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

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Compressors, Gas Turbines and Jet Engines
A closed cycle gas turbine gives ________ efficiency as compared to an open cycle gas turbine.

Higher
None of these
Same
Lower

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Compressors, Gas Turbines and Jet Engines
The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio

First decreases and then increases
First increases and then decreases
Increases
Decreases

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Compressors, Gas Turbines and Jet Engines
Reheating in multistage expansion gas turbine results in

High thermal efficiency
Decrease of heat loss in exhaust
Maximum work output
Reduction in compressor work

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Compressors, Gas Turbines and Jet Engines
The compression ratio in a gas turbine is of the order of

3.5 : 1
0.50069444444444
0.33402777777778
0.20902777777778

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Compressors, Gas Turbines and Jet Engines
Adiabatic compression is one in which

No heat leaves or enters the compressor cylinder during compression
Temperature rise follows a linear relationship
Temperature during compression remains constant
Work done is maximum

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