| Citation: | LI Guangyong, ZHANG Chaowei, CHEN Yanlong. Influence of splitter blade circumferential position on aerodynamic performance of high pressure ratio centrifugal compressor[J]. Journal of Aerospace Power, 2026, 41（5）：20250236 doi: 10.13224/j.cnki.jasp.20250236
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Taking the Krain 6 high-pressure-ratio centrifugal compressor as the research object, a splitter blade circumferential offset method—independent offset was proposed, and compared with the conventional integral offset method. The results showed that the new method can further improve the compressor performance based on the conventional method. When the splitter blade was offset to the pressure surface of main blade, the intensity and range of the shock wave near the suction surface leading edge of the splitter blade decreased, and the splitter blade effectively distributed the tip leakage flow. Meanwhile, the reduction in channel 1’s width and divergence angle strengthened the ejection of the tip leakage flow from the suction surface of the splitter blade to the channel 1, and weakened the adverse pressure gradient along the flow direction. These reduced the interaction between shock wave and tip leakage flow in channel 1, as well as the mixing and diffusion losses caused by tip leakage flow. However, too large offset could destroy the reasonable distribution of the tip leakage flow. Therefore, the circumferential position of the splitter blade set at 68% was optimal in the integral offset schemes, and the pressure ratio and efficiency increased by 1.44% and 0.62% at the mass flow rate of 2.95 kg/s. The circumferential position of the splitter blade’s leading edge set at 68% and that of trailing edge set at 72% was optimal in the independent schemes, where the pressure ratio and efficiency increased by 2.02% and 1.08% at the same mass flow rate. The reasons of independent offset scheme improving the compressor performance lied in that, the tip leakage flow intensity on the leading edge of the splitter blade decreased. The high intensity shock wave near the suction surface leading edge of the splitter blade disappeared. The decreased divergence angle mitigated the adverse pressure gradient along the flow direction of channel 1, and limited the mixing and diffusion of the tip leakage flow.
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