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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The effective power of gas turbines is increased by adding the following in compressor

Hydrogen
Carbon dioxide
Nitrogen
Ammonia and water vapour

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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
0.045138888888889
0.043055555555556
0.048611111111111

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Compressors, Gas Turbines and Jet Engines
A turboprop is preferred to turbojet because

It can fly at supersonic speeds
It can fly at high elevations
It has high propulsive efficiency at high speeds
It has high power for take off

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Compressors, Gas Turbines and Jet Engines
The pressure and temperature conditions of air at the suction of compressor are

Pressure slightly less than atmospheric and temperature slightly more than atmospheric
Slightly more than atmospheric
Atmospheric
Slightly less than atmospheric

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Compressors, Gas Turbines and Jet Engines
It is not possible to use closed gas turbine cycle in aeronautical engines because

It is bulky
None of these
It is inefficient
It requires cooling water for its operation

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

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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