(p₁ - p₂)/2
(p₁ + p₂)/2
p₁/p₂
p₁ p₂
D. p₁ p₂
Increases as clearance volume increases
Decreases as clearance volume increases
Is independent of clearance volume
Increases as clearance volume decreases
Mass flow rate
Pressure ratio
Change in load
Stagnation pressure at the outlet
Compressor efficiency
Isentropic efficiency
Euler's efficiency
Pressure coefficient
In the diffuser only
In the impeller only
In the diffuser and impeller
In the inlet guide vanes only
Equal to zero
In the direction of motion of blades
Opposite to the direction of motion of blades
Depending on the velocity
34 %
50 %
60 %
72 %
As large as possible
As small as possible
About 50% of swept volume
About 100% of swept volume
More
Less
Same
Depends on other factors
No propeller
Propeller in front
Propeller at back
Propeller on the top
700°C
2000°C
1500°C
1000°C
Requires less space for installation
Has compressor and combustion chamber
Has less efficiency
All of these
Provides greater flexibility
Provides lesser flexibility
In never used
Is used when gas is to be burnt
The ratio of the discharge pressure to the inlet pressure of air is called compressor efficiency
The compression ratio for the compressor is always greater than unity
The compressor capacity is the ratio of workdone per cycle to the stroke volume
During isothermal compression of air, the workdone in a compressor is maximum
Mechanical efficiency
Volumetric efficiency
Isothermal efficiency
Adiabatic efficiency
Net work output and work done by turbine
Net work output and heat supplied
Work done by turbine and heat supplied
Work done by turbine and net work output
Surrounding air
Compressed atmospheric air
Its own oxygen
None of these
1.03 kg/cm²
1.06 kg/cm²
1.00 kg/cm²
0.53 kg/cm²
Brayton or Atkinson cycle
Carnot cycle
Rankine cycle
Erricson cycle
Brayton or Atkinson cycle
Rankine cycle
Carnot cycle
Erricson cycle
7 : 1
15 : 1
30 : 1
50 : 1.
Equal to
Less than
More than
None of these
Atmospheric conditions at any specific location
20°C and 1 kg/cm² and relative humidity of 36%
0°C and standard atmospheric conditions
15°C and 1 kg/cm²
Less
More
Same
May be less or more depending upon speed
High thermal efficiency
Reduction in compressor work
Decrease of heat loss in exhaust
Maximum work output
Air stream blocking the passage
Motion of air at sonic velocity
Unsteady, periodic and reversed flow
Air stream not able to follow the blade contour
Vacuum
Atmospheric air
Compressed air
Oxygen alone
Lower power consumption per unit of air delivered
Higher volumetric efficiency
Decreased discharge temperature
All of the above
One stroke
Two strokes
Three strokes
Four strokes
A propeller system
Gas turbine engine equipped with a propulsive nozzle and diffuse
Chemical rocket engine
Ramjet engine
10 to 40 %
40 to 60 %
60 to 70 %
70 to 90 %