COMPRESSORS, GAS TURBINES AND JET ENGINES MCQ

SECTION-1

 

Q51. Maximum work is done in compressing air when the compression is

(a) isothermal

(b) adiabatic

(c) polytropic

(d) any one of the above

Ans: (b) adiabatic

Q52. Isothermal compression efficiency, even when running at high speed, can be approached by using

(a) multi-stage compression

(b) cold water spray

(c) both (a) and (b) above

(d) fully insulating the cylinder

Ans: (c) both (a) and (b) above

Q53.  An ideal air compressor cycle with clearance on p-v diagram can be represented by following processes

(a) one adiabatic, two isobaric, and one constant volume

(b) two adiabatic and two isobaric

(c) two adiabatic, one isobaric and one constant volume,

(d) one adiabatic, one isobaric and two constant volume

Ans: (b) two adiabatic and two isobaric

Q54. Cylinder clearance in a compressor should be

(a) as large as possible

(b) as small as possible

(c) about 50% of swept volume

(d) about 100% of swept volume

Ans: (b) as small as possible

Q55. The clearance volume of the air compressor is kept minimum because

(a) it allows maximum compression to be achieved

(b) it greatly affects volumetric efficiency

(c) it results in minimum work

(d) it permits isothermal compression

Ans: (b) it greatly affects volumetric efficiency

 

Q56. Choose the correct statement

(a) In gas turbine, the maximum combustion pressure is more than that of an I.C. engine. 
(b) Low weight and small frontal area are the requirements for a gas turbine to be used in aircrafts. 
(c) Gas turbine blades are given a rake opposite to the direction of motion of blades. 
(d) The pressure ratio in gas turbine is of the order of 10 : 1.

Ans:(b) Low weight and small frontal area are the requirements for a gas turbine to be used in aircrafts.

 

Q57. The air fuel ratio in a jet engine is

(a) 10 : 1 
(b) 40 : 1 
(c) 60 : 1 
(d) 90 : 1. 

Ans:(c) 60 : 1

 

Q58. In rocket propulsion, the oxygen for combustion of its fuel is

(a) taken from surrounding air 
(b) taken from the rocket itself 
(c) taken from compressed atmospheric air 
(d) none of the above. 

Ans:(b) taken from the rocket itself 

 

Q59. In jet propulsion, the oxygen for combustion of the fuel is

(a) taken from surrounding air 
(b) taken from the aircraft itself 
(c) taken from compressed atmospheric air 
(d) none of the above.

Ans:(a) taken from surrounding air

 

Q60. The thermal efficiency of a gas turbine cycle with regenerator increases with

(a) the increase of pressure ratio 
(b) the decrease of pressure ratio 
(c) constant pressure ratio 
(d) none of the above.

Ans:(b) the decrease of pressure ratio

 

 

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Read More Sections of Compressors, Gas turbines and Jet Engines

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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