SECTION-2

COMPRESSORS, GAS TURBINES AND JET ENGINES MCQ

 
Q51.The power input factor varies from

(a) 0.8 to 0.9
(b) 0.5 to 0.8
(c) 1.035 to 1.04
(d) 1.1 to 1.5.

Ans:(c) 1.035 to 1.04

 

Q52. The ratio of enthalpy rise in rotor to enthalpy rise in stage is called

(a) adiabatic efficiency
(b) degree of reaction
(c) static pressure ratio
(d) none of the above.

Ans:(b) degree of reaction
 

 

Q53. For minimum fluid friction and blade tip clearance losses, the blades of an axial flow compressor are designed for

(a) 80% reaction
(b) 60% reaction
(c) 50% reaction
d) 40% reaction.

Ans:(c) 50% reaction

 

Q54. The frontal area for a centrifugal compressor as compared to axial flow compressor is

(a) large
(b) same
(c) small
(d) none of the above.

Ans:(a) large

 

Q55. In axial flow compressor, stalling of blades is the phenomenon of

(a) air steam not able to follow the blade contour
(b) air stream blocking the passage
(c) air stream flowing with sonic velocity
(d) none of the above.

Ans:(a) air steam not able to follow the blade contour

 

Q56. In multi-stage compressors, intercooling is done to

(a) minimise the work of compression
(b) cool the air
(c) reduce the volume of air
(d) none of the above.

Ans:(a) minimise the work of compression

 

Q57. The use of after cooler is to

(a) minimise the work of compression
(b) cool the air
(c) reduce the volume of air
(d) none of the above.

Ans: (b) cool the air

 

Q58. Centrifugal blowers are used to supply

(a) small volume of air at low pressure
(b) small volume of air at high pressure
(c) large volume of air at low pressure
(d) large volume of air at high pressure.

Ans:(c) large volume of air at low pressure

 

Q59. The blades of compressor have profiles consisting of

(a) circular arcs
(b) straight lines
(c) aerofoil section
(d) none of the above.

Ans:(c) aerofoil section

 

Q60. Degree of reaction for an axial flow compressor is also equal to

(a) ratio of increase in pressure in rotor to total increase in pressure in the stage
(b) ratio of total increase in pressure in the stage to increase in pressure in rotor
(c) product of pressure in rotor and pressure in the stage
(d) none of the above.

Ans:(a) ratio of increase in pressure in rotor to total increase in pressure in the stage

 

 
 

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Each section contains maximum 80 Questions. To practice more questions visit other sections.
 
Compressors, Gas turbines and Jet Engines – Section-1
 
Compressors, Gas turbines and Jet Engines – Section-2
 
Compressors, Gas turbines and Jet Engines – Section-3
 


 


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