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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The stagnation pressure rise in a centrifugal compressor takes place

In the diffuser and impeller
In the inlet guide vanes only
In the diffuser only
In the impeller only

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Compressors, Gas Turbines and Jet Engines
For minimum work required to compress and deliver a quantity of air by multistage compression

The intercooling should be perfect
The compression ratio in each stage should be same
All of the listed here
The work-done in each stage should be same

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Compressors, Gas Turbines and Jet Engines
Which is false statement about advantages of multistage compressor in comparison to single stage compressor?

Lower volumetric efficiency
Better mechanical balance
Less power requirement
Less loss of air due to leakage past the cylinder

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Compressors, Gas Turbines and Jet Engines
The efficiency of a jet engine is higher at

Low speeds
High speeds
High altitudes
Low altitudes

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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
Increase
None of these
Remain same

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Compressors, Gas Turbines and Jet Engines
The ratio of the discharge pressure to the inlet pressure of air is called

Volumetric efficiency
Compressor efficiency
Compression ratio
Expansion ratio

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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