Compressors, Gas Turbines and Jet Engines The air-fuel ratio in gas turbines is of the order of 15: 1 50: 1. 7: 1 30: 1 15: 1 50: 1. 7: 1 30: 1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thermodynamic efficiency of rotary compressor is based on Isothermal compression Isentropic compression Adiabatic compression Polytropic compression Isothermal compression Isentropic compression Adiabatic compression Polytropic compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Maximum temperature in a gas turbine is of the order of 2000°C 1000°C 700°C 1500°C 2000°C 1000°C 700°C 1500°C ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compressor efficiency is the Isothermal H.P/indicated H.R Compression work/motor input Total output/air input Isothermal H.P./shaft H.R Isothermal H.P/indicated H.R Compression work/motor input Total output/air input Isothermal H.P./shaft H.R ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If V, U and Vr represent the absolute velocity of fluid, velocity of blade, and relative velocity of fluid, and suffix ‘I’ and ‘o’ stand for entry and exit conditions, then in a rotary machine whose degree of reaction is unity V = Uo U < Vo Vt > Vo Vi = Vo V = Uo U < Vo Vt > Vo Vi = Vo ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum delivery pressure in a rotary air compressor is 30 bar 50 bar 10 bar 20 bar 30 bar 50 bar 10 bar 20 bar ANSWER DOWNLOAD EXAMIANS APP
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