Compressors, Gas Turbines and Jet Engines During peak load periods, the best method of controlling compressors is Constant speed unloader Start-stop motor Variable speed Relief valve Constant speed unloader Start-stop motor Variable speed Relief valve ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Propulsive efficiency is defined as ratio of Propulsive power and fuel input Engine output and propulsive power Thrust power and propulsive power Thrust power and fuel energy Propulsive power and fuel input Engine output and propulsive power Thrust power and propulsive power Thrust power and fuel energy ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Cylinder clearance in a compressor should be As small as possible About 100% of swept volume About 50% of swept volume As large as possible As small as possible About 100% of swept volume About 50% of swept volume As large as possible ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of compressor is defined as the ratio of Isothermal h.p. to the BHP of motor Isothermal h.p. to adiabatic h.p. Work to compress air isothermally to work for actual compression Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Isothermal h.p. to adiabatic h.p. Work to compress air isothermally to work for actual compression Power to drive compressor to isothermal h.p. ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? 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 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 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 7: 1 30: 1 15: 1 50: 1. 7: 1 30: 1 15: 1 50: 1. ANSWER DOWNLOAD EXAMIANS APP
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