Compressors, Gas Turbines and Jet Engines The thermal efficiency of a gas turbine as compared to a diesel plant is Less Same Depends on other factors More Less Same Depends on other factors More ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Turbofan engine employs Two or more air streams One air stream No air stream Solid fuel firing Two or more air streams One air stream No air stream Solid fuel firing ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The work ratio of simple gas turbine cycle depends on Pressure ratio All of these Minimum cycle temperature Maximum cycle temperature Pressure ratio All of these Minimum cycle temperature Maximum cycle temperature ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency of a compressor with clearance volume Increases with increase in compression ratio In not dependent upon compression ratio Decreases with increase in compression ratio May increase/decrease depending on compressor capacity Increases with increase in compression ratio In not dependent upon compression ratio Decreases with increase in compression ratio May increase/decrease depending on compressor capacity ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines During peak load periods, the best method of controlling compressors is Constant speed unloader Variable speed Relief valve Start-stop motor Constant speed unloader Variable speed Relief valve Start-stop motor 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 All of these 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 The stagnation conditions exist at the combustion chamber All of these 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 ANSWER DOWNLOAD EXAMIANS APP
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