Compressors, Gas Turbines and Jet Engines For perfect intercooling in a two stage compressor p₁/p₃ = p₂/p₁ p₂/p₁ = p₃/p₂ p₁ = p3 p₁ = p₂ p3 p₁/p₃ = p₂/p₁ p₂/p₁ = p₃/p₂ p₁ = p3 p₁ = p₂ p3 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines High air-fuel ratio in gas turbines Reduces exhaust temperature Increases power output Improves thermal efficiency Do not damage turbine blades Reduces exhaust temperature Increases power output Improves thermal efficiency Do not damage turbine blades ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Temperature of gases at end of compression as compared to exhaust gases in a gas turbine is Equal Higher Lower Can't be compared Equal Higher Lower Can't be compared ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The combustion efficiency of a gas turbine using perfect combustion chamber is of the order of 0.99 0.85 0.9 0.75 0.99 0.85 0.9 0.75 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 r ɣ-1 1 - r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - (1/r) ɣ/ɣ-1 r ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Adiabatic compression is one in which No heat leaves or enters the compressor cylinder during compression Temperature during compression remains constant Work done is maximum Temperature rise follows a linear relationship No heat leaves or enters the compressor cylinder during compression Temperature during compression remains constant Work done is maximum Temperature rise follows a linear relationship ANSWER DOWNLOAD EXAMIANS APP
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