Compressors, Gas Turbines and Jet Engines
For an irreversible gas turbine cycle, the efficiency and work ratio both depend on

Maximum cycle temperature alone
Pressure ratio alone
Both pressure ratio and maximum cycle temperature
Minimum cycle temperature alone

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

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

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