COMPRESSORS, GAS TURBINES AND JET ENGINES QUIZ

As the turbine inlet temperature increases, the thermal efficiency of gas turbine for the optimum pressure ratio

First increases and then decreases

Remain same

Decreases

Increases

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Out of the following, from where you will prefer to take intake for air compressor

From an air conditioned room maintained at 20°C

From coal yard side

From a side where cooling tower is located nearby

From outside atmosphere at 1°C

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In a jet propulsion

The propulsive matter is caused to flow around the propelled body

The propulsive matter is ejected from within the propelled body

None of these

Its functioning does not depend upon presence of air

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In jet engines, for the efficient production of large power, fuel is burnt in an atmosphere of

Atmospheric air

Oxygen alone

Vacuum

Compressed air

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The output of a gas turbine is 300 KW and its efficiency is 20 percent, the heat supplied is

6000 KW

15 KW

600 KW

150 KW

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A simple turbojet engine is basically

Ramjet engine

A propeller system

Gas turbine engine equipped with a propulsive nozzle and diffuse

Chemical rocket engine

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The axial flow compressor is preferred in aircraft gas turbines because of

High pressure rise

None of the listed here

Higher thrust

Low frontal area

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The thermodynamic efficiency of rotary compressor is based on

Isothermal compression

Polytropic compression

Adiabatic compression

Isentropic compression

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For a two stage compressor, if index of compression for higher stage is greater than index of compression for lower stage, then the optimum pressure as compared to ideal case will

Other factors control it

Decrease

Remain unaffected

Increase

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Isothermal compression efficiency can be attained by running the compressor

At very high speed

At very slow speed

At zero speed

At average speed

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