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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The axial flow compressor is preferred in aircraft gas turbines because of

Low frontal area
Higher thrust
High pressure rise
None of the listed here

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

Nitrogen
Ammonia and water vapour
Carbon dioxide
Hydrogen

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Compressors, Gas Turbines and Jet Engines
Actual compression curve is

In between isothermal and adiabatic
Same as isothermal
Better than isothermal and adiabatic
Same as adiabatic

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Compressors, Gas Turbines and Jet Engines
For a two stage compressor, if index of compression for higher stage is greater than index of compression for lower stage, then the optimum pressure as compared to ideal case will

Remain unaffected
Decrease
Increase
Other factors control it

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Compressors, Gas Turbines and Jet Engines
Adiabatic compression is one in which

No heat leaves or enters the compressor cylinder during compression
Temperature during compression remains constant
Work done is maximum
Temperature rise follows a linear relationship

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Compressors, Gas Turbines and Jet Engines
The work ratio of simple gas turbine cycle depends on

Maximum cycle temperature
Minimum cycle temperature
Pressure ratio
All of these

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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