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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The maximum compression ratio in an actual single stage axial flow compressor is of the order of

0.00070833333333333
0.048611111111111
0.045138888888889
0.043055555555556

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Compressors, Gas Turbines and Jet Engines
Isothermal compression though most efficient, but is not practicable because

It does not increase pressure much
It requires very big cylinder
It is impossible in practice
Compressor has to run at very slow speed to achieve it

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

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Compressors, Gas Turbines and Jet Engines
The degree of reaction of an axial flow turbine is the ratio of isentropic temperature drop in a blade row to the

Total temperature drop in the stage
Total adiabatic temperature drop
Total temperature drop
Adiabatic temperature drop in the stage

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Compressors, Gas Turbines and Jet Engines
The compressed air may be used

In starting and supercharging of I.C. engines
For operating pneumatic drills
All of the listed here
In gas turbine plants

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Compressors, Gas Turbines and Jet Engines
The compressor performance at higher altitude compared to sea level will be

Higher
Dependent on other factors
Lower
Same

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