Compressors, Gas Turbines and Jet Engines The thrust on the rotor in a centrifugal compressor is produced by Tangential component None of these Axial component Radial component Tangential component None of these Axial component Radial component ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The ratio of specific weight/h.p. of gas turbine and I.C engines may be typically of the order of 0.045833333333333 0.084027777777778 0.042361111111111 0.16736111111111 0.045833333333333 0.084027777777778 0.042361111111111 0.16736111111111 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Isothermal compression though most efficient, but is not practicable because Compressor has to run at very slow speed to achieve it It does not increase pressure much It is impossible in practice It requires very big cylinder Compressor has to run at very slow speed to achieve it It does not increase pressure much It is impossible in practice It requires very big cylinder ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In an axial flow compressor, the ratio of pressure in the rotor blades to the pressure rise in the compressor in one stage is known as Work factor Degree of reaction Slip factor Pressure coefficient Work factor Degree of reaction Slip factor Pressure coefficient ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A rocket engine uses __________ for the combustion of its fuel. Compressed atmospheric air Its own oxygen None of these Surrounding air Compressed atmospheric air Its own oxygen None of these Surrounding air ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The work done per unit mass of air in compression will be least when 'n' is equal to 1.4 1.3 1.2 1 1.4 1.3 1.2 1 ANSWER DOWNLOAD EXAMIANS APP
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