Consider an air-standard cycle for the turbojet power plant shown in Fig. 8.13. The temperature and pressure of the air entering the compressor are 1 bar and 30oC. The pressure ratio in the compressor is 6.5, and the temperature at the turbine inlet is 1100oC, if expansion in the nozzle is isentropic and if the nozzle exhausts at I bar, what is the pressure at the nozzle inlet (turbine exhaust) and what is the velocity of the air leaving the nozzle?

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Combustion chamber Turbine Entering air Exhaust gases Noizle - Diffuser Fuel