Compressors, Gas Turbines and Jet Engines The ratio of outlet whirl velocity to blade velocity in case of centrifugal compressor is called None of these Velocity factor Slip factor Velocity coefficient None of these Velocity factor Slip factor Velocity coefficient ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A jet engine has Propeller in front Propeller on the top No propeller Propeller at back Propeller in front Propeller on the top No propeller Propeller at back ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The hottest point in a gas turbine is between ~ to i of the blade height in the center at the base at the tip between ~ to i of the blade height in the center at the base at the tip ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The indicated work per unit mass of air delivered is Greatly affected by clearance volume Not affected by clearance volume Inversely proportional to clearance volume Directly proportional to clearance volume Greatly affected by clearance volume Not affected by clearance volume Inversely proportional to clearance volume Directly proportional to clearance volume ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Phenomenon of choking in compressor means Reducing mass flow rate with increase in pressure ratio Increased inclination of chord with air steam Fixed mass flow rate regardless of pressure ratio No flow of air Reducing mass flow rate with increase in pressure ratio Increased inclination of chord with air steam Fixed mass flow rate regardless of pressure ratio No flow of air ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The stagnation conditions exist at the combustion chamber All of these The exit velocities of exhaust gases are much higher than those in jet engine The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The stagnation conditions exist at the combustion chamber All of these The exit velocities of exhaust gases are much higher than those in jet engine ANSWER DOWNLOAD EXAMIANS APP
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