Compressors, Gas Turbines and Jet Engines Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is Higher Equal Lower Can't be compared Higher Equal Lower Can't be compared 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 at the base at the tip in the center between ~ to i of the blade height at the base at the tip in the center ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a centrifugal compressor, the highest Mach number leading to shock wave in the fluid flow occurs at Diffuser outlet radius Impeller outlet radius Impeller inlet radius Diffuser inlet radius Diffuser outlet radius Impeller outlet radius Impeller inlet radius Diffuser inlet radius ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compressor efficiency is the Isothermal H.P./shaft H.R Total output/air input Compression work/motor input Isothermal H.P/indicated H.R Isothermal H.P./shaft H.R Total output/air input Compression work/motor input Isothermal H.P/indicated H.R ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of the compressor is defined as the ratio of Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor Volume of free air delivery per stroke to the swept volume of the piston Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio Isentropic power to the power required to drive the compressor Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor Volume of free air delivery per stroke to the swept volume of the piston Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio Isentropic power to the power required to drive the compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For perfect intercooling in a two stage compressor p₁ = p₂ p3 p₁/p₃ = p₂/p₁ p₂/p₁ = p₃/p₂ p₁ = p3 p₁ = p₂ p3 p₁/p₃ = p₂/p₁ p₂/p₁ = p₃/p₂ p₁ = p3 ANSWER DOWNLOAD EXAMIANS APP
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