Influence of splitter blade circumferential position on aerodynamic performance of high pressure ratio centrifugal compressor
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摘要:
以Krain 6高压比离心压气机为研究对象，提出了一种分流叶片周向偏置方法——独立偏置，并与传统的整体偏置方法进行对比。结果表明：独立偏置方法可以在整体偏置方法基础上进一步提高压气机性能。整体偏置方案中分流叶片向主叶片压力面偏置时，分流叶片吸力面前缘附近的激波强度和范围减小，分流叶片对泄漏流进行有效分配，同时流道1宽度以及扩张角的减小使分流叶片吸力面对流道1中泄漏流的引射作用加强以及沿流向的逆压梯度减弱，从而减小流道1中激波和叶顶泄漏流相互作用和泄漏流掺混扩散引起的损失，但过大的偏移量会破坏泄漏流的合理分配，分流叶片整体周向位置为68%时压气机性能最优，在压气机出口质量流量为2.95 kg/s工况下，压比和效率分别提升1.44%和0.62%；在独立偏置方案中，当分流叶片前缘周向位置为68%，尾缘周向位置为72%时压气机性能最优，在压气机出口质量流量为2.95 kg/s工况下，压比和效率分别提升2.02%和1.08%。独立偏置方案提升压气机性能的机理在于分流叶片前段泄漏流强度减小，分流叶片吸力面前缘附近高强度激波消失，以及流道1扩张角减小导致沿流向逆压力梯度减小，限制了泄漏流的掺混和扩散。
Abstract: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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图 5 Krain 6叶轮的CFD计算值和实验值对比图
Figure 5. Comparison between the CFD and experimental results of Krain 6 impeller
图 7 不同整体偏置方案总体特性曲线对比
Figure 7. Comparison of performance with integrate offset schemes
图 8 整体偏置各方案工作裕度和堵塞流量
Figure 8. Operating margin and mass flow rate at choke point with integrate offset schemes
图 9 整体偏置各方案总压比和等熵效率
Figure 9. Total pressure ratio and isentropic efficiency with integrate offset schemes
图 10 流道扩张角随整体偏置方案变化示意图
Figure 10. Flow channel divergence angle with integrate offset schemes
图 11 不同整体偏置方案95%叶高处相对马赫数分布 （qm=2.95 kg/s）
Figure 11. 95% span relative Mach number distribution with integrate offset schemes （qm=2.95 kg/s）
图 12 不同整体偏置方案叶轮吸力面熵分布 （qm=2.95 kg/s）
Figure 12. Entropy distribution of suction surface with integrate offset schemes （qm=2.95 kg/s）
图 13 不同整体偏置方案叶轮95%叶高熵值分布和三维泄漏流线分布 （qm=2.95 kg/s）
Figure 13. 95% span entropy distribution and tip leakage flow 3D streamline with integrate offset schemes （qm=2.95 kg/s）
图 14 不同整体偏置方案95%叶高处叶片表面静压分布 （qm=2.95 kg/s）
Figure 14. 95% span static pressure distribution with integrate offset schemes （qm=2.95 kg/s）
图 15 不同独立偏置方案特性曲线对比图
Figure 15. Comparison of performance with independent offset schemes
图 16 不同独立偏置方案95%叶高相对马赫数分布 （qm=2.95 kg/s）
Figure 16. 95% span relative Mach number distribution with independent offset schemes （qm=2.95 kg/s）
图 17 不同独立偏置方案叶轮吸力面熵分布 （qm=2.95 kg/s）
Figure 17. Entropy distribution of suction surface with independent offset schemes （qm=2.95 kg/s）
图 18 不同独立偏置方案95%叶高处叶片表面静压分布 （qm=2.95 kg/s）
Figure 18. Static pressure distribution at 95% span with independent offset schemes （qm=2.95 kg/s）
图 19 不同独立偏置方案分流叶片前25%弦长叶顶泄漏流流量 （qm=2.95 kg/s）
Figure 19. Tip leakage mass flow rate from leading edge to 25% chord of splitter blades with independent offset schemes （qm=2.95 kg/s）
图 20 流道扩张角随独立偏置方案变化示意图
Figure 20. Flow channel divergence angle with independent offset scheme
图 21 不同独立偏置方案叶轮95%叶高熵值分布和三维泄漏流线分布 （qm=2.95 kg/s）
Figure 21. 95% span entropy distribution and tip leakage flow 3D streamline with independent offset schemes （qm=2.95 kg/s）
表 1 Krain 6设计参数
Table 1. Design parameters of Krain 6
设计参数 数值 转速/（r/min） 50000 流量/（kg/s） 2.55 等熵效率 0.84 级压比 6.1 叶片数 Zf=13 Zs=13 进口叶尖相对马赫数 1.3 叶顶间隙/mm 0.5（前缘）
0.3（尾缘）进口轮毂半径/mm 30 出口轮毂半径/mm 78 叶尖速度/（m/s） 586 
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表 2 分流叶片偏置方案
Table 2. Splitter blade offset schemes
叶轮 偏置方向 方案参数 原始叶轮 γ=50% 整体偏置
叶轮主叶片吸力面方向 γ=41%, γ=36%,
γ=32%, γ=28%主叶片压力面方向 γ=59%, γ=64%,
γ=68%, γ=72%独立偏置
叶轮主叶片压力面方向 （γ1=64%, γ2=68%）,
（γ1 =72%, γ2=68%）,
（γ1=68%, γ2=64%）,
（γ1=68%, γ2=72%）
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表 3 不同独立偏置方案总体性能对比
Table 3. Comparison of performance for different independent offset schemes
方案参数 压比
（qm=2.95 kg/s）效率/%
（qm=2.95 kg/s）峰值效率/% 堵塞流量/
（kg/s）工作裕度/% γ=50% 5.668 77.60 77.60 3.074 12.20 γ1=64%、γ2=68% 5.793 78.48 78.48 3.071 10.77 γ1=68%、γ2=72% 5.783 78.68 78.68 3.072 11.14 γ=68% 5.750 78.22 78.22 3.088 11.60 γ1=68%、γ2=64% 5.547 76.83 77.01 3.091 14.27 γ1=72%、γ2=68% 5.526 76.94 77.21 3.089 13.89
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[1] FRADIN C H. Investigation of the three dimensional flow near the exit of two backswept transonic centrifugal impellers[C]// Proceedings of the 8th International Symposium on Air Breathing Engines, Cincinnati, US: ISABE. 1987: 149-155. [2] MILLOUR V. 3D flow computations in a centrifugal compressor with splitter blade including viscous effect simulation [C]// Proceedings of the 16th International Council of the Aeronautical Sciences (ICAS) Congress, Jerusalem, Israel: ICAS. 1988: 842-847. [3] 蒋松廷. 高压比离心压气机设计方法研究[D]. 北京: 中国科学院研究生院(工程热物理研究所), 2016. JIANG Songting. Study on design method of high pressure ratio centrifugal compressor[D]. Beijing: Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2016. (in ChineseJIANG Songting. Study on design method of high pressure ratio centrifugal compressor[D]. Beijing: Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2016. (in Chinese) [4] ZHANG Wenchao, SUN Zhenzhong, WANG Baotong, et al. Influence of splitter blades on the performance of a single-stage centrifugal compressor with pressure ratio 12.0[C]// Proceedings of Turbo Expo: Power for Land, Sea, and Air, London, UK: ASME, 2020: V02ET39A016. [5] OMIDI M, LIU Yan, MOHTARAM S, et al. Investigating on performance parameters and flow field of centrifugal compressor based on the splitter blade leading edge’s location effect[J]. Journal of Mechanical Science and Technology, 2022, 36(8): 4015-4020. doi: 10.1007/s12206-022-0722-5 [6] OU Jun, JIN Donghai, GUI Xingmin. Numerical investigation of the load distribution between the main blade and the splitter blade in a high-loading centrifugal compressor[J]. Journal of Thermal Science, 2022, 31(5): 1682-1695. doi: 10.1007/s11630-022-1608-7 [7] ERDMENGER R R, MICHELASSI V. Impact of main and splitter blade leading edge contour on the performance of high pressure ratio centrifugal compressors[C]// Proceedings of Turbo Expo: Power for Land, Sea, and Air, Düsseldorf, Germany: ASME, 2014: V02DT42A042. [8] YI Weilin, JI Lucheng, TIAN Yong, et al. An aerodynamic design and numerical investigation of transonic centrifugal compressor stage[J]. Journal of Thermal Science, 2011, 20(3): 211-217. doi: 10.1007/s11630-011-0460-y [9] JEBIESHIA T R, RAMAN S K, KIM H D. Performance analysis of the impeller of a centrifugal air compressor[C]// Proceedings of Mechanics of Solids, Structures, and Fluids, Salt Lake City, US: ASME, 2019: V009T11A015. [10] 康达, 何卫东, 徐毅. 