Study on control of severe corner separation in large-turning-angle diffuser cascades based on end-wall synthetic jets
-
摘要:
为改善大折转角扩压叶栅角区强分离状态，针对几何折转角68°的叶栅，系统探究了端壁合成射流在角区分离前缘、中部（回流点前/后）、后缘四种布置位置下的控制效果，并耦合射流角度、动量系数、激励频率这3个核心参数，深入分析了其对端壁附面层、分离泡及二次流结构的调控规律。研究结果表明：端壁合成射流可有效削弱角区分离，尤其是分离中部（回流点前）布置射流角度为30°的端壁合成射流可有效作用于分离泡核心区，破碎角区分离涡、阻断附面层迁移，总压损失系数最大降低20.27%，静压升系数提升13.07%；而分离前缘布置射流角度为30°的端壁合成射流可从源头削弱分离扩张，总压损失系数降低14.69%，静压升系数提升9.66%；而分离中部（回流点后）、后缘控制效果有限。通过提出角区分离全演化阶段控制策略，揭示了射流与分离阶段的适配机制，为大折转角扩压叶栅气动性能优化提供了一种路径。
Abstract:To mitigate severe corner separation in large-turning-angle diffuser cascades, this study systematically investigated the control effects of endwall synthetic jets on a cascade with a geometric turning angle of 68°. The jets were arranged at four distinct positions: the leading edge, mid-section (encompassing the locations anterior and posterior to the separation reattachment point), and trailing edge of corner separation. By coupling three core control parameters—jet angle, momentum coefficient, and excitation frequency, this study elucidated the modulation mechanisms of synthetic jets on the endwall boundary layer, separation bubble, and complex secondary flow structures. The results indicated that end-wall synthetic jets can effectively weaken corner separation. Specifically, the end-wall synthetic jet arranged at the middle region of the separation (before the reattachment point) with a jet angle of 30° can effectively act on the core area of the separation bubble, break up the corner separation vortex, and block the boundary layer migration. This configuration achieved a maximum reduction of 20.27% in total pressure loss coefficient and an increase of 13.07% in static pressure rise coefficient. In contrast, the end-wall synthetic jet placed at the leading edge of the separation with the same jet angle of 30° inhibited the separation expansion from the source, resulting in a 14.69% reduction in total pressure loss coefficient and a 9.66% increase in static pressure rise coefficient. However, the end-wall synthetic jets arranged at the middle region of the separation (after the reattachment point) and the trailing edge exhibited limited control effects. The study proposed a control strategy covering the entire evolution stage of corner separation, and revealed the adaptation mechanism between synthetic jets and separation stages, offering an approach to optimize the aerodynamic performance of large-turning-angle diffuser cascades.
-
图 1 端壁合成射流激励器布置位置示意图
Figure 1. Schematic diagram of arrangement positions of end-wall synthetic jet actuators
图 2 大折转角扩压叶栅计算域网格
Figure 2. Computational domain mesh of the large-turning-angle diffuser cascade
图 5 叶栅壁面极限流向切应力云图及端壁射流控制方案（侧视图）
Figure 5. Contour of limiting streamwise shear stress on cascade wall and endwall jet control scheme （side view）
图 7 不同射流位置下端壁及吸力面壁面极限时均流线图（$ {C}_{\text{u}} $=0.91%，f=600 Hz）
Figure 7. Time-averaged streamline diagrams of wall limiting on endwall and suction surface under different jet positions （$ {C}_{\text{u}} $=0.91%, f=600 Hz）
图 8 不同射流位置下角区时均总压损失系数云图（$ {C}_{\text{u}} $=0.91%，f=600 Hz）
Figure 8. Time-averaged total pressure loss contour maps in the corner region under different jet positions （$ {C}_{\text{u}} $=0.91%, f=600 Hz）
图 9 不同射流位置下时均马赫数的Q值云图（$ {C}_{\text{u}} $=0.91%，f=600 Hz，Q=2×104）
Figure 9. Q-value contour maps of time-averaged Mach number under different jet positions （$ {C}_{\text{u}} $=0.91%, f=600 Hz, Q=2×104）
图 10 不同射流位置下不同相对叶高的时均总压损失系数（SJ2_30d，$ {C}_{\text{u}} $=0.91%，f=600 Hz）
Figure 10. Total pressure loss coefficients at different relative blade heights under different jet positions （SJ2_30d, $ {C}_{\text{u}} $=0.91%, f=600 Hz）
图 11 不同动量系数的总压损失系数偏移量
