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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
High air-fuel ratio in gas turbines

Reduces exhaust temperature
Improves thermal efficiency
Increases power output
Do not damage turbine blades

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

Maximum cycle temperature
All of these
Minimum cycle temperature
Pressure ratio

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Compressors, Gas Turbines and Jet Engines
If infinite number of heaters be used in a gas turbine, then expansion process in turbine approaches

Isentropic
Isochoric
Isothermal
Adiabatic

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Compressors, Gas Turbines and Jet Engines
In a jet engine, the air-fuel ratio is

1.6673611111111
2.5006944444444
2.0840277777778
1.2506944444444

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Compressors, Gas Turbines and Jet Engines
In turbo fan engine, the jet velocity as compared to turbojet engine is

Less
May be less or more depending upon speed
More
Same

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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?

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

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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