Compressors, Gas Turbines and Jet Engines Which is false statement about advantages of multistage compressor in comparison to single stage compressor? Lower volumetric efficiency Less power requirement Less loss of air due to leakage past the cylinder Better mechanical balance Lower volumetric efficiency Less power requirement Less loss of air due to leakage past the cylinder Better mechanical balance ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The capacity of a compressor is expressed in m³/kg kg/m² kg/m³ m³/min m³/kg kg/m² kg/m³ m³/min ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of the compressor is defined as the ratio of Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor Isentropic power to the power required to drive the compressor Volume of free air delivery per stroke to the swept volume of the piston Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor Isentropic power to the power required to drive the compressor Volume of free air delivery per stroke to the swept volume of the piston Work required to compress the air isothermally to the actual work required to compress the air for the same pressure ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The pressure ratio in gas turbines is of the order of 0.084027777777778 0.37569444444444 0.16736111111111 2.5423611111111 0.084027777777778 0.37569444444444 0.16736111111111 2.5423611111111 ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The thrust on the rotor in a centrifugal compressor is produced by None of these Axial component Tangential component Radial component None of these Axial component Tangential component Radial component ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Maximum temperature in a gas turbine is of the order of 1500°C 1000°C 2000°C 700°C 1500°C 1000°C 2000°C 700°C ANSWER DOWNLOAD EXAMIANS APP
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