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 Blade camber and space-chord ratio Blade camber and incidence angle Space-chord ratio Blade camber Blade camber and space-chord ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The absolute pressure of air at the outlet of a compressor is called Back pressure None of the listed here Discharge pressure Critical pressure Back pressure None of the listed here Discharge pressure Critical pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compression ratio in a gas turbine is of the order of 0.20902777777778 3.5 : 1 0.50069444444444 0.33402777777778 0.20902777777778 3.5 : 1 0.50069444444444 0.33402777777778 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a centrifugal compressor, an increase in speed at a given pressure ratio causes Increase in flow and decrease in efficiency Increase in flow Decrease in flow Increase in efficiency Increase in flow and decrease in efficiency Increase in flow Decrease in flow Increase in efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The inter-cooler pressure, for minimum work required, for a two stage reciprocating air compressor, is given by (where p₁ = Intake pressure of air, p₂ = Inter-cooler pressure, and p₃ = Delivery pressure of air) p₂ = p₁ × p₃ p₂ = p₁/p₃ p₂ = p₁ × p₂ p₂ = p₃/p₁ p₂ = p₁ × p₃ p₂ = p₁/p₃ p₂ = p₁ × p₂ p₂ = p₃/p₁ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The volumetric efficiency of a compressor falls roughly as follows for every 5°C increase in atmospheric temperature 0.05 0.005 0.001 0.01 0.05 0.005 0.001 0.01 ANSWER DOWNLOAD EXAMIANS APP
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