Compressors, Gas Turbines and Jet Engines The thrust of a jet propulsion power unit can be increased by Injecting water into the compressor All of these Injecting ammonia into the combustion chamber Burning fuel after gas turbine Injecting water into the compressor All of these Injecting ammonia into the combustion chamber Burning fuel after gas turbine ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The pressure ratio for an open cycle gas turbine compared to closed cycle gas turbine of same h.p. is High Low/high depending on make and type Same Low High Low/high depending on make and type Same Low ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a turbo jet engine, subsequent to heat addition to compressed air, to get the power output, the working substance is expanded in Turbine blades, which is essentially an isentropic process Turbine blades, which is a constant volume process Exit nozzle, which is a constant volume process Exit nozzle, which is essentially an isentropic process Turbine blades, which is essentially an isentropic process Turbine blades, which is a constant volume process Exit nozzle, which is a constant volume process Exit nozzle, which is essentially an isentropic process ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The volumetric efficiency of a compressor falls roughly as follows for every 100 m increase in elevation 1.0% 0.5% 5% 0.1% 1.0% 0.5% 5% 0.1% ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines During peak load periods, the best method of controlling compressors is Relief valve Variable speed Start-stop motor Constant speed unloader Relief valve Variable speed Start-stop motor Constant speed unloader ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The exit velocities of exhaust gases are much higher than those in jet engine All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The stagnation conditions exist at the combustion chamber ANSWER DOWNLOAD EXAMIANS APP
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