Consider two versions of a turbojet engine. The first is an uncooled engine with

Question

Consider two versions of a turbojet engine. The first is an uncooled engine with a turbine inlet temperature of 1800 K. The second is identical, except that its turbine is cooled by bleeding air from the compressor; in this way the turbine inlet temperature is raised to 2000 K. The design conditions for this engine are as follows; Flight Mach number is 2.0 and ambient temperature is 200 K. The compressor pressure ratio is 9:1. Suppose that 10% of the airflow is used for turbine cooling and that it is bled off at the back of the compressor. After cooling the turbine the bleed air is exhausted overboard with no appreciable velocity. For simplicity assume all components of both engines to be reversible. Let gamma = 1.4 and Cp = 1.0 kJ/kg-K. Determine the thrust of the two engines per unit mass flow of air entering the compressor. What is the ratio of the thrust specific fuel consumption of the second engine to that of the first?

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a smaller image would be good

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