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 83.7 m^3/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 11140 K, and its isentropic efficiency is 85%. The turbine exit pressure is 50 kPa. Flow through the diffuser and nozzle is isentropic. Using an air-standard analysis, determine the power delivered to the propeller, in MW. the velocity at the nozzle exit, in m/s.
1 answer:
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Answer:
The heat transfer q = 18.32W
Explanation:
In this question, we are asked to calculate the heat entering the tube and also evaluate properties at T =400K
Please check attachment for complete solution and step by step explanation
