Compressors, Gas Turbines and Jet Engines The ideal efficiency of simple gas turbine cycle depends on Minimum cycle temperature All of these Maximum cycle temperature Pressure ratio Minimum cycle temperature All of these Maximum cycle temperature Pressure ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For supplying intermittent small quantity of air at high pressure, following compressor is best suited Screw Axial Centrifugal Reciprocating Screw Axial Centrifugal Reciprocating ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a centrifugal compressor, an increase in speed at a given pressure ratio causes Increase in efficiency Increase in flow Increase in flow and decrease in efficiency Decrease in flow Increase in efficiency Increase in flow Increase in flow and decrease in efficiency Decrease in flow ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For perfect intercooling in a three stage compressor p₁ p₂ = p₃ p₄ p₁ p₃ = p₂ p₄ p₂/p₁ = p₃/p₂ = p₄/p₃ p₃/p₁ = p₄/p₂ p₁ p₂ = p₃ p₄ p₁ p₃ = p₂ p₄ p₂/p₁ = p₃/p₂ = p₄/p₃ p₃/p₁ = p₄/p₂ 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 Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stage Stator to static enthalpy rise in the stage Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stage Stator to static enthalpy rise in the stage ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS