Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 30: 1 50: 1. 7: 1 15: 1 30: 1 50: 1. 7: 1 15: 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 Space-chord ratio Blade camber Blade camber and space-chord ratio Blade camber and incidence angle Space-chord ratio Blade camber Blade camber and space-chord ratio Blade camber and incidence angle 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. None of these Less than Equal to More than None of these Less than Equal to More than ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The fuel consumption in gas turbines is accounted for by Lower heating value Higher calorific value Heating value Higher heating value Lower heating value Higher calorific value Heating value Higher heating value ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Intercooling in gas turbines Increases net output and thermal efficiency both Decreases net output and thermal efficiency both Decreases net output but increases thermal efficiency Increases net output but decreases thermal efficiency Increases net output and thermal efficiency both Decreases net output and thermal efficiency both Decreases net output but increases thermal efficiency Increases net output but decreases thermal efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines There is a certain pressure ratio (optimum) for a gas turbine at which its thermal efficiency is maximum. With increase in turbine temperature, the value of pressure ratio for the peak efficiency would Decrease Increase Remain same None of these Decrease Increase Remain same None of these ANSWER DOWNLOAD EXAMIANS APP
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