xample 9.12 ANALYZING A TURBOJET ENGINE Air enters a turbojet engine at 0.8 bar. 240 K. and an inlet velocity of 1000 km/h (278 m/s). The pressure ratio across the compressor is 8. The turbine inlet temperature is 1200 K and the pressure at the nozzle exit is 0.8 bar. The work developed by the turbine equals the compressor work input. The diffuser, compressor, turbine, and nozzle processes are isentropic, and there is no pressure drop for flow through the combustor. For operation at steady state, determine the velocity at the nozzle exit and the pressure at each principal state. Neglect kinetic energy at the exit of all components except the nozzle and neglect potential energy throughout. Diffuser T₁ = 240 K P=0.8 bar V₁ = 1000 km/h =0 Combustor T₁-1200 K PP₁ = 8 Turbine Nozzle 5 Ps=0.8 bar T T₁ = 1200 K T₁ = 240 K 41