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A turbojet aircraft is flying with a velocity of 280 m/s at an altitude of 9150 m, where the ambient conditions are 32 kPa and -32°C. The pressure ratio across the compressor is 12, and the temperature at the turbine inlet is 1100 K. Air enters the compressor at a rate of 50 kg/ s, and the jet fuel has a heating value of 42,700 kJ/ kg. Assuming constant specific heats for air at room temperature, compressor efficiency is 80 percent and a turbine efficiency is 85 percent.Determine (a) the velocity of the exhaust gases, (b) the propulsive power developed, and (c) the rate of fuel consumption. (Put in part c as answer in unit kg/s)

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