The good circumferential position of offset splitter blades and its mechanism were studied in small centrifugal impellers
which operated with different tip clearances by the computational fluid dynamics. When the impeller worked with the small tip clearance
the main loss was attributable to the separation near the main suction surfaces
and then the offset splitter bias toward the main suction surface can suppress this loss and enhance the impeller performance. The tip leakages increased with the tip clearance
so the loss concentrated in the passage between the main pressure surface and splitter
therefore the splitters tended to the main pressure surface
and then the offset splitters can reduce the concentration of the tip leakage and the loss. The tip clearance and the circumferential position of the splitter affected together the tip leakage
the separation near the suction surface and their interrelation. The design of the splitter circumferential position can adjust the crosswise pressure gradient in the blade passage and the location where the tip leakage mixes in the main flow
and then improve the ratio of the losses in the passages at both sides of splitter
therefore the best circumferential position of the splitter changes with the tip clearance.
Effect of tip clearance leakage on performance of centimetre-level high subsonic micro axial flow turbine
Numerical investigation of effect of radial vane diffuser fillet on performance of centrifugal compressor
Influence of tip clearance size on flow losses of a transonic high pressure turbine stage
Design and numerical simulation of pipe diffuser in centrifugal compressor
Optimized design of a small type high speed centrifugal compressor
Related Author
YU Haibin
DENG Yang
XIA Chen
FU Xin
HUANG Guo-ping
TANG Hui
NING Fang-fei
WANG Da-lei
Related Institution
Department of Aviation Mechanical Engineering, Qingdao Branch of Naval Aviation Engineering Institute
College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics
National Key Laboratory of Science and Technology on Aero-engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
School of Aerospace, Tsinghua University
National Key Laboratory of Science and Technology on Aero-Engines Aero-thermodynamics, School of Jet Propulsion,Beijing University of Aeronautics and Astronautics