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
B. Two adiabatic and two isobaric
Remain same
Decrease
Increase
None of the above
Closed cycle gas turbine is an I.C engine
Gas turbine uses same working fluid over and over again
Ideal efficiency of closed cycle gas turbine plant is more than Carnot cycle efficiency
Thrust in turbojet is produced by nozzle exit gases.
Brayton or Atkinson cycle
Rankine cycle
Carnot cycle
Erricson cycle
W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1)
W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1)
W₁/W₂ = n₁/n₂
W₁/W₂ = n₂/n₁
Mechanical efficiency
Volumetric efficiency
Isothermal efficiency
Adiabatic efficiency
Forward curved
Backward curved
Radial
None of these
To cool the air during compression
To cool the air at delivery
To enable compression in two stages
To minimise the work of compression
20 - 30 %
40 - 50 %
60 - 70 %
70 - 90 %
Turbojet
Turbo-propeller
Rocket
Ramjet
Equal to
Less than
Greater than
None of these
More
Less
Same
Depends on other factors
Reciprocating compressor
Centrifugal compressor
Axial flow compressor
Turbo compressor
Electric motor
Engine
Either (A) or (B)
None of these
In the diffuser only
In the impeller only
In the diffuser and impeller
In the inlet guide vanes only
Thrust power and fuel energy
Engine output and propulsive power
Propulsive power and fuel input
Thrust power and propulsive power
Same
One-half
One fourth
One sixth
It allows maximum compression to be achieved
It greatly affects volumetric efficiency
It results in minimum work
It permits isothermal compression
Before intercooler
After intercooler
After receiver
Between after-cooler and air receiver
Increase
Decrease
Remain same
May increase or decrease depending on clearance volume
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
Pressure ratio
Pressure coefficient
Degree of reaction
Slip factor
There is no pressure drop in the intercooler
The compression in both the cylinders is polytropic
The suction and delivery of air takes place at constant pressure
All of the above
Blade camber
Blade camber and incidence angle
Spacechord ratio
Blade camber and spacechord ratio
1
1.2
1.3
1.4
Same
Higher
Lower
Dependent on other factors
Adding heat exchanger
Injecting water in/around combustion chamber
Reheating the air after partial expansion in the turbine
All of the above
Temperature during compression remains constant
No heat leaves or enters the compressor cylinder during compression
Temperature rise follows a linear relationship
Work done is maximum
Low frontal area
Higher thrust
High pressure rise
None of these
Work done in first stage should be more
Work done in subsequent stages should increase
Work done in subsequent stages should decrease
Work done in all stages should be equal
Higher
Lower
Same
None of the above