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Compressors, Gas Turbines and Jet Engines

Compressors, Gas Turbines and Jet Engines
A closed gas turbine in which fuel is burnt directly in the air is not possible because of

Paucity of O2
Increasing gas temperature
High specific volume
High friction losses

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

Improves thermal efficiency
Increases power output
Do not damage turbine blades
Reduces exhaust temperature

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Compressors, Gas Turbines and Jet Engines
Isothermal compression efficiency, even when running at high speed, can be approached by using

Both (A) and (B) above
Multistage compression
Cold water spray
Fully insulating the cylinder

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Compressors, Gas Turbines and Jet Engines
Ram compression in turbojet involves

Lost work
Reduction of speed of incoming air and conversion of part of it into pressure energy
Compression of inlet air
Increasing speed of incoming air

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

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

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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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