Compressors, Gas Turbines and Jet Engines In axial flow compressor, exit flow angle deviation from the blade angle is a function of Blade camber Space-chord ratio Blade camber and space-chord ratio Blade camber and incidence angle Blade camber Space-chord ratio Blade camber and space-chord ratio Blade camber and incidence angle ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Ram compression in turbojet involves Compression of inlet air Lost work Increasing speed of incoming air Reduction of speed of incoming air and conversion of part of it into pressure energy Compression of inlet air Lost work Increasing speed of incoming air Reduction of speed of incoming air and conversion of part of it into pressure energy ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For minimum work required to compress and deliver a quantity of air by multistage compression The compression ratio in each stage should be same The work-done in each stage should be same All of the listed here The intercooling should be perfect The compression ratio in each stage should be same The work-done in each stage should be same All of the listed here The intercooling should be perfect ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Stalling of blades in axial flow compressor is the phenomenon of Air stream not able to follow the blade contour Motion of air at sonic velocity Unsteady periodic and reversed flow Air stream blocking the passage Air stream not able to follow the blade contour Motion of air at sonic velocity Unsteady periodic and reversed flow Air stream blocking the passage 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 Higher Can't be compared Lower Equal Higher Can't be compared Lower Equal 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 - 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 W₁/W₂ = n₂/n₁ W₁/W₂ = n₁(n₂ - 1)/n₂(n₁ - 1) ANSWER DOWNLOAD EXAMIANS APP
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