They can generate very high thrust
They have high propulsion efficiency
These engines can work on several fuels
They are not air breathing engines
D. They are not air breathing engines
Increase in net output but decrease in thermal efficiency
Increase in thermal efficiency but decrease in net output
Increase in both thermal efficiency and net output
Decrease in both thermal efficiency and net output
Gas turbine
I.C engine
Compressor
Air motor
Standard air
Free air
Compressed air
Compressed air at delivery pressure
It is inefficient
It is bulky
It requires cooling water for its operation
None of the above
Zero
Less
More
Same
Employing intercooler
By constantly cooling the cylinder
By running compressor at very slow speed
By insulating the cylinder
These are used to dampen pulsations
These act as reservoir to take care of sudden demands
These increase compressor efficiency
These knock out some oil and moisture
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
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
r -1
1 - r -1
1 - (1/r) -1/
1 - (1/r) /-1
Constant volume
Constant temperature
Constant pressure
None of these
In two phases
In three phases
In a single phase
In the form of air and water mixture
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
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
Forward curved
Backward curved
Radial
None of these
Radial component
Axial component
Tangential component
None of the above
Large gas turbines employ axial flow compressors
Axial flow compressors are more stable than centrifugal type compressors but not as efficient
Axial flow compressors have high capacity and efficiency
Axial flow compressors have instability region of operation
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
1 : 1.2
1 : 2
1 : 5
1 : 10
Turbojet
Turbo-propeller
Rocket
Ramjet
10 to 40 %
40 to 60 %
60 to 70 %
70 to 90 %
Atmospheric
Slightly more than atmospheric
Slightly less than atmospheric
Pressure slightly less than atmospheric and temperature slightly more than atmospheric
W₁/(W₁ + W₂)
W₂/(W₁ + W₂)
(W₁ + W₂)/W₁
(W₁ + W₂)/W₂
As large as possible
As small as possible
About 50% of swept volume
About 100% of swept volume
Indicated power
Brake power
Frictional power
None of these
Same
Higher
Lower
Dependent on other factors
Stainless steel
High alloy steel
Duralumin
Timken, Haste alloys
Equal to
Less than
More than
None of these
Compressor work and turbine work
Output and input
Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet
Actual compressor work and theoretical compressor work
0.1 to 1.2 m³/s
0.15 to 5 m³/s
Above 5 m³/s
None of these