Compressors, Gas Turbines and Jet Engines
The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio

First decreases and then increases
Decreases
First increases and then decreases
Increases

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Compressors, Gas Turbines and Jet Engines
For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling and no pressure losses. If compression in both the cylinders follows the same polytropic process and the atmospheric pressure is pa, then the intermediate pressure p₂ is given by

P₂ = Pa × p₃/p₁
p₂ = Pa p₃/p₁
p₂ = (p₁ + p₃)/2
p₂ = p₁. p₃

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