Compressors, Gas Turbines and Jet Engines The propulsive power of the rocket is (where v₁ = Jet velocity, and v₂ = Aircraft velocity) (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/2g (v₁² -v₂²)/g (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/2g (v₁² -v₂²)/g ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A closed cycle gas turbine gives ________ efficiency as compared to an open cycle gas turbine. Higher None of these Same Lower Higher None of these Same Lower ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thermal efficiency of a simple gas turbine for a given turbine inlet temperature with increase in pressure ratio First decreases and then increases First increases and then decreases Increases Decreases First decreases and then increases First increases and then decreases Increases Decreases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Reheating in multistage expansion gas turbine results in High thermal efficiency Decrease of heat loss in exhaust Maximum work output Reduction in compressor work High thermal efficiency Decrease of heat loss in exhaust Maximum work output Reduction in compressor work ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compression ratio in a gas turbine is of the order of 3.5 : 1 0.50069444444444 0.33402777777778 0.20902777777778 3.5 : 1 0.50069444444444 0.33402777777778 0.20902777777778 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Adiabatic compression is one in which No heat leaves or enters the compressor cylinder during compression Temperature rise follows a linear relationship Temperature during compression remains constant Work done is maximum No heat leaves or enters the compressor cylinder during compression Temperature rise follows a linear relationship Temperature during compression remains constant Work done is maximum ANSWER DOWNLOAD EXAMIANS APP
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