Compressors, Gas Turbines and Jet Engines The pressure ratio in gas turbines is of the order of 2.5423611111111 0.37569444444444 0.084027777777778 0.16736111111111 2.5423611111111 0.37569444444444 0.084027777777778 0.16736111111111 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 Vacuum Compressed air Atmospheric air Oxygen alone Vacuum Compressed air Atmospheric air Oxygen alone ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines There is a certain pressure ratio (optimum) for a gas turbine at which its thermal efficiency is maximum. With increase in turbine temperature, the value of pressure ratio for the peak efficiency would Remain same Decrease Increase None of these Remain same Decrease Increase None of these 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 The volumetric efficiency for reciprocating air compressors is about 40 to 60% 60 to 70% 10 to 40% 70 to 90% 40 to 60% 60 to 70% 10 to 40% 70 to 90% ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Stalling of blades in axial flow compressor is the phenomenon of Air stream blocking the passage Air stream not able to follow the blade contour Unsteady periodic and reversed flow Motion of air at sonic velocity Air stream blocking the passage Air stream not able to follow the blade contour Unsteady periodic and reversed flow Motion of air at sonic velocity ANSWER DOWNLOAD EXAMIANS APP
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