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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The maximum temperature in a gas turbine is

700°C
1000°C
500°C
200°C

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Compressors, Gas Turbines and Jet Engines
High air-fuel ratio is used in gas turbines

To save fuel
To increase the efficiency
To increase the output
To reduce the exit temperature

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Compressors, Gas Turbines and Jet Engines
The pressure ratio of an ideal vaned compressor with increase in mass flow rate

First decreases and then increases
Increases
Remain constant
Decreases

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Compressors, Gas Turbines and Jet Engines
The type of rotary compressor used in gas turbines, is of

Centrifugal type
None of the listed here
Radial flow type
Axial flow type

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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
In open cycle turbojet engines used in military aircraft, reheating the exhaust gas from the turbine by burning, more fuel is used to increase the

Efficiency of the engine
Thrust and range of aircraft
Both (A) and (B)
None of these

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