Ideal turbojet problem: An ideal turbojet engine operates at an altitude of 15 km.Look up values for Ta and p a in a standard atmosphere table on the web.Flight Mach number is 0.85. The compressor pressure ratio CPR is 40, the maximumgas temperature (T04 ) is 1500 K. The Jet-A fuel has a heating value of Q R = 45,000kJ/kg. The nozzle perfectly expands the gas so that exit static pressure p e equals p a .Use the same equations as we did in our lecture problem for an ideal turbojet.Ideal means that the inlet, compressor, turbine and exhaust are isentropic.As we discussed, the Mach number of the air is small at stations 2-5 so static andstagnation conditions are the same. a) calculate the following numbers so you can eventually use them to create the plots in part b.i) what is the exit velocity of air in the exhaust ?ii) what is the specific thrust, in kN thrust / (kg/s of air) ?iii) what is the specific fuel consumption = kg/s of fuel / kN thrust ? iv) what is the fuel-air ratio f ? Please help me with this I have little to no idea what to do, and please show work so I can gain an understanding
Ideal turbojet problem: An ideal turbojet engine operates at an altitude of 15 km.
Look up values for Ta and p a in a standard atmosphere table on the web.
Flight Mach number is 0.85. The compressor pressure ratio CPR is 40, the maximum
gas temperature (T04 ) is 1500 K. The Jet-A fuel has a heating value of Q R = 45,000
kJ/kg. The nozzle perfectly expands the gas so that exit static pressure p e equals p a .
Use the same equations as we did in our lecture problem for an ideal turbojet.
Ideal means that the inlet, compressor, turbine and exhaust are isentropic.
As we discussed, the Mach number of the air is small at stations 2-5 so static and
stagnation conditions are the same.
a) calculate the following numbers so you can eventually use them to create the plots in part b.
i) what is the exit velocity of air in the exhaust ?
ii) what is the specific thrust, in kN thrust / (kg/s of air) ?
iii) what is the specific fuel consumption = kg/s of fuel / kN thrust ? iv) what is the fuel-air ratio f ?
Please help me with this I have little to no idea what to do, and please show work so I can gain an understanding
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