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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The maximum propulsion efficiency of a turbojet is attained at around following speed

1050 km/hr
550 km/hr
2400 km/hr
1700 km/hr

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

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

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Compressors, Gas Turbines and Jet Engines
In axial flow compressor, exit flow angle deviation from the blade angle is a function of

Space-chord ratio
Blade camber
Blade camber and incidence angle
Blade camber and space-chord ratio

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Compressors, Gas Turbines and Jet Engines
A rocket engine for the combustion of its fuel

Does not require oxygen
Uses surrounding air
Carries its own oxygen
Uses compressed atmospheric air

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

To increase the output
To reduce the exit temperature
To save fuel
To increase the efficiency

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Compressors, Gas Turbines and Jet Engines
In a single stage, single acting reciprocating air compressor, without clearance, the work-done on the air during isentropic compression is ________ the heat required to raise the temperature of air from T₁ to T₂ at a constant pressure.

Greater than
None of these
Equal to
Less than

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