Question

An ideal turbofan operates at 11,000m with a free-stream Mach number of 0.85. Considering the following design inputs:

Bypass ratio:= 8

Fan pressure ratio:= 1.6

Compressor pressure ratio:= 25

Fuel heating energy:hPR= 43,500kJ/kg

Total temperature downstream of the combustor:Tt4= 1420K

a)Calculate all the points and plot the thermodynamic cycle of the core flow on a T-sdiagram.

b)Calculate specific thrust, specific fuel consumption, thermal efficiency, propulsive efficiency and overall efficiency.

c)Compare the performance parameters in part b)with those of an ideal turbojet with the same ?c, Tt4 and hPR.

Answer 1