Compressors, Gas Turbines and Jet Engines Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is Can't be compared Higher Equal Lower Can't be compared Higher Equal Lower ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thermodynamic efficiency of rotary compressor is based on Isothermal compression Isentropic compression Adiabatic compression Polytropic compression Isothermal compression Isentropic compression Adiabatic compression Polytropic compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a single stage, single acting reciprocating air compressor, without clearance volume, the work-done is minimum during None of these Isentropic compression Polytropic compression Isothermal compression None of these Isentropic compression Polytropic compression Isothermal 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)/g (v₁² -v₂²)/2g (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/g (v₁² -v₂²)/2g (v₁ - v₂)²/2g (v₁ - v₂)²/g ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For speed above 3000 km/hour, it is more advantageous to use Turbojet engine Rockets Propellers Ramjet engine Turbojet engine Rockets Propellers Ramjet engine ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Axial flow compressor has the following advantage over centrifugal compressor Higher pressure ratio per stage Higher average velocities Aerofoil blades are used Larger air handling ability per unit frontal area Higher pressure ratio per stage Higher average velocities Aerofoil blades are used Larger air handling ability per unit frontal area ANSWER DOWNLOAD EXAMIANS APP
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