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

Decrease
None of these
Increase
Remain same

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Compressors, Gas Turbines and Jet Engines
The overall isothermal efficiency of the compressor is defined as the ratio of

Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor
Isentropic power to the power required to drive the compressor
Volume of free air delivery per stroke to the swept volume of the piston
Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio

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