Answer Happy

Consider a single-spool turbojet engine for which the following
parameters are provided:
Altitude: 10𝑘𝑚
Combustion efficiency: 0.97
Turbine efficiency: 0.94
Nozzle efficiency: 0.96
Pressure drop in combustion chamber: 5%
Air mass flow rate: 15 𝑘𝑔⁄𝑠
1) For the following data Diffuser efficiency: 0.90 Compressor
efficiency: 0.88 Turbine inlet temperature: 1300𝐾 Flight Mach
number: 0.9 Fuel heating value: 45000 𝑘𝐽⁄𝑘𝑔 show the variation of
thrust specific fuel consumption with the compressor pressure ratio
for a pressure ratio range of 4 − 12.
Consider a single-spool turbojet engine for which the following parameters are provided: Altitude: 10km Combustion efficiency: 0.97 Turbine efficiency: 0.94 Nozzle efficiency: 0.96 Pressure drop in combustion chamber: 5% Air mass flow rate: 15 kg/s 1) For the following data Diffuser efficiency: 0.90 Compressor efficiency: 0.88 Turbine inlet temperature: 1300K Flight Mach number: 0.9 Fuel heating value: 45000 kJ/kg show the variation of thrust specific fuel consumption with the compressor pressure ratio for a pressure ratio range of 4 - 12. a