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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The work done per unit mass of air in compression will be least when 'n' is equal to

1.3
1.2
1
1.4

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Compressors, Gas Turbines and Jet Engines
The thrust of a jet propulsion power unit can be increased by

Injecting ammonia into the combustion chamber
All of these
Injecting water into the compressor
Burning fuel after gas turbine

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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

None of these
Increase
Decrease
Remain same

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Compressors, Gas Turbines and Jet Engines
When air is to be compressed at a high pressure, then it is advantageous to use

Multistage compression without intercooling
Single stage compression
Multistage compression with intercooling
None of these

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Compressors, Gas Turbines and Jet Engines
Pressure ratio in gas turbines is the ratio of

Inlet pressure to exhaust pressure
Compressor pressure ratio
Pressures across the turbine
Highest pressure to exhaust pressure

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Compressors, Gas Turbines and Jet Engines
Propulsive efficiency is defined as ratio of

Thrust power and propulsive power
Propulsive power and fuel input
Thrust power and fuel energy
Engine output and propulsive power

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