Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of Blade camber and space-chord ratio Blade camber Blade camber and incidence angle Space-chord ratio Blade camber and space-chord ratio Blade camber Blade camber and incidence angle Space-chord ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines It is not possible to use closed gas turbine cycle in aeronautical engines because It is inefficient It is bulky None of these It requires cooling water for its operation It is inefficient It is bulky None of these It requires cooling water for its operation ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency is Reciprocal of compression ratio The ratio of stroke volume to clearance volume Index of compressor performance The ratio of the air actually delivered to the amount of piston displacement Reciprocal of compression ratio The ratio of stroke volume to clearance volume Index of compressor performance The ratio of the air actually delivered to the amount of piston displacement ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum temperature in a gas turbine is 200°C 1000°C 700°C 500°C 200°C 1000°C 700°C 500°C ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 15: 1 50: 1. 30: 1 7: 1 15: 1 50: 1. 30: 1 7: 1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency of a compressor with clearance volume Decreases with increase in compression ratio Increases with increase in compression ratio May increase/decrease depending on compressor capacity In not dependent upon compression ratio Decreases with increase in compression ratio Increases with increase in compression ratio May increase/decrease depending on compressor capacity In not dependent upon compression ratio ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS