Compressors, Gas Turbines and Jet Engines
There is a certain pressure ratio (optimum) for a gas turbine at which its thermal efficiency is maximum. With increase in turbine temperature, the value of pressure ratio for the peak efficiency would

Decrease
None of these
Increase
Remain same

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Compressors, Gas Turbines and Jet Engines
If p₁ is the pressure of air entering the L.P, cylinder and p₃ is the pressure of air leaving the H.P. cylinder, then the ratio of cylinder diameters for a single acting, two stage reciprocating compressor with complete intercooling is given by

D₁/D₂ = (p₁ p₃)1/4
D₁/D₂ = (p₃/p₁)1/4
D₁/D₂ = (p₁/p₃)1/4
D₁/D₂ = (p₁ p₃)1/2

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