Compressors, Gas Turbines and Jet Engines Stalling of blades in axial flow compressor is the phenomenon of Air stream not able to follow the blade contour Motion of air at sonic velocity Air stream blocking the passage Unsteady periodic and reversed flow Air stream not able to follow the blade contour Motion of air at sonic velocity Air stream blocking the passage Unsteady periodic and reversed flow ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The advantage of multistage compression over single stage compression is Decreased discharge temperature All of these Higher volumetric efficiency Lower power consumption per unit of air delivered Decreased discharge temperature All of these Higher volumetric efficiency Lower power consumption per unit of air delivered ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines An after-cooler is used to Cause moisture and oil vapour to drop out Reduce volume of air Cool the air Remove impurities from air Cause moisture and oil vapour to drop out Reduce volume of air Cool the air Remove impurities from air ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thermodynamic efficiency of rotary compressor is based on Polytropic compression Isentropic compression Isothermal compression Adiabatic compression Polytropic compression Isentropic compression Isothermal compression Adiabatic compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The work ratio of a gas turbine plant is defined as the ratio of Net work output and isentropic heat drop Net work output and heat supplied Net work output and work done by turbine Actual heat drop and isentropic heat drop Net work output and isentropic heat drop Net work output and heat supplied Net work output and work done by turbine Actual heat drop and isentropic heat drop ANSWER DOWNLOAD EXAMIANS APP
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