Compressors, Gas Turbines and Jet Engines The ratio of work-done per cycle to the stroke volume of the compressor is known as Compressor capacity Mean effective pressure Compression ratio Compressor efficiency Compressor capacity Mean effective pressure Compression ratio Compressor efficiency 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 fuel energy Thrust power and propulsive power Propulsive power and fuel input Engine output and propulsive power Thrust power and fuel energy Thrust power and propulsive power ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Ratio of compression is the ratio of Gauge discharge pressure to the gauge intake pressure Stroke volume and clearance volume Pressures at discharge and suction corresponding to same temperature Absolute discharge pressure to the absolute intake pressure Gauge discharge pressure to the gauge intake pressure Stroke volume and clearance volume Pressures at discharge and suction corresponding to same temperature Absolute discharge pressure to the absolute intake pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The mean effective pressure of the compressor is the None of these Volume of air delivered by the compressor Actual volume of the air delivered by the compressor when reduced to normal temperature and pressure conditions Volume of air sucked by the compressor during its suction stroke None of these Volume of air delivered by the compressor Actual volume of the air delivered by the compressor when reduced to normal temperature and pressure conditions Volume of air sucked by the compressor during its suction stroke ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The efficiency of a jet engine is higher at Low speeds High speeds High altitudes Low altitudes Low speeds High speeds High altitudes Low altitudes 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 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 ANSWER DOWNLOAD EXAMIANS APP
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