Compressor pressure ratio
Highest pressure to exhaust pressure
Inlet pressure to exhaust pressure
Pressures across the turbine
B. Highest pressure to exhaust pressure
One adiabatic, two isobaric, and one constant volume
Two adiabatic and two isobaric
Two adiabatic, one isobaric and one constant volume
One adiabatic, one isobaric and two constant volumes
Isothermal H.P/indicated H.R
Isothermal H.P./shaft H.R
Total output/air input
Compression work/motor input
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
Low speeds
High speeds
Low altitudes
High altitudes
Collect more air
Convert kinetic energy of air into pressure energy
Provide robust structure
Beautify the shape
In a two stage reciprocating air compressor with complete intercooling, maximum work is saved.
The minimum work required for a two stage reciprocating air compressor is double the work required for each stage.
The ratio of the volume of free air delivery per stroke to the swept volume of the piston is called volumetric efficiency.
None of the above
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
Atmospheric
Slightly more than atmospheric
Slightly less than atmospheric
Pressure slightly less than atmospheric and temperature slightly more than atmospheric
Equal to
Less than
More than
None of these
Employing intercooler
By constantly cooling the cylinder
By running compressor at very slow speed
By insulating the cylinder
Lower power consumption per unit of air delivered
Higher volumetric efficiency
Decreased discharge temperature
All of the above
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
Radial component
Axial component
Tangential component
None of the above
10 bar
20 bar
30 bar
50 bar
Centrifugal compressor
Axial compressor
Pumps
All of the above
700°C
2000°C
1500°C
1000°C
N.T.P. conditions
Intake temperature and pressure conditions
0°C and 1 kg/cm²
20°C and 1 kg/cm²
Start-stop motor
Constant speed unloader
Relief valve
Variable speed
Turbojet engine
Ramjet engine
Propellers
Rockets
Thrust power and fuel energy
Engine output and propulsive power
Propulsive power and fuel input
Thrust power and propulsive power
Isothermal
Polytropic
Isentropic
Any one of these
0.1 to 1.2 m³/s
0.15 to 5 m³/s
Above 5 m³/s
None of these
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
p₂/p₁ = p₃/p₂
p₁/p₃ = p₂/p₁
p₁ = p₃
p₁ = p₂ p₃
One air stream
Two or more air streams
No air stream
Solid fuel firing
1 bar
16 bar
64 bar
256 bar
Increases the thermal efficiency
Increases the compressor work
Increases the turbine work
Decreases the thermal efficiency
Remain same
Decrease
Increase
None of the above
Brayton or Atkinson cycle
Rankine cycle
Carnot cycle
Erricson cycle
Single stage compression
Multistage compression without intercooling
Multistage compression with intercooling
None of these