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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)

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

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Compressors, Gas Turbines and Jet Engines
There is a certain pressure ratio (optimum) for a gas turbine at which its thermal efficiency is maximum. With increase in turbine temperature, the value of pressure ratio for the peak efficiency would

Increase
Remain same
Decrease
None of these

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Compressors, Gas Turbines and Jet Engines
If infinite number of heaters be used in a gas turbine, then expansion process in turbine approaches

Adiabatic
Isochoric
Isothermal
Isentropic

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Compressors, Gas Turbines and Jet Engines
Reciprocating air compressor is best suited for

Small quantity of air at low pressure
Large quantity of air at high pressure
Small quantity of air at high pressure
Large quantity of air at low pressure

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Compressors, Gas Turbines and Jet Engines
The ratio of the increase in pressure in rotor blades to total increase in pressure in the stage is called

Pressure coefficient
Degree of reaction
Slip factor
Pressure ratio

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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

Isentropic compression
Isothermal compression
Polytropic compression
None of these

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