Compressors, Gas Turbines and Jet Engines The compression ratio in a gas turbine is of the order of 0.20902777777778 0.50069444444444 3.5 : 1 0.33402777777778 0.20902777777778 0.50069444444444 3.5 : 1 0.33402777777778 ANSWER DOWNLOAD EXAMIANS APP
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 0.043055555555556 0.00070833333333333 0.048611111111111 0.045138888888889 0.043055555555556 0.00070833333333333 0.048611111111111 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The volumetric efficiency of compressor with increase in compression ratio will Increase Remain same May increase or decrease depending on clearance volume Decrease Increase Remain same May increase or decrease depending on clearance volume Decrease ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The pressure and temperature conditions of air at the suction of compressor are Slightly less than atmospheric Atmospheric Pressure slightly less than atmospheric and temperature slightly more than atmospheric Slightly more than atmospheric Slightly less than atmospheric Atmospheric Pressure slightly less than atmospheric and temperature slightly more than atmospheric Slightly more than atmospheric ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A rocket engine for the combustion of its fuel Does not require oxygen Uses compressed atmospheric air Uses surrounding air Carries its own oxygen Does not require oxygen Uses compressed atmospheric air Uses surrounding air Carries its own oxygen ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of Blade camber Blade camber and space-chord ratio Space-chord ratio Blade camber and incidence angle Blade camber Blade camber and space-chord ratio Space-chord ratio Blade camber and incidence angle ANSWER DOWNLOAD EXAMIANS APP
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