Compressors, Gas Turbines and Jet Engines The compression ratio in a gas turbine is of the order of 0.33402777777778 3.5 : 1 0.50069444444444 0.20902777777778 0.33402777777778 3.5 : 1 0.50069444444444 0.20902777777778 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio in gas turbines Reduces exhaust temperature Increases power output Do not damage turbine blades Improves thermal efficiency Reduces exhaust temperature Increases power output Do not damage turbine blades Improves thermal efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the axial flow gas turbine, the work ratio is the ratio of Actual total head temperature drop to the isentropic total head drop from total head inlet to static head outlet Compressor work and turbine work Output and input 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 Compressor work and turbine work Output and input Actual compressor work and theoretical compressor work ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The working fluid in a turbine is In the form of air and water mixture In a single phase In three phases In two phases In the form of air and water mixture In a single phase In three phases In two phases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Open cycle gas turbine works on Ericsson cycle Brayton or Atkinson cycle Rankine cycle Carnot cycle Ericsson cycle Brayton or Atkinson cycle Rankine cycle Carnot cycle ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine ANSWER DOWNLOAD EXAMIANS APP
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