Compressors, Gas Turbines and Jet Engines The thermodynamic efficiency of rotary compressor is based on Isentropic compression Polytropic compression Isothermal compression Adiabatic compression Isentropic compression Polytropic compression Isothermal compression Adiabatic compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The propulsive power of the rocket is (where v₁ = Jet velocity, and v₂ = Aircraft velocity) (v₁² -v₂²)/2g (v₁ - v₂)²/g (v₁ - v₂)²/2g (v₁² -v₂²)/g (v₁² -v₂²)/2g (v₁ - v₂)²/g (v₁ - v₂)²/2g (v₁² -v₂²)/g ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The pressure ratio in gas turbines is of the order of 2.5423611111111 0.084027777777778 0.16736111111111 0.37569444444444 2.5423611111111 0.084027777777778 0.16736111111111 0.37569444444444 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In jet engines the products of combustion after passing through the gas turbine are discharged into Discharge nozzle Vacuum Back to the compressor Atmosphere Discharge nozzle Vacuum Back to the compressor Atmosphere ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a single acting reciprocating compressor, the suction, compression and delivery of air takes place in ________ of the piston. Three strokes Two strokes One stroke Four strokes Three strokes Two strokes One stroke Four strokes ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The degree of reaction in an axial flow compressor is defined as the ratio of static enthalpy rise in the Stator to static enthalpy rise in the stage Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stator Rotor to static enthalpy rise in the stage Stator to static enthalpy rise in the stage Stator to static enthalpy rise in the rotor Rotor to static enthalpy rise in the stator Rotor to static enthalpy rise in the stage ANSWER DOWNLOAD EXAMIANS APP
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