Compressors, Gas Turbines and Jet Engines In a single acting reciprocating air compressor, without clearance, the compression of air may be Any one of these Isothermal Isentropic Polytropic Any one of these Isothermal Isentropic Polytropic ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The degree of reaction of an axial flow turbine is the ratio of isentropic temperature drop in a blade row to the Total temperature drop Adiabatic temperature drop in the stage Total adiabatic temperature drop Total temperature drop in the stage Total temperature drop Adiabatic temperature drop in the stage Total adiabatic temperature drop Total temperature drop in the stage ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall efficiency of the compressed air system is the Product of shaft output of air motor and shaft input to the compressor Ratio of shaft output of the air motor to the shaft input to the compressor Ratio of shaft input to the compressor to the shaft output of air motor None of these Product of shaft output of air motor and shaft input to the compressor Ratio of shaft output of the air motor to the shaft input to the compressor Ratio of shaft input to the compressor to the shaft output of air motor None of these ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines For a two stage reciprocating compressor, compression from p₁ to p₃ is with perfect intercooling and no pressure losses. If compression in both the cylinders follows the same polytropic process and the atmospheric pressure is pa, then the intermediate pressure p₂ is given by p₂ = Pa p₃/p₁ P₂ = Pa × p₃/p₁ p₂ = p₁. p₃ p₂ = (p₁ + p₃)/2 p₂ = Pa p₃/p₁ P₂ = Pa × p₃/p₁ p₂ = p₁. p₃ p₂ = (p₁ + p₃)/2 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Propulsive efficiency is defined as ratio of Thrust power and propulsive power Propulsive power and fuel input Thrust power and fuel energy Engine output and propulsive power Thrust power and propulsive power Propulsive power and fuel input Thrust power and fuel energy Engine output and propulsive power ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Which of the following statement is correct as regard to centrifugal compressors? The flow of air is parallel to the axis of the compressor The static pressure of air in the impeller increases in order to provide centripetal force on the air The maximum efficiency is higher than multistage axial flow compressors The impeller rotates at high speeds The flow of air is parallel to the axis of the compressor The static pressure of air in the impeller increases in order to provide centripetal force on the air The maximum efficiency is higher than multistage axial flow compressors The impeller rotates at high speeds ANSWER DOWNLOAD EXAMIANS APP
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