Solution by clear handwritten There is a two spool axial flow turbofan engine designed to power an aircraft. The followi

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Solution by clear handwritten
There is a two spool axial flow turbofan engine designed to power an aircraft. The following are some preliminary data under the conditions:
Mach number 0.5, overall pressure ratio 10.5, inlet diameter 0.8 m, ambient conditions pa = 0.2650 bar, Ta = 223.3 K.
Inlet diffuser: stagnation pressure ratio 0.98, engine intake diameter 2 m.
Fan: pressure ratio 1.7, isentropic efficiency 0.88.
Compressor: isentropic efficiency 0.85.
Combustor: exit temperature 1400 K, burning efficiency 0.98, and pressure loss 3%. HPT: drives the compressor, isentropic efficiency 0.9 and mechanical efficiency 0.99. LPT: drives the fan, isentropic efficiency 0.9 and mechanical efficiency 0.99.
Mixer: Ideal mixing
Exhaust nozzle: efficiency 0.95
It is required to:
1. Draw the neat engine diagram and label different components.
2. Find the bypass ratio assuming Fan, LPT, and Fan exit pressures are equal.
3. Draw the T-s diagram and write all the pressure and temperature magnitudes.
4. Calculate the engine total and specific thrust and fuel consumption.
5. Calculate thermal, propulsion and overall efficiencies.
6. Discuss the effect of increasing the TIT on the engine performance.
7. Discuss the effect of increasing the OPR on the engine performance.