Determine what is the turbine isentropic efficiency

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Reference no: EM13265190

A jet engine is modeled as a serial combination of a compressor, an adiabatic constant pressure combustor, and a turbine. Air (considered to have a variable specific heat) is compressed through a compression pressure ratio of 8.25:1. Air enters the compressor at 14.7 psia and 60 F. Air leaves the combustor at 2,200 R. The compression isentropic efficiency is 83%, and the turbine isentropic efficiency is 85%.

An engineer claims that 5% of the air should be bypassed around the compressor and combustor, and used to cool the engine walls in a double wall arrangement. If that is done, the air leaving the combustor can be increased by 5 psi. It is claimed that the engine will produce more thrust.

Assuming that the bypassed air produces no thrust, and ignoring fuel mass, is the engineering corrector?

Reference no: EM13265190

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