Compressors, Gas Turbines and Jet Engines Ratio of compression is the ratio of Pressures at discharge and suction corresponding to same temperature Gauge discharge pressure to the gauge intake pressure Absolute discharge pressure to the absolute intake pressure Stroke volume and clearance volume Pressures at discharge and suction corresponding to same temperature Gauge discharge pressure to the gauge intake pressure Absolute discharge pressure to the absolute intake pressure Stroke volume and clearance volume ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In multistage compressor, the isothermal compression is achieved by Employing inter-cooler By insulating the cylinder By running compressor at very slow speed By constantly cooling the cylinder Employing inter-cooler By insulating the cylinder By running compressor at very slow speed By constantly cooling the cylinder ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A compressor mostly used for supercharging of I.C. engines is Radial flow compressor Reciprocating compressor Roots blower Axial flow compressor Radial flow compressor Reciprocating compressor Roots blower Axial flow compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is Can't be compared Equal Lower Higher Can't be compared Equal Lower Higher ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The air power of the compressor is also known as Brake power None of these Frictional power Indicated power Brake power None of these Frictional power Indicated power ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The exit velocities of exhaust gases are much higher than those in jet engine All of these 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 The exit velocities of exhaust gases are much higher than those in jet engine All of these 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 ANSWER DOWNLOAD EXAMIANS APP
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