Compressors, Gas Turbines and Jet Engines The compressor efficiency is the Isothermal H.P./shaft H.R Isothermal H.P/indicated H.R Total output/air input Compression work/motor input Isothermal H.P./shaft H.R Isothermal H.P/indicated H.R Total output/air input Compression work/motor input ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Adiabatic compression is one in which Temperature rise follows a linear relationship Temperature during compression remains constant No heat leaves or enters the compressor cylinder during compression Work done is maximum Temperature rise follows a linear relationship Temperature during compression remains constant No heat leaves or enters the compressor cylinder during compression Work done is maximum ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines There is a certain pressure ratio (optimum) for a gas turbine at which its thermal efficiency is maximum. With increase in turbine temperature, the value of pressure ratio for the peak efficiency would Increase Remain same Decrease None of these Increase Remain same Decrease None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines An ideal air compressor cycle without clearance on P-V diagram can be represented by following processes One adiabatic, two isobaric, and one constant volume Two adiabatic and two isobaric One adiabatic, one isobaric and two constant volumes Two adiabatic, one isobaric and one constant volume One adiabatic, two isobaric, and one constant volume Two adiabatic and two isobaric One adiabatic, one isobaric and two constant volumes Two adiabatic, one isobaric and one constant volume 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 Polytropic compression Isentropic compression None of these Isothermal compression Polytropic compression Isentropic compression None of these Isothermal compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Stalling of blades in axial flow compressor is the phenomenon of Air stream blocking the passage Air stream not able to follow the blade contour Unsteady periodic and reversed flow Motion of air at sonic velocity Air stream blocking the passage Air stream not able to follow the blade contour Unsteady periodic and reversed flow Motion of air at sonic velocity ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS