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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Compressors, Gas Turbines and Jet Engines
If p₁, is the pressure of air entering the L.P. cylinder and p₂ is the pressure of air leaving the L.P. cylinder (or inter-cooler pressure), then the ratio of cylinder diameters for a single acting, two stage reciprocating air compressor with complete intercooling is given by (where D₁ = Dia. of L.P. cylinder, and D₂ = Dia. of H.P. cylinder)

D₁/D₂ = p₁ p₂
D₁/D₂ = p₂/p₁
None of these
D₁/D₂ = p₁/p₂

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Compressors, Gas Turbines and Jet Engines
Which of the following statement is correct relating to rocket engines?

The exit velocities of exhaust gases are much higher than those in jet engine
The stagnation conditions exist at the combustion chamber
All of these
The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel

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