进口附面层条件对压气机串列叶栅端区流动特性的影响

茅晓晨; 焦英辰; 杨宗豪

doi:10.13224/j.cnki.jasp.20220668

进口附面层条件对压气机串列叶栅端区流动特性的影响

doi: 10.13224/j.cnki.jasp.20220668

茅晓晨^{1, 2,},
焦英辰^{1, 2},
杨宗豪^{1, 2}

1.
西北工业大学动力与能源学院，西安 710129
2.
西北工业大学翼型、叶栅空气动力学国家级重点实验室，西安 710129

基金项目: 国家自然科学基金青年项目（52106057）；引智计划（B17037）；中央高校基本科研业务费（D5000210483）；翼型、叶栅空气动力学国家级重点实验室基金（D5150210006，D5050210015）；气动院流动显示与测量重点实验室基金（D5110220177）

详细信息

作者简介:
茅晓晨（1989-），男，副教授，博士，主要从事叶轮机械气动热力学研究。E-mail：maoxiao_chen@nwpu.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2022-09-07
- 网络出版日期: 2024-12-04

Effect of inlet boundary layer condition on the flow characteristics at endwall region of a compressor tandem cascade

MAO Xiaochen^{1, 2
,},
JIAO Yingchen^{1, 2},
YANG Zonghao^{1, 2}

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China
2.
The National Key Laboratory of Aerodynamic Design and Research，Northwestern Polytechnical University，Xi’an 710129，China

摘要

摘要:
进口附面层（IBL）条件对压气机内部流动特性具有显著影响，为探究其对高负荷压气机串列叶栅端区流动特性的影响，采用定常数值方法对某高亚声速压气机串列叶栅流场进行计算，并研究了不同进口条件，包括附面层厚度及常规和倾斜两种形式对叶尖泄漏和角区分离两种流动结构的影响，结果表明：在无叶尖间隙时，进口附面层增厚会使角区分离在前叶的三维尺度以及后叶的周向范围增大，附面层倾斜效应使前叶二次流削弱而后叶二次流增强，总压损失降低，且进口附面层厚度增大使倾斜效应对角区流动的影响降低。1%叶高间隙下，增大附面层厚度使泄漏涡的展向尺度增大，附面层倾斜效应则使前叶泄漏涡增强，后叶泄漏涡减弱，总压损失减小，而进口附面层厚度增加使倾斜效应对叶尖端区流动的影响增强。
- 串列叶栅 /
- 进口附面层 /
- 倾斜附面层 /
- 叶尖泄漏流 /
- 角区分离
Abstract:
Inlet boundary layer (IBL) condition can make a significant effect on the flow condition in the compressors. In order to explore the effect of IBL condition on the flow characteristics at the endwall region of the highly loaded compressor tandem cascade, a steady numerical method was used to calculate the flow field of a high subsonic tandem cascade, and comparatively analyze the effects of different IBL conditions, including thickness and form (normal and skewed), on the corner separation and tip leakage flow characteristics. The results showed that: without tip clearance, increasing the IBL thickness could increase the three-dimensional corner separation range from the front blade and the circumferential range of the rear blade. The skewed IBL weakened the secondary flow in the front blade passage but enhanced the secondary flow in the rear blade passage, the total pressure loss decreased and the effect of the skewed IBL on corner flow was weakened with the increase of IBL thickness. With 1% blade height clearance, increasing the IBL thickness could increase the scale of the leakage vortex in spanwise direction and the skewed IBL could enhance the leakage vortex of the front blade but weaken the leakage vortex of the rear blade, the total pressure loss decreased but the effect of the skewed IBL on tip flow was enhanced with the increase of IBL thickness.
- tandem cascade /
- inlet boundary layer /
- skewed boundary layer /
- tip leakage flow /
- corner separation

HTML

图 1 串列叶型和原始叶型的二维平面示意图

Figure 1. Two-dimensional blade profile of original cascade and tandem cascade

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图 2 串列叶栅的数值计算域

Figure 2. Computational domain of the tandem cascade

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图 3 倾斜附面层原理示意图及条件设置

Figure 3. Principle and setting of the skewed IBL

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图 4 带间隙串列叶栅的网格无关性验证

Figure 4. Grid independence validation for the tandem cascade with tip gap

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图 5 串列叶栅的网格示意图

Figure 5. Meshes of the tandem cascade

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图 6 原始叶栅实验数据与数值计算结果的对比

Figure 6. Comparison between the simulation and experimental results of the original cascade

