Compressor polytropic efficiency ?? = 1 Combustion chamber efficiency ?? = 1 Turbine Inlet temperature ?4 = 1796 ? Calculate:

a. The total temperature and pressure at entry to the compressor.

b. The total temperature and pressure at entry to the combustion chamber.

c. The fuel-to-air ratio in the combustion chamber.

Expert Solution

samet mamat answered 8 months ago

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