A small high speed centrifugal impellor had been modified by rearranging the blade thickness and meridian line type;then the improved impellor was simulated with Fine/Turbo software.The result shows that: the adiabatic efficiency of the improved impellor increases by 2.4% and it also has wilder surge margin.Besides
changing radial flow impellor to inclined flow impellor will comparatively decrease the separation of blades with sacrifice of the pressure ratio.
Aerodynamic Redesign of a Centrifugal Compressor Impeller
Effect of tip clearance on the operating mechanism of offset splitter blades in a centrifugal compressor
Study of unsteady tip leakage flow characteristic in high pressure turbine stage
Numerical investigation of effect of radial vane diffuser fillet on performance of centrifugal compressor
Effect of annular chamber radial width on the performance and inner flow characteristics of an after-burning oil pump
Related Author
CHEN Jiang
JI Lu-cheng
CHEN Jie
HE Min-xiang
HUANG Guo-ping
WANG Da-lei
PIAO Ying
CHEN Mei-ning
Related Institution
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
Institute of Engineering Thermophysics, Chinese Academy of Sciences
Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics
School of Aerospace, Tsinghua University
National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics