Compressors, Gas Turbines and Jet Engines The maximum compression ratio in an actual single stage axial flow compressor is of the order of 0.045138888888889 0.00070833333333333 0.043055555555556 0.048611111111111 0.045138888888889 0.00070833333333333 0.043055555555556 0.048611111111111 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency is The ratio of stroke volume to clearance volume Reciprocal of compression ratio The ratio of the air actually delivered to the amount of piston displacement Index of compressor performance The ratio of stroke volume to clearance volume Reciprocal of compression ratio The ratio of the air actually delivered to the amount of piston displacement Index of compressor performance ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the axial flow gas turbine, the work ratio is the ratio of 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 Compressor work and turbine work Actual compressor work and theoretical compressor work ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In jet engines, for the efficient production of large power, fuel is burnt in an atmosphere of Atmospheric air Compressed air Oxygen alone Vacuum Atmospheric air Compressed air Oxygen alone Vacuum 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 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 Collect more air ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The hottest point in a gas turbine is at the tip at the base between ~ to i of the blade height in the center at the tip at the base between ~ to i of the blade height in the center ANSWER DOWNLOAD EXAMIANS APP
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