Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Pick up the wrong statement about advantages of multistage compression More loss of air due to leakage past the cylinder Air can be cooled perfectly in between Mechanical balance is better Better lubrication is possible advantages of multistage More loss of air due to leakage past the cylinder Air can be cooled perfectly in between Mechanical balance is better Better lubrication is possible advantages of multistage ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The gas in cooling chamber of a closed cycle gas turbine is cooled at Constant volume None of the listed here Constant temperature Constant pressure Constant volume None of the listed here Constant temperature Constant pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thrust on the rotor in a centrifugal compressor is produced by None of these Radial component Tangential component Axial component None of these Radial component Tangential component Axial component ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Rotary compressors are suitable for Low discharge at high pressure Large discharge at low pressure Large discharge at high pressure Low discharge at low pressure Low discharge at high pressure Large discharge at low pressure Large discharge at high pressure Low discharge at low pressure 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 Rotor to static enthalpy rise in the stage Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the rotor Stator to static enthalpy rise in the stage Rotor to static enthalpy rise in the stage Rotor to static enthalpy rise in the stator Stator to static enthalpy rise in the rotor ANSWER DOWNLOAD EXAMIANS APP
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