Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 15: 1 50: 1. 7: 1 30: 1 15: 1 50: 1. 7: 1 30: 1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of compressor is defined as the ratio of Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Work to compress air isothermally to work for actual compression Isothermal h.p. to adiabatic h.p. Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Work to compress air isothermally to work for actual compression Isothermal h.p. to adiabatic h.p. ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The effective power of gas turbines is increased by adding the following in compressor Hydrogen Ammonia and water vapour Nitrogen Carbon dioxide Hydrogen Ammonia and water vapour Nitrogen Carbon dioxide ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Stalling of blades in axial flow compressor is the phenomenon of Air stream blocking the passage Unsteady periodic and reversed flow Motion of air at sonic velocity Air stream not able to follow the blade contour Air stream blocking the passage Unsteady periodic and reversed flow Motion of air at sonic velocity Air stream not able to follow the blade contour ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? 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 All of these 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 a constant volume process Exit nozzle, which is essentially an isentropic process Turbine blades, which is essentially an isentropic process Exit nozzle, which is a constant volume process Turbine blades, which is a constant volume process Exit nozzle, which is essentially an isentropic process Turbine blades, which is essentially an isentropic process Exit nozzle, which is a constant volume process ANSWER DOWNLOAD EXAMIANS APP
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