Compressors, Gas Turbines and Jet Engines In a compressor, free air delivered is the actual volume delivered at the stated pressure reduced to Intake temperature and pressure conditions 0°C and 1 kg/cm² N.T.P. conditions 20°C and 1 kg/cm² Intake temperature and pressure conditions 0°C and 1 kg/cm² N.T.P. conditions 20°C and 1 kg/cm² ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The work ratio of simple gas turbine cycle depends on Maximum cycle temperature Pressure ratio Minimum cycle temperature All of these Maximum cycle temperature Pressure ratio Minimum cycle temperature All of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The minimum work required for a three stage reciprocating air compressor is ___ the work required for each stage. Three times Double Six times Equal to Three times Double Six times Equal to ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The ratio of work done per cycle to the swept volume in case of compressor is called Compressor efficiency Mean effective pressure Compression ratio Compression index Compressor efficiency Mean effective pressure Compression ratio Compression index ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A rocket engine uses __________ for the combustion of its fuel. None of these Surrounding air Its own oxygen Compressed atmospheric air None of these Surrounding air Its own oxygen Compressed atmospheric air ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? 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 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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