分流叶片长度和周向位置对高压比离心压气机性能的影响[J]. 推进技术, 2020, 41(12): 2709-2719. KANG Da, HE Weidong, XU Yi. Effects of splitter blade length and circumferential position on performance of high pressure ratio centrifugal compressor[J]. Journal of Propulsion Technology, 2020, 41(12): 2709-2719. (in ChineseKANG Da, HE Weidong, XU Yi. Effects of splitter blade length and circumferential position on performance of high pressure ratio centrifugal compressor[J]. Journal of Propulsion Technology, 2020, 41(12): 2709-2719. (in Chinese) [11] 刘瑞韬, 徐忠. 叶片数及分流叶片位置对压气机性能的影响[J]. 工程热物理学报, 2004, 25(2): 223-225. LIU Ruitao, XU Zhong. Effect of blade number and splitter blade position on the performance characteristic of the compressor[J]. Journal of Engineering Thermophysics, 2004, 25(2): 223-225. (in Chinese doi: 10.3321/j.issn:0253-231X.2004.02.012LIU Ruitao, XU Zhong. Effect of blade number and splitter blade position on the performance characteristic of the compressor[J]. Journal of Engineering Thermophysics, 2004, 25(2): 223-225. (in Chinese) doi: 10.3321/j.issn:0253-231X.2004.02.012 [12] 邵佳丰, 罗晨, 周怡君, 等. 离心压缩机分流叶片长度与周向位置优化设计[J]. 机械设计与制造, 2023(9): 32-36. SHAO Jiafeng, LUO Chen, ZHOU Yijun, et al. Optimization design of the length and circumferential position of centrifugal compressor splitter blades[J]. Machinery Design & Manufacture, 2023(9): 32-36. (in Chinese doi: 10.3969/j.issn.1001-3997.2023.09.007SHAO Jiafeng, LUO Chen, ZHOU Yijun, et al. Optimization design of the length and circumferential position of centrifugal compressor splitter blades[J]. Machinery Design & Manufacture, 2023(9): 32-36. (in Chinese) doi: 10.3969/j.issn.1001-3997.2023.09.007 [13] 顾云开, 刘艳, 张闯, 等. 高压比离心压气机参数化造型与分流叶片位置优化[J]. 工程热物理学报, 2024, 45(4): 1022-1030. GU Yunkai, LIU Yan, ZHANG Chuang, et al. Parametric modeling and the splitter location optimization of high pressure ratio centrifugal compressor[J]. Journal of Engineering Thermophysics, 2024, 45(4): 1022-1030. (in ChineseGU Yunkai, LIU Yan, ZHANG Chuang, et al. Parametric modeling and the splitter location optimization of high pressure ratio centrifugal compressor[J]. Journal of Engineering Thermophysics, 2024, 45(4): 1022-1030. (in Chinese) [14] 卜远远, 楚武利. 分流叶片周向位置对离心叶轮性能及内部流动的影响[J]. 