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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
In a centrifugal compressor, the highest Mach number leading to shock wave in the fluid flow occurs at

Impeller outlet radius
Diffuser inlet radius
Diffuser outlet radius
Impeller inlet radius

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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?

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

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Compressors, Gas Turbines and Jet Engines
Axial flow compressor has the following advantage over centrifugal compressor

Higher pressure ratio per stage
Higher average velocities
Aerofoil blades are used
Larger air handling ability per unit frontal area

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Compressors, Gas Turbines and Jet Engines
In a single stage, single acting reciprocating air compressor without clearance volume, the work-done is maximum during

None of these
Polytropic compression
Isothermal compression
Isentropic compression

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Compressors, Gas Turbines and Jet Engines
For perfect intercooling in a two stage compressor

p₂/p₁ = p₃/p₂
p₁ = p3
p₁ = p₂ p3
p₁/p₃ = p₂/p₁

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

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

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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