Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of Space-chord ratio Blade camber Blade camber and incidence angle Blade camber and space-chord ratio Space-chord ratio Blade camber Blade camber and incidence angle Blade camber and space-chord ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In multistage compressor, the isothermal compression is achieved by By constantly cooling the cylinder By running compressor at very slow speed By insulating the cylinder Employing inter-cooler By constantly cooling the cylinder By running compressor at very slow speed By insulating the cylinder Employing inter-cooler ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Losses in a centrifugal compressor are due to All of the listed here Impeller channel losses Inlet losses Diffuser losses All of the listed here Impeller channel losses Inlet losses Diffuser losses ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio in gas turbines Reduces exhaust temperature Improves thermal efficiency Do not damage turbine blades Increases power output Reduces exhaust temperature Improves thermal efficiency Do not damage turbine blades Increases power output ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a centrifugal compressor, the flow of air is ________ to the axis of compressor. Inclined Parallel Perpendicular None of these Inclined Parallel Perpendicular None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In jet engines the products of combustion after passing through the gas turbine are discharged into Vacuum Atmosphere Discharge nozzle Back to the compressor Vacuum Atmosphere Discharge nozzle Back to the compressor ANSWER DOWNLOAD EXAMIANS APP
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