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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The criterion of the thermodynamic efficiency for rotary compressor is

Isothermal compression
None of the listed here
Polytropic compression
Isentropic compression

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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

0.043055555555556
0.048611111111111
0.045138888888889
0.00070833333333333

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Compressors, Gas Turbines and Jet Engines
The thrust of a jet propulsion power unit can be increased by

All of these
Injecting water into the compressor
Burning fuel after gas turbine
Injecting ammonia into the combustion chamber

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Compressors, Gas Turbines and Jet Engines
As the turbine inlet temperature increases, the thermal efficiency of gas turbine for the optimum pressure ratio

Increases
Remain same
First increases and then decreases
Decreases

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Compressors, Gas Turbines and Jet Engines
Euler's equation is applicable for

All of these
Axial compressor
Centrifugal compressor
Pumps

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Compressors, Gas Turbines and Jet Engines
Maximum work is done in compressing air when the compression is

None of these
Isothermal
Adiabatic
Polytropic

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