Figure 11. Total pressure loss offset under different momentum coefficients
图 12 不同动量系数的静压升系数偏移量
Figure 12. Static pressure rise offset under different momentum coefficients
图 13 不同动量系数下SJ1控制方案的时均湍动能云图
Figure 13. Time-averaged turbulent kinetic energy contours of the SJ1 control scheme at various momentum coefficients
图 14 不同动量系数下不同相对叶高的总压损失系数
Figure 14. Total pressure loss coefficient at different relative blade heights under various momentum coefficients
图 15 不同动量系数下的40%及60%轴向弦长处时均总压损失系数云图及其流线图
Figure 15. Time-averaged total pressure loss contour maps and streamline diagrams at 40% and 60% relative blade heights under different momentum coefficients
图 16 不同激励频率的总压损失系数偏移量
Figure 16. Total pressure loss offset under different excitation frequencies
图 17 不同激励频率的静压升系数偏移量
Figure 17. Static pressure rise offset under different excitation frequencies
图 18 SJ2不同激励频率的时均总压损失系数
Figure 18. Time-averaged total pressure loss coefficients of SJ2 under different excitation frequencies
图 19 SJ2布置方案下不同射流角度的总压损失系数偏移量
Figure 19. Total pressure loss offset under different jet angles for the SJ2 arrangement scheme
图 20 SJ2布置方案下不同射流角度的静压升系数偏移量
Figure 20. Static pressure rise offset under different jet angles for the SJ2 arrangement scheme
图 21 SJ2控制方案下不同射流角度时均轴向涡量云图
Figure 21. Time-averaged axial vorticity contour maps under different jet angles for the SJ2 control scheme
图 22 SJ2控制方案下不同射流角度时均总压损失系数云图
Figure 22. Time-averaged total pressure loss contour maps under different jet angles for the SJ2 control scheme
表 1 大折转角扩压叶栅几何参数
Table 1. Geometric parameters of large-turning-angle diffuser cascades
参数 数值 弦长$ L/\text{mm} $ 100 叶高$ H/\text{mm} $ 100 安装角$ {\beta }_{y} $/（°） 68.8 几何折转角β/（°） 68 稠度$ \sigma $ 1.538 
下载: 导出CSV
-
[1] 曾纯. 皇冠上的明珠[J]. 中国工业评论, 2016(11): 2. Zeng Chun. The jewel in the crown[J]. China Industry Review, 2016(11): 2. (in ChineseZeng Chun. The jewel in the crown[J]. China Industry Review, 2016(11): 2. (in Chinese) [2] 周拜豪, 张少平, 黄萍, 等. 压气机气动设计发展与思考[J]. 燃气涡轮试验与研究, 2025, 38(2): 45-57. Zhou Baihao, Zhang Shaoping, Huang Ping, et al. Evolution and perspectives in compressor aerodynamic design[J]. Gas Turbine Experiment and Research, 2025, 38(2): 45-57. (in Chinese doi: 10.3724/j.GTER.20250032Zhou Baihao, Zhang Shaoping, Huang Ping, et al. Evolution and perspectives in compressor aerodynamic design[J]. Gas Turbine Experiment and Research, 2025, 38(2): 45-57. (in Chinese) doi: 10.3724/j.GTER.20250032 [3] 曹志鹏, 赵龙波, 关朝斌, 等. 轴流压气机新技术探讨[J]. 航空动力, 2023(6): 65-69. Cao Zhipeng, Zhao Longbo, Guan Chaobin, et al. New technologies for axial compressor[J]. Aerospace Power, 2023(6): 65-69. (in ChineseCao Zhipeng, Zhao Longbo, Guan Chaobin, et al. New technologies for axial compressor[J]. Aerospace Power, 2023(6): 65-69. (in Chinese) [4] Hergt A, Meyer R, Liesner K, et al. A new approach for compressor endwall contouring[C]//Proceeding of ASME Turbo Expo: Turbine Technical Conference and Exposition: Vancouver, Canada: ASME, 2011: 177-186. [5] Li Zhiyuan, Du Juan, Jemcov A, et al. A study of loss mechanism in a linear compressor cascade at the corner stall condition[C]//Proceeding of ASME Turbo Expo: Turbomachinery Technical Conference and Exposition. Charlotte, US: ASME, 2017: V02AT39A044. [6] Camp T R, Day I J. A study of spike and modal stall phenomena in a low-speed axial compressor [C]//Proceeding of ASME International Gas Turbine and Aeroengine Congress and Exhibition. Orlando, US: ASME, 1997: V001T03A109. [7] 刘华坪, 陈焕龙, 杨晓光, 等. 基于耗散函数的低速扩压叶栅损失机理探讨[J]. 航空动力学报, 2011, 26(2): 289-296. Liu Huaping, Chen Huanlong, Yang Xiaoguang, et al. Study of loss mechanism in low speed compressor cascade using dissipation function[J]. Journal of Aerospace Power, 2011, 26(2): 289-296. (in ChineseLiu Huaping, Chen Huanlong, Yang Xiaoguang, et al. Study of loss mechanism in low speed compressor cascade using dissipation function[J]. Journal of Aerospace Power, 2011, 26(2): 289-296. (in Chinese) [8] 田思濛, 吴云, 张海灯, 等. 