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A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a...

A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser with a volumetric flow rate of 63.7 m3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 10 and the compressor has an isentropic efficiency of 85%. The turbine inlet temperature is 1240 K, and its isentropic efficiency is 85%. The turbine exit pressure is 50 kPa and the nozzle exit pressure is 40 kPa. Flow through the diffuser and nozzle is isentropic. Use an air-standard analysis and neglect kinetic energy except at the diffuser inlet and the nozzle exit

a)

Determine the power delivered to the propeller, in MW.

b) velocity at the nozzle exit in m/s

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