Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - (1/r) ɣ-1/ɣ r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 1 - (1/r) ɣ-1/ɣ r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of Blade camber and incidence angle Space-chord ratio Blade camber and space-chord ratio Blade camber Blade camber and incidence angle Space-chord ratio Blade camber and space-chord ratio Blade camber ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thrust on the rotor in a centrifugal compressor is produced by None of these Radial component Axial component Tangential component None of these Radial component Axial component Tangential component ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The ratio of isentropic work to Euler’s work is known as Isentropic efficiency Compressor efficiency Pressure coefficient Euler Isentropic efficiency Compressor efficiency Pressure coefficient Euler ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The air is delivered ________ in one revolution in case of a three lobbed rotor. Six times Three times Four times Two times Six times Three times Four times Two times ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A centrifugal compressor works on the principle of Centripetal action Conversion of kinetic energy into pressure energy Conversion of pressure energy into kinetic energy Generating pressure directly Centripetal action Conversion of kinetic energy into pressure energy Conversion of pressure energy into kinetic energy Generating pressure directly ANSWER DOWNLOAD EXAMIANS APP
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