Compressors, Gas Turbines and Jet Engines Compression efficiency is compared against Ideal compression Isothermal compression Adiabatic compression Isentropic compression Ideal compression Isothermal compression Adiabatic compression Isentropic compression ANSWER DOWNLOAD EXAMIANS APP
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 - 1)/n₂(n₁ - 1) W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₁/n₂ W₁/W₂ = n₂/n₁ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) W₁/W₂ = n₂(n₁ - 1)/n₁(n₂ - 1) W₁/W₂ = n₁/n₂ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The stagnation pressure rise in a centrifugal compressor takes place In the diffuser only In the inlet guide vanes only In the diffuser and impeller In the impeller only In the diffuser only In the inlet guide vanes only In the diffuser and impeller In the impeller only 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 0.85 0.75 0.99 0.9 0.85 0.75 0.99 0.9 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of Space-chord ratio Blade camber and space-chord ratio Blade camber Blade camber and incidence angle Space-chord ratio Blade camber and space-chord ratio Blade camber Blade camber and incidence angle ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In jet engines, for the efficient production of large power, fuel is burnt in an atmosphere of Oxygen alone Compressed air Vacuum Atmospheric air Oxygen alone Compressed air Vacuum Atmospheric air ANSWER DOWNLOAD EXAMIANS APP
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