COMPRESSORS, GAS TURBINES AND JET ENGINES MCQ

SECTION-1

 

Q71. Axial flow compressor has the following advantage over centrifugal compressor

(a) larger air handling ability per unit frontal area

(b) higher pressure ratio per stage

(c) aerofoil blades are used

(d) higher average velocities

Ans: (a) larger air handling ability per unit frontal area

Q72. 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

Ans: (d) air stream not able to follow the blade contour

Q73. The fuel consumption in gas turbines is accounted for by

(a) lower heating value

(b) higher heating value

(c) heating value

(d) higher calorific value

Ans: (a) lower heating value

Q74. The pressure ratio in gas turbines is of the order of

(a) 2:1

(b) 4:1

(c) 61: 1

(d) 9 : 1

Ans: (c) 61: 1

Q75. The material commonly used for air craft gas turbine is

(a) stainless steel

(b) high alloy’ steel

(c) duralumin

(d) Timken, Haste and Inconel alloys

Ans: (d) Timken, Haste and Inconel alloys

 

Q76. In a gas turbine, the maximum temperature is

(a) 2000°C 
(b) 1000°C 
(c) 700°C 
(d) 200°C. 

Ans:(c) 700°C

 

Q77. In the air after practical expansion in the turbine is reheated, the efficiency of the gas turbine cycle

(a) decreases 
(b) increases 
(c) remains constant 
(d) first increases then decreases.

Ans:(b) increases

 

Q78. The thermal efficiency of a gas turbine with regenerator is maximum when pressure ratio is

(a) less than 1.3 
(b) more than 1.0 
(c) equal to 1.0 
(d) zero. 

Ans:(c) equal to 1.0

 

Q79. When the pressure ratio is equal to 1.0, the thermal efficiency of a gas turbine with regenerator is

(a) less than Carnot cycle 
(b) more than Carnot cycle 
(c) equal to Carnot cycle 
(d) none of the above.

Ans:(c) equal to Carnot cycle

 

Q80. The power produced in kW/ton for a steam plant is

(a) 140 
(b) 27 
(c) 10 
(d) 50.

Ans:(c) 10

 

 

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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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