Compressors, Gas Turbines and Jet Engines
In the axial flow gas turbine, the work ratio is the ratio of

Compressor work and turbine work
Actual compressor work and theoretical compressor work
Output and input
Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet

ANSWER DOWNLOAD EXAMIANS APP

Compressors, Gas Turbines and Jet Engines
Which of the following statement is correct relating to rocket engines?

The stagnation conditions exist at the combustion chamber
The exit velocities of exhaust gases are much higher than those in jet engine
The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel
All of these

ANSWER DOWNLOAD EXAMIANS APP