Ratio of shaft output of the air motor to the shaft input to the compressor
Ratio of shaft input to the compressor to the shaft output of air motor
Product of shaft output of air motor and shaft input to the compressor
None of the above
A. Ratio of shaft output of the air motor to the shaft input to the compressor
Compressor efficiency
Volumetric efficiency
Isothermal efficiency
Mechanical efficiency
Isothermally
Polytropically
Isentropically
None of these
Zero
Less
More
Same
The reciprocating compressors are best suited for high pressure and low volume capacity
The effect of clearance volume on power consumption is negligible for the same volume of discharge
Both (A) and (B)
None of these
Compressor efficiency
Isentropic efficiency
Euler's efficiency
Pressure coefficient
Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio
Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor
Volume of free air delivery per stroke to the swept volume of the piston
Isentropic power to the power required to drive the compressor
Highly heated atmospheric air
Solids
Liquid
Plasma
Centrifugal compressor
Axial compressor
Pumps
All of the above
0.5 kg
1.0 kg
1.3 kg
2.2 kg
p₂ = p₁ × p₃
p₂ = p₁/p₃
p₂ = p₁ × p₂
p₂ = p₃/p₁
10 bar
20 bar
30 bar
50 bar
Reciprocating compressor
Centrifugal compressor
Axial flow compressor
Turbo compressor
High calorific value
Ease of atomisation
Low freezing point
Both (A) and (C) above
They can generate very high thrust
They have high propulsion efficiency
These engines can work on several fuels
They are not air breathing engines
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
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
The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel
The stagnation conditions exist at the combustion chamber
The exit velocities of exhaust gases are much higher than those in jet engine
All of the above
Radial flow compressors
Axial flow compressors
Pumps
All of these
Vi = Vo
Vt > Vo
U < Vo
V = Uo
Less
More
Same
May be less or more depending upon speed
Large quantity of air at high pressure
Small quantity of air at high pressure
Small quantity of air at low pressure
Large quantity of air at low pressure
kg/m²
kg/m³
m³/min
m³/kg
Conversion of pressure energy into kinetic energy
Conversion of kinetic energy into pressure energy
Centripetal action
Generating pressure directly
Decreases
Increases
Does not change
None of these
Gas turbine is a self starting unit
Gas turbine does not require huge quantity of water like steam plant
Exhaust losses in gas turbine are high due to large mass flow rate
Overall efficiency of gas turbine plant is lower than that of a reciprocating engine
Radial flow
Axial flow
Centrifugal
None of the above
Increases with increase in compression ratio
Decreases with increase in compression ratio
In not dependent upon compression ratio
May increase/decrease depending on compressor capacity
Back pressure
Critical pressure
Discharge pressure
None of these
Same
More
Less
Depends on other factors
As large as possible
As small as possible
About 50% of swept volume
About 100% of swept volume