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图 7 串列叶栅吸力面静压云图和极限流线图

Figure 7. Static pressure contours and limiting streamlines on the tandem cascade suction surface

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图 8 串列叶栅端壁极限流线图

Figure 8. Limiting streamlines on the endwall of tandem cascade

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图 9 串列叶栅通道内的Q等值面（Q=8×10⁷ s⁻²）

Figure 9. Q isosurfaces in the tandem cascade passage （ Q=8×10⁷ s⁻²）

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图 10 不同截面处串列叶栅的轴向涡量云图

Figure 10. Tandem cascade axial vorticity contours on the different planes

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图 11 1%叶高处C_p沿轴向弦长的分布

Figure 11. C_p distributions along the axial chord at the1% blade span

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图 12 两种附面层条件下串列叶栅不同截面处的展向速度云图和流线图

Figure 12. Spanwise velocity contours and streamlines on the different planes of the tandem cascade for the two IBL conditions

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图 13 4种附面层条件下出口气流角的展向分布

Figure 13. Spanwise distributions of the outlet flow angle or the four IBL conditions

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图 14 串列叶栅总压损失系数云图

Figure 14. Loss coefficient contours of the tandem cascade

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图 15 4种工况下串列叶栅总压损失系数的展向分布

Figure 15. Spanwise distributions of tandem cascade total pressure loss coefficient for the four IBL conditions

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图 16 串列叶栅（无间隙）总压损失系数对比

Figure 16. Tandem cascade total pressure loss coefficient comparison （without tip）

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图 17 4种附面层条件下串列叶栅的吸力面静压云图及局部放大图

Figure 17. Tandem cascade static pressure contours and partial enlarged view on suction surface for the four IBL conditions

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图 18 串列叶栅端壁极限流线以及静压等值线云图

Figure 18. Tandem cascade static pressure isolines contours and limiting streamlines on the endwall

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图 19 两种附面层条件下叶栅通道内的涡系结构（Q=8×10⁷ s⁻²）

Figure 19. Vortex structures of the tandem cascade for the two IBL conditions （Q=8×10⁷ s⁻²）

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图 20 两组附面层条件下串列叶栅在不同截面处的轴向涡量云图

Figure 20. Tandem cascade axial vorticity contours on the different planes for the two IBL conditions

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图 21 1%叶高处C_p沿轴向弦长的分布

Figure 21. C_p distributions along the axial chord at the1% blade span

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图 22 4种附面层条件下出口气流角的展向分布

Figure 22. Spanwise distributions of the outlet flow angle for the four IBL conditions

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图 23 4种附面层条件下串列叶栅总压损失系数的分布云图

Figure 23. Tandem cascade total pressure loss coefficient contours for the four IBL conditions

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图 24 4种附面层条件下串列叶栅总压损失系数展向分布

Figure 24. Spanwise distributions of tandem cascade total pressure loss coefficient for the four IBL conditions

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图 25 串列叶栅（带间隙）总压损失系数对比

Figure 25. Tandem cascade （with tip） total pressure loss coefficient comparison

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表 1 串列叶栅的匹配参数

Table 1. Configuration parameters of tandem cascade

配置参数	定义	取值
轴向重叠度	d_Z/C_Z	0
节距比例	t/S	0.9
弯角比	（β₂₁−β₂₂）/（ β₁₁−β₁₂）	2.3
弦长比	C_rb/C_fb	1
后叶近似攻角/（°）	β₁₂−β₂₁	−6

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参考文献(24)

