Single stage compression
Multistage compression without intercooling
Multistage compression with intercooling
None of these
C. Multistage compression with intercooling
Decreasing the compression work
Increasing the compression work
Increasing the turbine work
Both (A) and (C) above
Diffuser inlet radius
Diffuser outlet radius
Impeller inlet radius
Impeller outlet radius
Centrifugal type
Axial flow type
Radial flow type
None of these
Adding heat exchanger
Injecting water in/around combustion chamber
Reheating the air after partial expansion in the turbine
All of the above
It requires very big cylinder
It does not increase pressure much
It is impossible in practice
Compressor has to run at very slow speed to achieve it
0.1 bar and 20°C
1 bar and 20°C
0.1 bar and 40°C
1 bar and 40°C
It is inefficient
It is bulky
It requires cooling water for its operation
None of the above
Radial flow compressor
Axial flow compressor
Roots blower
Reciprocating compressor
Backward curved blades has poor efficiency
Backward curved blades lead to stable performance
Forward curved blades has higher efficiency
Forward curved blades produce lower pressure ratio
1 - k + k (p₁/p₂)1/n
1 + k - k (p₂/p₁)1/n
1 - k + k (p₁/p₂) n- 1/n
1 + k - k (p₂/p₁) n-1/n
Provides greater flexibility
Provides lesser flexibility
In never used
Is used when gas is to be burnt
One air stream
Two or more air streams
No air stream
Solid fuel firing
Gas turbine plant
Petrol engine
Diesel engine
Solar plant
Atmosphere
Vacuum
Discharge nozzle
Back to the compressor
Same
More
Less
Depends on other factors
Isothermal H.P/indicated H.R
Isothermal H.P./shaft H.R
Total output/air input
Compression work/motor input
p₂/p₁ = p₃/p₂
p₁/p₃ = p₂/p₁
p₁ = p₃
p₁ = p₂ p₃
Atmospheric conditions at any specific location
20°C and 1 kg/cm² and relative humidity 36%
0°C and standard atmospheric conditions
15°C and 1 kg/cm²
Gas turbine uses low air-fuel ratio to economise on fuel
Gas turbine uses high air-fuel ratio to reduce outgoing temperature
Gas turbine uses low air-fuel ratio to develop the high thrust required
All of the above
High calorific value
Ease of atomisation
Low freezing point
Both (A) and (C) above
The flow of air is parallel to the axis of the compressor
The static pressure of air in the impeller increases in order to provide centripetal force on the air
The impeller rotates at high speeds
The maximum efficiency is higher than multistage axial flow compressors
Increases the thermal efficiency
Increases the compressor work
Increases the turbine work
Decreases the thermal efficiency
Increases
Decreases
Remain constant
First decreases and then increases
To cool the air during compression
To cool the air at delivery
To enable compression in two stages
To minimise the work of compression
Equal to
Less than
More than
None of these
20 - 30 %
40 - 50 %
60 - 70 %
70 - 90 %
Atmosphere
Back to the compressor
Discharge nozzle
Vacuum
Turbojet
Turbo-propeller
Rocket
Ramjet
No propeller
Propeller in front
Propeller at back
Propeller on the top
It has high propulsive efficiency at high speeds
It can fly at supersonic speeds
It can fly at high elevations
It has high power for take off