Compressors, Gas Turbines and Jet Engines Work ratio of a gas turbine may be improved by Both (A) and (C) above Increasing the compression work Decreasing the compression work Increasing the turbine work Both (A) and (C) above Increasing the compression work Decreasing the compression work Increasing the turbine work ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Stalling of blades in axial flow compressor is the phenomenon of Unsteady periodic and reversed flow Air stream blocking the passage Motion of air at sonic velocity Air stream not able to follow the blade contour Unsteady periodic and reversed flow Air stream blocking the passage Motion of air at sonic velocity Air stream not able to follow the blade contour ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If p₁, is the pressure of air entering the L.P. cylinder and p₂ is the pressure of air leaving the L.P. cylinder (or inter-cooler pressure), then the ratio of cylinder diameters for a single acting, two stage reciprocating air compressor with complete intercooling is given by (where D₁ = Dia. of L.P. cylinder, and D₂ = Dia. of H.P. cylinder) None of these D₁/D₂ = p₁/p₂ D₁/D₂ = p₂/p₁ D₁/D₂ = p₁ p₂ None of these D₁/D₂ = p₁/p₂ D₁/D₂ = p₂/p₁ D₁/D₂ = p₁ p₂ ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines In the aircraft propellers All of these Its functioning does not depend on presence of air Propulsive matter is ejected from within the propelled body The propulsive matter is caused to flow around the propelled body All of these Its functioning does not depend on presence of air Propulsive matter is ejected from within the propelled body The propulsive matter is caused to flow around the propelled body ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The axial flow compressor is preferred in aircraft gas turbines because of Higher thrust Low frontal area None of the listed here High pressure rise Higher thrust Low frontal area None of the listed here High pressure rise ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Propulsive efficiency is defined as ratio of Engine output and propulsive power Thrust power and propulsive power Thrust power and fuel energy Propulsive power and fuel input Engine output and propulsive power Thrust power and propulsive power Thrust power and fuel energy Propulsive power and fuel input ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS