Compressors, Gas Turbines and Jet Engines For minimum work in multistage compression, assuming same index of compression in all stages Work done in first stage should be more Work done in all stages should be equal Work done in subsequent stages should increase Work done in subsequent stages should decrease Work done in first stage should be more Work done in all stages should be equal Work done in subsequent stages should increase Work done in subsequent stages should decrease ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of compressor is defined as the ratio of Power to drive compressor to isothermal h.p. Work to compress air isothermally to work for actual compression Isothermal h.p. to adiabatic h.p. Isothermal h.p. to the BHP of motor Power to drive compressor to isothermal h.p. Work to compress air isothermally to work for actual compression Isothermal h.p. to adiabatic h.p. Isothermal h.p. to the BHP of motor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A turboprop is preferred to turbojet because It can fly at supersonic speeds It can fly at high elevations It has high power for take off It has high propulsive efficiency at high speeds It can fly at supersonic speeds It can fly at high elevations It has high power for take off It has high propulsive efficiency at high speeds ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines A large clearance volume in a reciprocating compressor results in Reduced volume flow rate Lower delivery pressure Increased volume flow rate Lower suction pressure Reduced volume flow rate Lower delivery pressure Increased volume flow rate Lower suction pressure ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The volumetric efficiency of compressor with increase in compression ratio will Decrease Increase Remain same May increase or decrease depending on clearance volume Decrease Increase Remain same May increase or decrease depending on clearance volume ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The hottest point in a gas turbine is at the base between ~ to i of the blade height at the tip in the center at the base between ~ to i of the blade height at the tip in the center ANSWER DOWNLOAD EXAMIANS APP
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