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Compressors, Gas Turbines and Jet Engines

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

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

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Compressors, Gas Turbines and Jet Engines
Inter cooling in compressors

Results in saving of power in compressing a given volume to given pressure
Cools the delivered air
Is the standard practice for big compressors
Enables compression in two stages

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Compressors, Gas Turbines and Jet Engines
Phenomenon of choking in compressor means

No flow of air
Reducing mass flow rate with increase in pressure ratio
Fixed mass flow rate regardless of pressure ratio
Increased inclination of chord with air steam

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

200°C
500°C
1000°C
700°C

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Compressors, Gas Turbines and Jet Engines
Gas turbine blades are given a rake

In the direction of motion of blades
Depending on the velocity
Equal to zero
Opposite to the direction of motion of blades

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Compressors, Gas Turbines and Jet Engines
The thermodynamic efficiency of rotary compressor is based on

Isentropic compression
Isothermal compression
Adiabatic compression
Polytropic compression

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MORE MCQ ON Compressors, Gas Turbines and Jet Engines

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