流体机械, 2011, 39(9): 16-20, 44. BU Yuanyuan, CHU Wuli. Effect of the splitter blade position on the performance and the internal flow of centrifugal impeller[J]. Fluid Machinery, 2011, 39(9): 16-20, 44. (in ChineseBU Yuanyuan, CHU Wuli. Effect of the splitter blade position on the performance and the internal flow of centrifugal impeller[J]. Fluid Machinery, 2011, 39(9): 16-20, 44. (in Chinese) [15] MALIK A, ZHENG Qun, QURESHI S R, et al. Centrifugal compressor performance improvement through multi splitter impeller[J]. Polish Maritime Research, 2019, 26(2): 6-14. doi: 10.2478/pomr-2019-0020 [16] MALIK A, ZHENG Qun. Effect of double splitter blades position in a centrifugal compressor impeller[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2019, 233(6): 689-701. doi: 10.1177/0957650918792462 [17] XU C, AMANO R S. Centrifugal compressor performance improvements through impeller splitter location[J]. Journal of Energy Resources Technology, 2018, 140(5): 051201. doi: 10.1115/1.4037813 [18] EISENLOHR G, KRAIN H, RICHTER F A, et al. Investigations of the flow through a high pressure ratio centrifugal impeller[C]// Proceedings of Turbo Expo: Power for Land, Sea, and Air, New York, US: ASME, 2002: 649-657. [19] 马威, 王丹华, 陆利蓬. 提高Spalart-Allmaras湍流模型对分离模拟能力的研究[J]. 航空动力学报, 2008, 23(8): 1474-1479. MA Wei, WANG Danhua, LU Lipeng. Investigation on improving the capability of predicting separation of Spalart-Allmaras turbulence model[J]. Journal of Aerospace Power, 2008, 23(8): 1474-1479. (in ChineseMA Wei, WANG Danhua, LU Lipeng. Investigation on improving the capability of predicting separation of Spalart-Allmaras turbulence model[J]. Journal of Aerospace Power, 2008, 23(8): 1474-1479. (in Chinese) [20] KRAIN H, HOFFMANN B, PAK H. Aerodynamics of a centrifugal compressor impeller with transonic inlet conditions[M]. New York, US: AMSE, 1995. [21] 康顺, 孙丽萍. 叶根倒角对离心叶轮气动性能的影响[J]. 工程热物理学报, 2009, 30(1): 41-43. KANG Shun, SUN Liping. Influence of root fillet on the aerodynamic performance of centrifugal impeller[J]. Journal of Engineering Thermophysics, 2009, 30(1): 41-43. (in ChineseKANG Shun, SUN Liping. Influence of root fillet on the aerodynamic performance of centrifugal impeller[J]. Journal of Engineering Thermophysics, 2009, 30(1): 41-43. (in Chinese) [22] 康顺, 刘强, 祁明旭. 一个高压比离心叶轮的CFD结果确认[J]. 工程热物理学报, 2005, 26(3): 400-404. KANG Shun, LIU Qiang, QI Mingxu. Cfd validation of a high speed centrifugal compressor impeller[J]. Journal of Engineering Thermophysics, 2005, 26(3): 400-404. (in ChineseKANG Shun, LIU Qiang, QI Mingxu. Cfd validation of a high speed centrifugal compressor impeller[J]. Journal of Engineering Thermophysics, 2005, 26(3): 400-404. (in Chinese) [23] 陈杰, 何敏祥, 黄国平. 叶尖间隙对离心叶轮偏置分流叶片工作机理的影响[J]. 航空动力学报, 2016, 31(8): 1950-1956. CHEN Jie, HE Minxiang, HUANG Guoping. Effect of tip clearance on the operating mechanism of offset splitter blades in a centrifugal compressor[J]. Journal of Aerospace Power, 2016, 31(8): 1950-1956. (in ChineseCHEN Jie, HE Minxiang, HUANG Guoping. Effect of tip clearance on the operating mechanism of offset splitter blades in a centrifugal compressor[J]. Journal of Aerospace Power, 2016, 31(8): 1950-1956. (in Chinese) -
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