Compressors, Gas Turbines and Jet Engines The overall efficiency of the compressed air system is the None of these Ratio of shaft output of the air motor to the shaft input to the compressor Product of shaft output of air motor and shaft input to the compressor Ratio of shaft input to the compressor to the shaft output of air motor None of these Ratio of shaft output of the air motor to the shaft input to the compressor Product of shaft output of air motor and shaft input to the compressor Ratio of shaft input to the compressor to the shaft output of air motor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a jet propulsion Its functioning does not depend upon presence of air None of these The propulsive matter is caused to flow around the propelled body The propulsive matter is ejected from within the propelled body Its functioning does not depend upon presence of air None of these The propulsive matter is caused to flow around the propelled body The propulsive matter is ejected from within the propelled body ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Reheating in a multistage expansion gas turbine ________ compressor work. None of these Has no effect on Increases Decreases None of these Has no effect on Increases Decreases ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The advantage of multistage compression over single stage compression is All of these Decreased discharge temperature Lower power consumption per unit of air delivered Higher volumetric efficiency All of these Decreased discharge temperature Lower power consumption per unit of air delivered Higher volumetric efficiency ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If p₁ is the pressure of air entering the L.P, cylinder and p₃ is the pressure of air leaving the H.P. cylinder, then the ratio of cylinder diameters for a single acting, two stage reciprocating compressor with complete intercooling is given by D₁/D₂ = (p₃/p₁)1/4 D₁/D₂ = (p₁/p₃)1/4 D₁/D₂ = (p₁ p₃)1/2 D₁/D₂ = (p₁ p₃)1/4 D₁/D₂ = (p₃/p₁)1/4 D₁/D₂ = (p₁/p₃)1/4 D₁/D₂ = (p₁ p₃)1/2 D₁/D₂ = (p₁ p₃)1/4 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum temperature in a gas turbine is 500°C 200°C 1000°C 700°C 500°C 200°C 1000°C 700°C ANSWER DOWNLOAD EXAMIANS APP
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