[1]	GBADEBO S A,CUMPSTY N A,HYNES T P. Control of three-dimensional separations in axial compressors by tailored boundary layer suction[J]. Journal of Turbomachinery,2008,130(1): 011004. doi: 10.1115/1.2749294
[2]	BIOLLO R,BENINI E. Recent advances in transonic axial compressor aerodynamics[J]. Progress in Aerospace Sciences,2013,56: 1-18. doi: 10.1016/j.paerosci.2012.05.002
[3]	SAHA U K,ROY B. Experimental investigations on tandem compressor cascade performance at low speeds[J]. Experimental Thermal and Fluid Science,1997,14(3): 263-276. doi: 10.1016/S0894-1777(96)00125-2
[4]	MCGLUMPHY J,NG W F,WELLBORN S R,et al. Numerical investigation of tandem airfoils for subsonic axial-flow compressor blades[J]. Journal of Turbomachinery,2009,131(2): 021018. doi: 10.1115/1.2952366
[5]	邓向阳. 压气机叶顶间隙流的数值模拟研究[D]. 北京: 中国科学院工程热物理研究所,2006. DENG Xiangyang. Numerical simulation of compressor tip clearance flow[D]. Beijing: Institute of Engineering Thermophysics,Chinese Academy of Sciences,2006. (in Chinese DENG Xiangyang. Numerical simulation of compressor tip clearance flow[D]. Beijing: Institute of Engineering Thermophysics, Chinese Academy of Sciences, 2006. (in Chinese)
[6]	GAO F. Advanced numerical simulation of corner separation in a linear compressor cascade[D]. Lyon: Ecole Centrale de Lyon,2014.
[7]	张燕峰. 高载荷压气机端壁流动及其控制策略研究[D]. 西安: 西北工业大学,2010. ZHANG Yanfeng. Investigation of endwall flow behaviour and its control strategies in highly-loaded compressor[D]. Xi’an: Northwestern Polytechnic University,2010. (in Chinese ZHANG Yanfeng. Investigation of endwall flow behaviour and its control strategies in highly-loaded compressor[D]. Xi’an: Northwestern Polytechnic University, 2010. (in Chinese)
[8]	郭爽,宋彦萍,陆华伟,等. 来流附面层对大转角扩压叶栅气动性能的影响[J]. 工程热物理学报,2011,32(10): 1661-1664. GUO Shuang,SONG Yanping,LU Huawei,et al. Effects of inlet boundary layer on aerodynamic performance of a high-turning compressor cascade[J]. Journal of Engineering Thermophysics,2011,32(10): 1661-1664. (in Chinese GUO Shuang, SONG Yanping, LU Huawei, et al. Effects of inlet boundary layer on aerodynamic performance of a high-turning compressor cascade[J]. Journal of Engineering Thermophysics, 2011, 32(10): 1661-1664. (in Chinese)
[9]	茅晓晨,杨宗豪,刘波,等. 进口附面层对串列叶栅气动性能的影响研究[J]. 推进技术,2023,44(1): 105-115. MAO Xiaochen,YANG Zonghao,LIU Bo,et al. Effects of inlet boundary layer on aerodynamic performance of tandem cascade[J]. Journal of Propulsion Technology,2023,44(1): 105-115. (in Chinese MAO Xiaochen, YANG Zonghao, LIU Bo, et al. Effects of inlet boundary layer on aerodynamic performance of tandem cascade[J]. Journal of Propulsion Technology, 2023, 44(1): 105-115. (in Chinese)
[10]	BOEHLE M,STARK U. A numerical investigation of the effect of end-wall boundary layer skew on the aerodynamic performance of a low aspect ratio,high turning compressor cascade[C]//Proceedings of ASME 2007 International Mechanical Engineering Congress and Exposition,2009: 555-564.
[11]	BODE C,HOFFMANN J,STARK U. Effects of a skewed inlet boundary layer on the aerodynamic performance of a stator-hub equivalent high-turning compressor cascade[C]//Proceedings of ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition,2016.
[12]	李相君. 高负荷轴流压气机端区流动机制及被动控制[D]. 西安: 西北工业大学,2018. LI Xiangjun. Flow mechanism and passive control of high-load axial compressor end region[D]. Xi’an: Northwestern Polytechnical University,2018. (in Chinese LI Xiangjun. Flow mechanism and passive control of high-load axial compressor end region[D]. Xi’an: Northwestern Polytechnical University, 2018. (in Chinese)
