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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

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

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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
Inversely proportional to clearance volume
Greatly affected by clearance volume
Directly proportional to clearance volume

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Compressors, Gas Turbines and Jet Engines
For maximum work, the reheating should be done to an intermediate pressure of (Where p₁ = Maximum pressure, and p₂ = Minimum pressure)

p₁ p₂
(p₁ - p₂)/2
(p₁ + p₂)/2
p₁/p₂

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Compressors, Gas Turbines and Jet Engines
Actual compression curve is

In between isothermal and adiabatic
Same as isothermal
Better than isothermal and adiabatic
Same as adiabatic

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Compressors, Gas Turbines and Jet Engines
Stalling of blades in axial flow compressor is the phenomenon of

Air stream blocking the passage
Unsteady periodic and reversed flow
Air stream not able to follow the blade contour
Motion of air at sonic velocity

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Compressors, Gas Turbines and Jet Engines
The efficiency of jet engine is

Higher at high altitudes
Same at all altitudes
Higher at high speed
Lower at low speed

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