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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio)

1 - (1/r) ɣ/ɣ-1
1 - r ɣ-1
r ɣ-1
1 - (1/r) ɣ-1/ɣ

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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
Decrease
Remain same
None of these

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

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

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Compressors, Gas Turbines and Jet Engines
The thrust on the rotor in a centrifugal compressor is produced by

Axial component
None of these
Radial component
Tangential component

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Compressors, Gas Turbines and Jet Engines
For an irreversible gas turbine cycle, the efficiency and work ratio both depend on

Minimum cycle temperature alone
Both pressure ratio and maximum cycle temperature
Maximum cycle temperature alone
Pressure ratio alone

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Compressors, Gas Turbines and Jet Engines
For slow speed large capacity compressor, following type of valve will be best suited

Disc or feather type
Mechanical valve of the Corliss, sleeve, rotary or semi rotary type
Poppet valve
Any of the above

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