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吸力面前缘涡流发生器对压气机叶栅性能影响

徐文峰 邹世龙 孙丹 鲁文昕 任国哲 赵欢

徐文峰, 邹世龙, 孙丹, 等. 吸力面前缘涡流发生器对压气机叶栅性能影响[J]. 航空动力学报, 2024, 39(X):202230485 doi: 10.13224/j.cnki.jasp.20230485
引用本文: 徐文峰, 邹世龙, 孙丹, 等. 吸力面前缘涡流发生器对压气机叶栅性能影响[J]. 航空动力学报, 2024, 39(X):202230485 doi: 10.13224/j.cnki.jasp.20230485
XU Wenfeng, ZOU Shilong, SUN Dan, et al. Effect of suction leading edge vortex generator on characteristics of compressor cascade[J]. Journal of Aerospace Power, 2024, 39(X):202230485 doi: 10.13224/j.cnki.jasp.20230485
Citation: XU Wenfeng, ZOU Shilong, SUN Dan, et al. Effect of suction leading edge vortex generator on characteristics of compressor cascade[J]. Journal of Aerospace Power, 2024, 39(X):202230485 doi: 10.13224/j.cnki.jasp.20230485

吸力面前缘涡流发生器对压气机叶栅性能影响

doi: 10.13224/j.cnki.jasp.20230485
基金项目: 辽宁省教育厅基本科研青年项目(JYTQN2023069); 沈阳航空航天大学引进人才科研启动基金(23YB20); 国家自然科学基金(52075346)
详细信息
    作者简介:

    徐文峰(1993-),男,讲师,博士,主要从事航空发动机气动热力学研究。E-mail:xuwf789@163.com

    通讯作者:

    孙丹(1981-),男,教授,博士,主要从事透平机械先进密封技术研究。E-mail:phd_sundan@163.com

  • 中图分类号: V233.5

Effect of suction leading edge vortex generator on characteristics of compressor cascade

  • 摘要:

    以压气机平面叶栅实验件为研究对象,在叶栅端壁靠近吸力面前缘布置涡流发生器,来改善压气机静叶气动性能并控制角区分离流动。采用数值模拟的方法,研究不同高度、长度和节距位置的涡流发生器对角区分离流动和气动性能的影响。研究结果表明,吸力面前缘涡流发生器在通道进口端壁附近产生诱导涡,抑制角区低能流体聚集,使分离起始点后移,缩小角区沿着节距方向范围,降低流动损失。涡流发生器应设置在角区分离起始位置,角区分离控制效果随着涡流发生器高度的增高先增强后减弱,随着涡流发生器的弦长增加逐渐减弱,随着布置位置远离吸力面而先增强后减弱,当涡流发生器布置在端壁回流区与主流区交界线、弦长为25%叶片弦长、高度等于2%叶高时,叶栅流动损失减小10.3%。

     

  • 图 1  叶栅参数示意图

    Figure 1.  Cascade parameters diagram

    图 2  涡流发生器简图

    Figure 2.  Schematic diagram of an eddy current generator

    图 3  计算网格和边界

    Figure 3.  Computational mesh and boundary

    图 4  进口总压分布[29]

    Figure 4.  Inlet total pressure distribution [29]

    图 5  叶表y+值云图

    Figure 5.  Contours of y+ on blade surface

    图 6  网格无关性

    Figure 6.  Mesh Independence

    图 7  数值及实验结果[29]

    Figure 7.  Numerical and experimental result[29]

    图 8  不同高度方案对$ {\overline C _{{\text{pt}}}} $的影响

    Figure 8.  Effect of different height schemes on $ {\overline C _{{\text{pt}}}} $

    图 9  不同高度方案下Cpt 的径向分布

    Figure 9.  Radial distribution of Cpt values under different height schemes

    图 10  不同高度方案下叶根静压系数曲线

    Figure 10.  Static pressure coefficient curves of leaf roots under different height schemes

    图 11  不同高度方案端壁及吸力面极限流线和静压系数

    Figure 11.  Static pressure coefficient contour and limiting streamlines of the end wall and the suction under different height schemes

    图 12  不同高度方案下的三维涡系结构

    Figure 12.  Three-dimensional vortex structure under different height schemes

    图 13  不同弦长方案对$ {\overline C _{{\text{pt}}}} $的影响

    Figure 13.  Effect of different chord schemes on $ {\overline C _{{\text{pt}}}} $

    图 14  不同弦长方案下叶根静压系数曲线

    Figure 14.  Static pressure coefficient curve of leaf roots under different chord schemes

    图 15  不同弦长方案端壁及吸力面极限流线和静压系数

    Figure 15.  Static pressure coefficient contour and limiting streamlines of the end wall and the suction under different chord schemes

    图 16  不同弦长方案下的三维涡系结构

    Figure 16.  Three-dimensional vortex structure under different chord schemes

    图 17  不同位置方案对$ {\overline C _{{\text{pt}}}} $的影响

    Figure 17.  Effect of different location scheme on $ {\overline C _{{\text{pt}}}} $

    图 18  不同位置方案下Cpt径向分布

    Figure 18.  Radial distribution of Cpt under different location schemes

    图 19  原型方案以及方案9的出口总压损失、轴向涡量和二次流

    Figure 19.  Total pressure loss, axial vortex and secondary flow of the ORI and Case 9 outlet

    图 20  不同位置方案下的三维涡系结构

    Figure 20.  Three-dimensional vortex structure under different position schemes

    图 21  改型前后叶栅通道内涡系结构

    Figure 21.  Vortex structure in the cascade passage before and after modification

    表  1  叶栅几何参数

    Table  1.   Cascade geometry parameters

    参数数值
    弦长 c/mm40
    叶高 H/mm100
    节距 t/mm30
    安装角 γ/(°)60
    几何进口角 α/(°)46.23
    几何出口角 β/(°)76.93
    进口马赫数 Ma0.7
    下载: 导出CSV

    表  2  不同高度方案

    Table  2.   Different height schemes

    方案编号涡流发生器高度 h/mm
    11
    22
    33
    44
    55
    下载: 导出CSV

    表  3  不同弦长方案

    Table  3.   Different chord schemes

    方案编号涡流发生器弦长与叶片弦长之比
    20.50
    60.25
    70.75
    下载: 导出CSV

    表  4  不同位置方案

    Table  4.   Different location schemes

    方案编号 $ \overline {t_{}^{}} $/%
    6 5
    8 10
    9 15
    10 20
    11 25
    下载: 导出CSV
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  • 收稿日期:  2023-07-27
  • 网络出版日期:  2024-07-10

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