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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
In an axial flow compressor, the ratio of pressure in the rotor blades to the pressure rise in the compressor in one stage is known as

Degree of reaction
Pressure coefficient
Work factor
Slip factor

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

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

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Compressors, Gas Turbines and Jet Engines
For an irreversible gas turbine cycle, the efficiency and work ratio both depend on

Minimum cycle temperature alone
Maximum cycle temperature alone
Pressure ratio alone
Both pressure ratio and maximum cycle temperature

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Compressors, Gas Turbines and Jet Engines
The indicated work per unit mass of air delivered is

Greatly affected by clearance volume
Directly proportional to clearance volume
Not affected by clearance volume
Inversely proportional to clearance volume

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

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Compressors, Gas Turbines and Jet Engines
Air-fuel ratio in a jet engine will be of the order of

2.5006944444444
0.62569444444444
0.83402777777778
0.41736111111111

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