Compressors, Gas Turbines and Jet Engines The air power of the compressor is also known as None of these Frictional power Indicated power Brake power None of these Frictional power Indicated power Brake power ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In jet propulsion power unit, the inlet duct of diverging shape is used in order to Collect more air Beautify the shape Provide robust structure Convert kinetic energy of air into pressure energy Collect more air Beautify the shape Provide robust structure Convert kinetic energy of air into pressure energy ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The ratio of the indicated power to the shaft power or brake power of the motor or engine required to drive the compressor, is called Isothermal efficiency Compressor efficiency Mechanical efficiency Volumetric efficiency Isothermal efficiency Compressor efficiency Mechanical efficiency Volumetric efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency of a compressor without clearance volume Increases with increase in compression ratio Is not dependent upon compression ratio Decreases with increase in compression ratio May increase/decrease depending on compressor capacity Increases with increase in compression ratio Is 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 Axial flow compressor resembles Turbine Reciprocating pump Centrifugal pump Sliding vane compressor Turbine Reciprocating pump Centrifugal pump Sliding vane compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber All of these ANSWER DOWNLOAD EXAMIANS APP
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