Compressors, Gas Turbines and Jet Engines
Axial flow compressor has the following advantage over centrifugal compressor

Higher pressure ratio per stage
Higher average velocities
Larger air handling ability per unit frontal area
Aerofoil blades are used

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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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