Compressors, Gas Turbines and Jet Engines The process, which causes the air to enter the impeller blades of a centrifugal compressor at ________ velocity (without effecting the mass of air to flow and velocity of flow) is known as prewhirl. Reduced Zero Increased None of these Reduced Zero Increased None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For a two stage compressor, if index of compression for higher stage is greater than index of compression for lower stage, then the optimum pressure as compared to ideal case will Decrease Increase Remain unaffected Other factors control it Decrease Increase Remain unaffected Other factors control it ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio in gas turbines Improves thermal efficiency Increases power output Do not damage turbine blades Reduces exhaust temperature Improves thermal efficiency Increases power output Do not damage turbine blades Reduces exhaust temperature ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the axial flow gas turbine, the work ratio is the ratio of Actual compressor work and theoretical compressor work Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Compressor work and turbine work Output and input Actual compressor work and theoretical compressor work Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Compressor work and turbine work Output and input 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
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