Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 50: 1. 15: 1 30: 1 7: 1 50: 1. 15: 1 30: 1 7: 1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Reheating in multistage expansion gas turbine results in High thermal efficiency Maximum work output Reduction in compressor work Decrease of heat loss in exhaust High thermal efficiency Maximum work output Reduction in compressor work Decrease of heat loss in exhaust ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Inter cooling in compressors Enables compression in two stages Results in saving of power in compressing a given volume to given pressure Cools the delivered air Is the standard practice for big compressors Enables compression in two stages Results in saving of power in compressing a given volume to given pressure Cools the delivered air Is the standard practice for big compressors ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines When the temperature of air leaving the inter-cooler, in a two stage compression with inter-cooler, is ________ the original atmospheric air temperature, then the intercooling is known as perfect or complete intercooling. More than Less than None of these Equal to More than Less than None of these Equal to ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the aircraft propellers The propulsive matter is caused to flow around the propelled body Propulsive matter is ejected from within the propelled body Its functioning does not depend on presence of air All of these The propulsive matter is caused to flow around the propelled body Propulsive matter is ejected from within the propelled body Its functioning does not depend on presence of air All of these 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 All of these The exit velocities of exhaust gases are much higher than those in jet engine 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 All of these The exit velocities of exhaust gases are much higher than those in jet engine The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel ANSWER DOWNLOAD EXAMIANS APP
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