N = 7 Question # 1 There is a two spool axial flow turbofan engine designed to power an aircraft. The following are some

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N = 7
Question # 1 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.N, overall pressure ratio 10+N, 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. Calculate thermal, propulsion and overall efficiencies.