Compressors, Gas Turbines and Jet Engines A closed gas turbine in which fuel is burnt directly in the air is not possible because of High specific volume High friction losses Increasing gas temperature Paucity of O2 High specific volume High friction losses Increasing gas temperature Paucity of O2 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 Remain same Decrease None of these Increase Remain same Decrease None of these Increase ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compressor capacity with decrease in suction temperature Remain unaffected Decreases Increases May increase or decrease depending on compressor capacity Remain unaffected Decreases Increases May increase or decrease depending on compressor capacity ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If the flow of air through the compressor is parallel to its axis, then the compressor is Turbo compressor Centrifugal compressor Reciprocating compressor Axial flow compressor Turbo compressor Centrifugal compressor Reciprocating compressor Axial flow compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The maximum combustion pressure in gas turbine as compared to I.C. engine is Same Depends on other factors More Less Same Depends on other factors More Less 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
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