Compressors, Gas Turbines and Jet Engines The work ratio of a gas turbine plant is defined as the ratio of Actual heat drop and isentropic heat drop Net work output and work done by turbine Net work output and isentropic heat drop Net work output and heat supplied Actual heat drop and isentropic heat drop Net work output and work done by turbine Net work output and isentropic heat drop Net work output and heat supplied ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compressor capacity with decrease in suction temperature Remain unaffected Increases May increase or decrease depending on compressor capacity Decreases Remain unaffected Increases May increase or decrease depending on compressor capacity Decreases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall efficiency of the compressed air system is the None of these Ratio of shaft input to the compressor to the shaft output of air motor Ratio of shaft output of the air motor to the shaft input to the compressor Product of shaft output of air motor and shaft input to the compressor None of these Ratio of shaft input to the compressor to the shaft output of air motor Ratio of shaft output of the air motor to the shaft input to the compressor Product of shaft output of air motor and shaft input to the compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a double acting compressor, the air is compressed In one cylinder In a single cylinder on both sides of the piston In two cylinders In two cylinders on both sides of the piston In one cylinder In a single cylinder on both sides of the piston In two cylinders In two cylinders on both sides of the piston ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The temperature of air at the beginning of the compression stroke is ________ the atmospheric temperature. Less than Equal to More than None of these Less than Equal to More than None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The exit velocities of exhaust gases are much higher than those in jet engine The stagnation conditions exist at the combustion chamber 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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