基于能量耗散率的低速扩压叶栅损失研究[J]. 航空学报, 2015, 36(10): 3249-3262. Tian Simeng, Wu Yun, Zhang Haideng, et al. Energy loss in a low-speed compressor cascade with dissipation function[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(10): 3249-3262. (in ChineseTian Simeng, Wu Yun, Zhang Haideng, et al. Energy loss in a low-speed compressor cascade with dissipation function[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(10): 3249-3262. (in Chinese) [9] 吴艳辉, 王博, 付裕, 等. 轴流压气机角区分离的研究进展[J]. 航空学报, 2017, 38(9): 520974. Wu Yanhui, Wang Bo, Fu Yu, et al. Research progress of corner separation in axial-flow compressor[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(9): 520974. (in ChineseWu Yanhui, Wang Bo, Fu Yu, et al. Research progress of corner separation in axial-flow compressor[J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(9): 520974. (in Chinese) [10] Sun Shuxian, Zhou Ling, Zhu Yichen, et al. PIV investigation on corner separation control in a compressor cascade based on a vortex generator[J]. Journal of Visualization, 2024, 27(2): 159-175. doi: 10.1007/s12650-024-00962-6 [11] 杨凌, 陈韵之, 钟兢军. 不同形状吸力面翼刀对叶栅二次流及性能的影响[J]. 工程热物理学报, 2022, 43(1): 50-57. Yang Ling, Chen Yunzhi, Zhong Jingjun. Effects of suction surface fences with different profiles on secondary flow and performance of compressor cascade[J]. Journal of Engineering Thermophysics, 2022, 43(1): 50-57. (in ChineseYang Ling, Chen Yunzhi, Zhong Jingjun. Effects of suction surface fences with different profiles on secondary flow and performance of compressor cascade[J]. Journal of Engineering Thermophysics, 2022, 43(1): 50-57. (in Chinese) [12] 王博, 吴艳辉, 黄令举, 等. 基于端壁L形凹槽的扩压叶栅角区分离控制[J]. 航空学报, 2024, 45(10): 129206. Wang Bo, Wu Yanhui, Huang Lingju, et al. Corner separation control in compressor cascade based on L-shaped endwall groove[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 129206. (in Chinese doi: 10.7527/S1000-6893.2023.29206Wang Bo, Wu Yanhui, Huang Lingju, et al. Corner separation control in compressor cascade based on L-shaped endwall groove[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 129206. (in Chinese) doi: 10.7527/S1000-6893.2023.29206 [13] 孙槿静, 柳阳威, 陆利蓬, 等. 根部开槽对叶栅三维角区分离的控制研究[J]. 工程热物理学报, 2019, 40(12): 2769-2776. Sun Jinjing, Liu Yangwei, Lu Lipeng, et al. Control of corner separation by slot at the root of the blade[J]. Journal of Engineering Thermophysics, 2019, 40(12): 2769-2776. (in ChineseSun Jinjing, Liu Yangwei, Lu Lipeng, et al. Control of corner separation by slot at the root of the blade[J]. Journal of Engineering Thermophysics, 2019, 40(12): 2769-2776. (in Chinese) [14] Lu Huawei, Yang Yi, Guo Shuang, et al. Control of corner separation via dimpled surface for a highly loaded compressor cascade under different inlet Mach number[J]. Aerospace Science and Technology, 2019, 85: 48-60. doi: 10.1016/j.ast.2018.11.054 [15] 刘晓波, 陈涛, 周蜜. 主动流动控制技术的发展与应用展望[J]. 空天技术, 2023(5): 54-62, 71. Liu Xiaobo, Chen Tao, Zhou Mi. Development status and application prospect of the active flow control technology[J]. Aerospace Technology, 2023(5): 54-62, 71. (in Chinese doi: 10.16338/j.issn.2097-0714.20230121Liu Xiaobo, Chen Tao, Zhou Mi. Development status and application prospect of the active flow control technology[J]. Aerospace Technology, 2023(5): 54-62, 71. (in Chinese) doi: 10.16338/j.issn.2097-0714.20230121 [16] Zhang Haideng, Yu Xianjun, Liu Baojie, et al. Control of corner separation with plasma actuation in a high-speed compressor cascade[J]. Applied Sciences, 2017, 7(5): 465. doi: 10.3390/app7050465 [17] 梁作召, 孙鹏, 李晓东, 等. 