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4

Axial flow compressor resembles

A. Centrifugal pump

B. Reciprocating pump

C. Turbine

D. Sliding vane compressor

Correct Answer :

C. Turbine


Related Questions

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4

Reheating in gas turbine results in

A. Increase of work ratio

B. Decrease of thermal efficiency

C. Decrease of work ratio

D. Both (A) and (B) above

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4

Reheating in a multistage expansion gas turbine __________ compressor work.

A. Has no effect on

B. Decreases

C. Increases

D. None of these

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4

A compressor mostly used for supercharging of I.C. engines is

A. Radial flow compressor

B. Axial flow compressor

C. Roots blower

D. Reciprocating compressor

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4

A closed cycle gas turbine gives ________ efficiency as compared to an open cycle gas turbine.

A. Same

B. Lower

C. Higher

D. None of these

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4

Reciprocating air compressor is best suited for

A. Large quantity of air at high pressure

B. Small quantity of air at high pressure

C. Small quantity of air at low pressure

D. Large quantity of air at low pressure

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4

A simple turbojet engine is basically

A. A propeller system

B. Gas turbine engine equipped with a propulsive nozzle and diffuse

C. Chemical rocket engine

D. Ramjet engine

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4

To avoid moisture troubles, the branch connections from compressed air lines should be taken from

A. Top side of main

B. Bottom side of main

C. Left side of main

D. Right side of main

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4

The effective power of gas turbines is increased by adding the following in compressor

A. Ammonia and water vapour

B. Carbon dioxide

C. Nitrogen

D. Hydrogen

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4

Pick up the correct statement

A. Gas turbine uses low air-fuel ratio to economise on fuel

B. Gas turbine uses high air-fuel ratio to reduce outgoing temperature

C. Gas turbine uses low air-fuel ratio to develop the high thrust required

D. All of the above

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4

In a jet propulsion unit, the products of combustion after passing through the gas turbine are discharged into

A. Atmosphere

B. Vacuum

C. Discharge nozzle

D. Back to the compressor

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4

The compressor efficiency is the

A. Isothermal H.P/indicated H.R

B. Isothermal H.P./shaft H.R

C. Total output/air input

D. Compression work/motor input

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4

Stalling of blades in axial flow compressor is the phenomenon of

A. Air stream blocking the passage

B. Motion of air at sonic velocity

C. Unsteady periodic and reversed flow

D. Air stream not able to follow the blade contour

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4

The air-fuel ratio in gas turbines is of the order of

A. 7 : 1

B. 15 : 1

C. 30 : 1

D. 50 : 1.

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4

It is not possible to use closed gas turbine cycle in aeronautical engines because

A. It is inefficient

B. It is bulky

C. It requires cooling water for its operation

D. None of the above

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4

A gas turbine used in air craft should have

A. High h.p. and low weight

B. Low weight and small frontal area

C. Small frontal area and high h.p.

D. High speed and high h.p

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4

The ideal efficiency of simple gas turbine cycle depends on

A. Pressure ratio

B. Maximum cycle temperature

C. Minimum cycle temperature

D. All of the above

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4

During peak load periods, the best method of controlling compressors is

A. Start-stop motor

B. Constant speed unloader

C. Relief valve

D. Variable speed

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4

The thermal efficiency of a gas turbine as compared to a diesel plant is

A. Same

B. More

C. Less

D. Depends on other factors

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4

A jet engine works on the principle of conservation of

A. Mass

B. Energy

C. Flow

D. Linear momentum

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4

The air entry velocity m a rocket as compared to aircraft is

A. Same

B. More

C. Less

D. Zero

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4

A closed cycle gas turbine works on

A. Carnot cycle

B. Rankine cycle

C. Ericsson cycle

D. Joule cycle

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4

The compressor capacity with decrease in suction temperature

A. Increases

B. Decreases

C. Remain unaffected

D. May increase or decrease depending on compressor capacity

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4

For slow speed large capacity compressor, following type of valve will be best suited

A. Poppet valve

B. Mechanical valve of the Corliss, sleeve, rotary or semi rotary type

C. Disc or feather type

D. Any of the above

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4

The ratio of workdone per cycle to the stroke volume of the compressor is known as

A. Compressor capacity

B. Compression ratio

C. Compressor efficiency

D. Mean effective pressure

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4

Ratio of indicated h.p. to shaft h.p. in known as

A. Compressor efficiency

B. Isothermal efficiency

C. Volumetric efficiency

D. Mechanical efficiency

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4

In a single acting reciprocating air compressor, without clearance, the compression of air may be

A. Isothermal

B. Polytropic

C. Isentropic

D. Any one of these

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4

The following property is most important for material used for gas turbine blade

A. Toughness

B. Fatigue

C. Creep

D. Corrosion resistance

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4

Propulsive efficiency is defined as ratio of

A. Thrust power and fuel energy

B. Engine output and propulsive power

C. Propulsive power and fuel input

D. Thrust power and propulsive power

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4

The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio)

A. r -1

B. 1 - r -1

C. 1 - (1/r) -1/

D. 1 - (1/r) /-1

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4

For speed above 3000 km/hour, it is more advantageous to use

A. Turbojet engine

B. Ramjet engine

C. Propellers

D. Rockets