Compressors, Gas Turbines and Jet Engines The maximum combustion pressure in gas turbine as compared to I.C. engine is Depends on other factors Same More Less Depends on other factors Same More Less ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The inter-cooler pressure, for minimum work required, for a two stage reciprocating air compressor, is given by (where p₁ = Intake pressure of air, p₂ = Inter-cooler pressure, and p₃ = Delivery pressure of air) p₂ = p₁/p₃ p₂ = p₁ × p₃ p₂ = p₁ × p₂ p₂ = p₃/p₁ p₂ = p₁/p₃ p₂ = p₁ × p₃ p₂ = p₁ × p₂ p₂ = p₃/p₁ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The criterion of the thermodynamic efficiency for rotary compressor is None of the listed here Isothermal compression Polytropic compression Isentropic compression None of the listed here Isothermal compression Polytropic compression Isentropic compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The effective power of gas turbines is increased by adding the following in compressor Hydrogen Nitrogen Ammonia and water vapour Carbon dioxide Hydrogen Nitrogen Ammonia and water vapour Carbon dioxide ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The efficiency of jet engine is Higher at high speed Lower at low speed Higher at high altitudes Same at all altitudes Higher at high speed Lower at low speed Higher at high altitudes Same at all altitudes ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct relating to rocket engines? The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine All of these The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel ANSWER DOWNLOAD EXAMIANS APP
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