Compressors, Gas Turbines and Jet Engines In an axial flow compressor, the ratio of pressure in the rotor blades to the pressure rise in the compressor in one stage is known as Pressure coefficient Degree of reaction Work factor Slip factor Pressure coefficient Degree of reaction Work factor Slip factor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall isothermal efficiency of the compressor is defined as the ratio of 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 Isothermal power to the shaft power or B.P. of the motor or engine required to drive the compressor ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines More than one stage will be preferred for reciprocating compressor if the delivery pressure is more than 6 kg/cm² 2 kg/cm² 10 kg/cm² 14.7 kg/cm² 6 kg/cm² 2 kg/cm² 10 kg/cm² 14.7 kg/cm² ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines Reheating in gas turbine results in Decrease of work ratio Decrease of thermal efficiency Both (A) and (B) above Increase of work ratio Decrease of work ratio Decrease of thermal efficiency Both (A) and (B) above Increase of work ratio ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines If the clearance ratio for a reciprocating air compressor is 'K', then its volumetric efficiency is given by 1 - k + k (p₁/p₂)1/n 1 - k + k (p₁/p₂) n- 1/n 1 + k - k (p₂/p₁)1/n 1 + k - k (p₂/p₁) n-1/n 1 - k + k (p₁/p₂)1/n 1 - k + k (p₁/p₂) n- 1/n 1 + k - k (p₂/p₁)1/n 1 + k - k (p₂/p₁) n-1/n ANSWER DOWNLOAD EXAMIANS APP
Compressors, Gas Turbines and Jet Engines The overall thermal efficiency of an ideal gas turbine plant is (where r = Pressure ratio) 1 - (1/r) ɣ-1/ɣ 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 r ɣ-1 1 - (1/r) ɣ-1/ɣ 1 - r ɣ-1 1 - (1/r) ɣ/ɣ-1 r ɣ-1 ANSWER DOWNLOAD EXAMIANS APP
EXAMIANS