Engineering, 29.04.2021 04:50 24lbriscoe

A turboprop engine (Fig. 9.27a) 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 83.7 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 1140 K, and its isentropic efficiency is 85%. The turbine exit pressure is 50 kPa. Combustion occurs at constant pressure. Flow through the diffuser and nozzle is isentropic. Using an air-standard analysis, determine (a) the power delivered to the propeller, in MW. (b) the velocity at the nozzle exit, in m/s. Neglect kinetic energy except at the diffuser inlet and the nozzle exit.

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A turboprop engine (Fig. 9.27a) consists of a diffuser, compressor, combustor, turbine, and nozzle....

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