端壁自适应射流出口位置对高速扩压叶栅角区分离的影响[J]. 航空动力学报, 2025, 40(3): 20230325. Liang Zuozhao, Sun Peng, Li Xiaodong, et al. Effects of outlet position on corner separation of high speed compressor cascade with endwall self-adaptive injection[J]. Journal of Aerospace Power, 2025, 40(3): 20230325. (in Chinese doi: 10.13224/j.cnki.jasp.20230325Liang Zuozhao, Sun Peng, Li Xiaodong, et al. Effects of outlet position on corner separation of high speed compressor cascade with endwall self-adaptive injection[J]. Journal of Aerospace Power, 2025, 40(3): 20230325. (in Chinese) doi: 10.13224/j.cnki.jasp.20230325 [18] Liu Yangwei, Sun Jinjing, Lu Lipeng. Corner separation control by boundary layer suction applied to a highly loaded axial compressor cascade[J]. Energies, 2014, 7(12): 7994-8007. doi: 10.3390/en7127994 [19] Yang Pengcheng, Chen Shaowen, Liu Guanyu, et al. Corner separation control using sweeping jet actuator in a compressor cascade[J]. Journal of Turbomachinery, 2024, 146(10): 104503. doi: 10.1115/1.4065412 [20] Zhu Yinxin, Peng Wenqiang, Luo Zhenbing, et al. Trailing-edge shock loss control with self-sustaining synthetic jet in a supersonic compressor cascade[J]. Chinese Journal of Aeronautics, 2023, 36(7): 366-377. doi: 10.1016/j.cja.2023.04.006 [21] 刘华坪, 卢炳潇. 射流旋涡发生器对高速扩压叶栅端区流动的影响[J]. 工程热物理学报, 2016, 37(8): 1663-1668. Liu Huaping, Lu Bingxiao. End-wall flow control in a high speed compressor cascade using vortex generator jet[J]. Journal of Engineering Thermophysics, 2016, 37(8): 1663-1668. (in ChineseLiu Huaping, Lu Bingxiao. End-wall flow control in a high speed compressor cascade using vortex generator jet[J]. Journal of Engineering Thermophysics, 2016, 37(8): 1663-1668. (in Chinese) [22] 杨宗豪, 刘波, 茅晓晨, 等. 脉冲型流体振荡器射流对叶栅角区分离的控制研究[J]. 推进技术, 2024, 45(7): 2307040. Yang Zonghao, Liu Bo, Mao Xiaochen, et al. Control of cascade corner separation by pulsed fluid oscillator jet[J]. Journal of Propulsion Technology, 2024, 45(7): 2307040. (in Chinese doi: 10.13675/j.cnki.tjjs.2307040Yang Zonghao, Liu Bo, Mao Xiaochen, et al. Control of cascade corner separation by pulsed fluid oscillator jet[J]. Journal of Propulsion Technology, 2024, 45(7): 2307040. (in Chinese) doi: 10.13675/j.cnki.tjjs.2307040 [23] 朱寅鑫, 彭文强, 罗振兵, 等. 全叶高合成双射流对大折转角扩压叶栅的影响[J]. 航空学报, 2023, 44(12): 127734. Zhu Yinxin, Peng Wenqiang, Luo Zhenbing, et al. Influence of full-span dual synthetic jets on high-turning compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(12): 127734. (in ChineseZhu Yinxin, Peng Wenqiang, Luo Zhenbing, et al. Influence of full-span dual synthetic jets on high-turning compressor cascade[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(12): 127734. (in Chinese) [24] 贾俊. 压气机合成射流的流动控制机理[D]. 哈尔滨: 哈尔滨工业大学, 2018. Jia Jun. Flow control mechanism of synthetic jet in a low-reaction compressor cascade[D]. Harbin: Harbin Institute of Technology, 2018. (in ChineseJia Jun. Flow control mechanism of synthetic jet in a low-reaction compressor cascade[D]. Harbin: Harbin Institute of Technology, 2018. (in Chinese) [25] 罗振兵, 夏智勋. 合成射流技术及其在流动控制中应用的进展[J]. 力学进展, 2005, 35(2): 221-234. Luo Zhenbing, Xia Zhixun. Advances in synthetic jet technology and applications in flow control[J]. Advances in Mechanics, 2005, 35(2): 221-234. (in ChineseLuo Zhenbing, Xia Zhixun. Advances in synthetic jet technology and applications in flow control[J]. Advances in Mechanics, 2005, 35(2): 221-234. (in Chinese) [26] Zander V, Dobriloff C, Lumpe M, et al. Wall shear stress measurements on a highly loaded compressor cascade[J]. Journal of Turbomachinery, 2013, 135: 011020. doi: 10.1115/1.4006333 -
点击查看大图
计量
- 文章访问数: 72
- HTML浏览量: 67
- PDF量: 9
- 被引次数: 0