Compressors, Gas Turbines and Jet Engines The propulsive power of the rocket is (where v₁ = Jet velocity, and v₂ = Aircraft velocity) (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/2g (v₁² -v₂²)/g (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/2g (v₁² -v₂²)/g ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Volumetric efficiency of air compressors is of the order of 60 - 70% 20 - 30% 40 - 50% 70 - 90% 60 - 70% 20 - 30% 40 - 50% 70 - 90% ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the Stator to static enthalpy rise in the stage Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stage Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the stage Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stage Rotor to static enthalpy rise in the stator ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Maximum temperature in a gas turbine is of the order of 1500°C 2000°C 1000°C 700°C 1500°C 2000°C 1000°C 700°C ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A rocket engine for the combustion of its fuel Uses compressed atmospheric air Does not require oxygen Carries its own oxygen Uses surrounding air Uses compressed atmospheric air Does not require oxygen Carries its own oxygen Uses surrounding air ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The axial flow compressor is preferred in aircraft gas turbines because of Higher thrust High pressure rise None of the listed here Low frontal area Higher thrust High pressure rise None of the listed here Low frontal area ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS