3 m³/ mt.
1.5 m³/ mt.
18 m³/ mt.
6 m³/ mt.
A. 3 m³/ mt.
Increase temperature
Reduce turbine size
Increase power output
Increase speed
Low speeds
High speeds
Low altitudes
High altitudes
Turbojet
Turbo-propeller
Rocket
Ramjet
Isothermal compression
Isentropic compression
Polytropic compression
None of these
Back pressure
Critical pressure
Discharge pressure
None of these
Decreasing the compression work
Increasing the compression work
Increasing the turbine work
Both (A) and (C) above
Compressor efficiency
Isentropic efficiency
Euler's efficiency
Pressure coefficient
Pulsejet requires no ambient air for propulsion
Ramjet engine has no turbine
Turbine drives compressor in a Turbojet
Bypass turbojet engine increases the thrust without adversely affecting, the propulsive efficiency and fuel economy
High h.p. and low weight
Low weight and small frontal area
Small frontal area and high h.p.
High speed and high h.p
Diffuser inlet radius
Diffuser outlet radius
Impeller inlet radius
Impeller outlet radius
Adding heat exchanger
Injecting water in/around combustion chamber
Reheating the air after partial expansion in the turbine
All of the above
Equal to
Less than
More than
None of these
Constant volume
Constant temperature
Constant pressure
None of these
Free air delivery
Compressor capacity
Swept volume
None of these
Isothermal
Adiabatic
Polytropic
None of the above
No flow of air
Fixed mass flow rate regardless of pressure ratio
Reducing mass flow rate with increase in pressure ratio
Increased inclination of chord with air steam
The ratio of stroke volume to clearance volume
The ratio of the air actually delivered to the amount of piston displacement
Reciprocal of compression ratio
Index of compressor performance
Pressure ratio
Maximum cycle temperature
Minimum cycle temperature
All of the above
Remove impurities from air
Reduce volume of air
Cause moisture and oil vapour to drop out
Cool the air
Less power requirement
Better mechanical balance
Less loss of air due to leakage past the cylinder
Lower volumetric efficiency
In gas turbine plants
For operating pneumatic drills
In starting and supercharging of I.C. engines
All of the above
7 : 1
15 : 1
30 : 1
50 : 1.
The compression ratio in each stage should be same
The intercooling should be perfect
The workdone in each stage should be same
All of the above
Stainless steel
High alloy steel
Duralumin
Timken, Haste alloys
In two phases
In three phases
In a single phase
In the form of air and water mixture
Compression index
Compression ratio
Compressor efficiency
Mean effective pressure
3 m³/ mt.
1.5 m³/ mt.
18 m³/ mt.
6 m³/ mt.
Is self operating at zero flight speed
Is not self operating at zero flight speed
Requires no air for its operation
Produces a jet consisting of plasma
Paucity of O2
Increasing gas temperature
High specific volume
High friction losses
Mechanical efficiency
Volumetric efficiency
Isothermal efficiency
Adiabatic efficiency