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. 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.

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. 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.