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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
Propulsion efficiency of the following order is obtained in practice

0.34
0.5
0.6
0.72

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

Both (A) and (B) above
Increase of work ratio
Decrease of thermal efficiency
Decrease of work ratio

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Compressors, Gas Turbines and Jet Engines
Inter cooling in compressors

Is the standard practice for big compressors
Results in saving of power in compressing a given volume to given pressure
Cools the delivered air
Enables compression in two stages

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Compressors, Gas Turbines and Jet Engines
A closed cycle gas turbine consists of a

Cooling chamber
Heating chamber
All of these
Compressor

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

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

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