[13]	茅晓晨,焦英辰,杨宗豪. 进口附面层形式对压气机叶栅端区流动特性的影响研究[J]. 工程热物理学报,2023,44(12): 3229-3236. MAO Xiaochen,JIAO Yingchen,YANG Zonghao. Research on the influence of inlet boundary layer on the flow characteristics in the end region of the compressor cascade[J]. Journal of Engineering Thermophysics,2023,44(12): 3229-3236. (in Chinese MAO Xiaochen, JIAO Yingchen, YANG Zonghao. Research on the influence of inlet boundary layer on the flow characteristics in the end region of the compressor cascade[J]. Journal of Engineering Thermophysics, 2023, 44(12): 3229-3236. (in Chinese)
[14]	魏巍,刘波,李俊. 大弯角串列叶栅间隙效应数值研究[J]. 航空工程进展,2013,4(4): 443-449. WEI Wei,LIU Bo,LI Jun. Numerical study on the clearance effects of a high-turning tandem cascade[J]. Advances in Aeronautical Science and Engineering,2013,4(4): 443-449. (in Chinese doi: 10.3969/j.issn.1674-8190.2013.04.009 WEI Wei, LIU Bo, LI Jun. Numerical study on the clearance effects of a high-turning tandem cascade[J]. Advances in Aeronautical Science and Engineering, 2013, 4(4): 443-449. (in Chinese) doi: 10.3969/j.issn.1674-8190.2013.04.009
[15]	周正贵,吴国钏,阮立群. 采用平面叶栅模拟压气机动叶叶尖间隙流[J]. 航空学报,2002,23(1): 69-71. ZHOU Zhenggui,WU Guochuan,RUAN Liqun. Experimental investigation of compressor rotor tip leakage flow by using a linear cascade[J]. Acta Aeronautica et Astronautica Sinica,2002,23(1): 69-71. (in Chinese doi: 10.3321/j.issn:1000-6893.2002.01.013 ZHOU Zhenggui, WU Guochuan, RUAN Liqun. Experimental investigation of compressor rotor tip leakage flow by using a linear cascade[J]. Acta Aeronautica et Astronautica Sinica, 2002, 23(1): 69-71. (in Chinese) doi: 10.3321/j.issn:1000-6893.2002.01.013
[16]	吴艳辉,楚武利,刘志伟. 移动壁对压气机叶栅间隙流动的影响[J]. 航空动力学报,2006,21(1): 112-118. WU Yanhui,CHU Wuli,LIU Zhiwei. Influence of moving end-wall on tip clearance flow in an axial-flow compressor cascade[J]. Journal of Aerospace Power,2006,21(1): 112-118. (in Chinese doi: 10.3969/j.issn.1000-8055.2006.01.021 WU Yanhui, CHU Wuli, LIU Zhiwei. Influence of moving end-wall on tip clearance flow in an axial-flow compressor cascade[J]. Journal of Aerospace Power, 2006, 21(1): 112-118. (in Chinese) doi: 10.3969/j.issn.1000-8055.2006.01.021
[17]	LI Xiangjun,CHU Wuli,WU Yanhui. Numerical investigation of inlet boundary layer skew in axial-flow compressor cascade and the corresponding non-axisymmetric end wall profiling[J]. Proceedings of the Institution of Mechanical Engineers,Part A: Journal of Power and Energy,2014,228(6): 638-656. doi: 10.1177/0957650914532264
[18]	LI Zhihui,ZHENG Xinqian,LIU Yanming,et al. The effect of end wall boundary layer on matching and corresponding flow control technique for multistage axial compressor[J]. Proceedings of the Institution of Mechanical Engineers,Part G: Journal of Aerospace Engineering,2016,230(12): 2179-2194. doi: 10.1177/0954410015621928
[19]	ZHENG Xinqian,YANG Heli. End-wall boundary layers and blockages of multistage axial compressors under different conditions[J]. Journal of Propulsion and Power,2017,33(4): 908-916. doi: 10.2514/1.B36251
[20]	CHEN P P,LIESNER K,MEYER R,et al. Effect of inflow variations on compressor secondary flow behavior[R]. Gliwice,Poland: Polish Fluid Mechanics Conference,2012.
[21]	HERGT A,MEYER R,LIESNER K,et al. A new approach for compressor endwall contouring[R]. ASME Paper,GT2011-45858,2011.
[22]	MEYER R,BECHERT D W,HAGE W. Secondary flow control oncompressor blades to improve the performance of axial turbomachines[R]. Prag Tschechische,Republik: Proceedings 5th European Conference on Turbomachinery,2003.
[23]	TESCH A,LANGE M,VOGELER K,et al. An experimental investigation of a tandem stator flow characteristic in a low speed axial research compressor[R]. Düsseldorf,Germany: American Society of Mechanical Engineers,2014.
[24]	KUMAR A,PRADEEP A M. Performance evaluation of a tandem rotor under design and off-design operation[R]. ASME Paper,GT2018-75478,2018.