Consider an ideal air-standard cycle for a gas-turbine, jet propulsion unit, such as that shown below. The pressure and temperature entering the compressor are 90 kPa, 290 K. The pressure ratio across the compressor is 14 to 1, and the turbine inlet temperature is 1500 K. When the air leaves the turbine, it enters the nozzle and expands to 90 kPa. Determine (a) the velocity of the air leaving the nozzle, sketch and label the T-s diagram Bumer Compressor Turbine Nozzle

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