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 Other factors control it Remain unaffected Decrease Increase Other factors control it Remain unaffected ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio in gas turbines Reduces exhaust temperature Increases power output Do not damage turbine blades Improves thermal efficiency Reduces exhaust temperature Increases power output Do not damage turbine blades Improves thermal efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the axial flow gas turbine, the work ratio is the ratio of Compressor work and turbine work Actual compressor work and theoretical compressor work Output and input Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Compressor work and turbine work Actual compressor work and theoretical compressor work Output and input Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet 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 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 All of these ANSWER DOWNLOAD EXAMIANS APP
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