Compressors, Gas Turbines and Jet Engines In n₁ and n₂ are the indices of compression for the first and second stage of compression, then the ratio of work-done on the first and second stages (W₁/W₂) with perfect intercooling is given by W₁/W₂ = n₂/n₁ W₁/W₂ = n₁/n₂ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₂/n₁ W₁/W₂ = n₁/n₂ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The compressor capacity with decrease in suction temperature Increases Remain unaffected Decreases May increase or decrease depending on compressor capacity Increases Remain unaffected Decreases May increase or decrease depending on compressor capacity ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of compressor is defined as the ratio of Isothermal h.p. to adiabatic h.p. Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Work to compress air isothermally to work for actual compression Isothermal h.p. to adiabatic h.p. Power to drive compressor to isothermal h.p. Isothermal h.p. to the BHP of motor Work to compress air isothermally to work for actual compression ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In a jet engine, the air-fuel ratio is 2.5006944444444 2.0840277777778 1.6673611111111 1.2506944444444 2.5006944444444 2.0840277777778 1.6673611111111 1.2506944444444 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 The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these The stagnation conditions exist at the combustion chamber The exit velocities of exhaust gases are much higher than those in jet engine The combustion chamber in a rocket engine is directly analogous to the reservoir of a supersonic wind tunnel All of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Mechanical efficiency of gas turbines as compared to I.C engines is Same Lower None of these Higher Same Lower None of these Higher ANSWER DOWNLOAD EXAMIANS APP
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