Compressors, Gas Turbines and Jet Engines The propulsive power of the rocket is (where v₁ = Jet velocity, and v₂ = Aircraft velocity) (v₁ - v₂)²/g (v₁² -v₂²)/g (v₁² -v₂²)/2g (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/g (v₁² -v₂²)/2g (v₁ - v₂)²/2g ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In an axial flow compressor, the ratio of pressure in the rotor blades to the pressure rise in the compressor in one stage is known as Pressure coefficient Work factor Slip factor Degree of reaction Pressure coefficient Work factor Slip factor Degree of reaction ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Maximum temperature in a gas turbine is of the order of 700°C 1000°C 2000°C 1500°C 700°C 1000°C 2000°C 1500°C 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 tip at the base between ~ to i of the blade height in the center at the tip at the base ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The degree of reaction is usually kept ________ for all types of axial flow compressors. 0.3 0.4 0.2 0.5 0.3 0.4 0.2 0.5 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines With the decrease in compression ratio, the volumetric efficiency Does not change Decreases Increases First decrease and then increase Does not change Decreases Increases First decrease and then increase ANSWER DOWNLOAD EXAMIANS APP
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