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

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

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Compressors, Gas Turbines and Jet Engines
Intercooling in gas turbines

Increases net output but decreases thermal efficiency
Decreases net output and thermal efficiency both
Decreases net output but increases thermal efficiency
Increases net output and thermal efficiency both

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