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)/g (v₁² -v₂²)/2g (v₁ - v₂)²/2g (v₁ - v₂)²/g (v₁² -v₂²)/g (v₁² -v₂²)/2g ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For a two stage compressor, if index of compression for higher stage is greater than index of compression for lower stage, then the optimum pressure as compared to ideal case will Increase Other factors control it Decrease Remain unaffected Increase Other factors control it Decrease Remain unaffected ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Ratio of compression is the ratio of Gauge discharge pressure to the gauge intake pressure Pressures at discharge and suction corresponding to same temperature Stroke volume and clearance volume Absolute discharge pressure to the absolute intake pressure Gauge discharge pressure to the gauge intake pressure Pressures at discharge and suction corresponding to same temperature Stroke volume and clearance volume Absolute discharge pressure to the absolute intake pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio in gas turbines Reduces exhaust temperature Do not damage turbine blades Improves thermal efficiency Increases power output Reduces exhaust temperature Do not damage turbine blades Improves thermal efficiency Increases power output ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the axial flow gas turbine, the work ratio is the ratio of Actual compressor work and theoretical compressor work Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Output and input Compressor work and turbine work Actual compressor work and theoretical compressor work Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Output and input Compressor work and turbine work ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 1 - (1/r) ɣ-1/ɣ r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 1 - (1/r) ɣ-1/ɣ ANSWER DOWNLOAD EXAMIANS APP
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