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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The propulsive power of the rocket is (where v₁ = Jet velocity, and v₂ = Aircraft velocity)

(v₁ - v₂)²/g
(v₁ - v₂)²/2g
(v₁² -v₂²)/g
(v₁² -v₂²)/2g

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

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

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Compressors, Gas Turbines and Jet Engines
Reheating in a gas turbine

Increases the thermal efficiency
Increases the turbine work
Decreases the thermal efficiency
Increases the compressor work

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Compressors, Gas Turbines and Jet Engines
Pick up the wrong statement about advantages of multistage compression

Better lubrication is possible advantages of multistage
More loss of air due to leakage past the cylinder
Air can be cooled perfectly in between
Mechanical balance is better

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Compressors, Gas Turbines and Jet Engines
The ratio of specific weight/h.p. of gas turbine and I.C engines may be typically of the order of

0.084027777777778
0.16736111111111
0.042361111111111
0.045833333333333

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Compressors, Gas Turbines and Jet Engines
Isothermal compression efficiency, even when running at high speed, can be approached by using

Cold water spray
Both (A) and (B) above
Fully insulating the cylinder
Multistage compression

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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