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轴流压气机叶片与机匣处理一体化优化设计

范忠岗 巴顿 邱佳慧 杨晨 杜娟

范忠岗, 巴顿, 邱佳慧, 等. 轴流压气机叶片与机匣处理一体化优化设计[J]. 航空动力学报, 2024, 39(7):20220069 doi: 10.13224/j.cnki.jasp.20220069
引用本文: 范忠岗, 巴顿, 邱佳慧, 等. 轴流压气机叶片与机匣处理一体化优化设计[J]. 航空动力学报, 2024, 39(7):20220069 doi: 10.13224/j.cnki.jasp.20220069
FAN Zhonggang, BA Dun, QIU Jiahui, et al. Integrated design optimization of blade and casing treatment in axial compressor[J]. Journal of Aerospace Power, 2024, 39(7):20220069 doi: 10.13224/j.cnki.jasp.20220069
Citation: FAN Zhonggang, BA Dun, QIU Jiahui, et al. Integrated design optimization of blade and casing treatment in axial compressor[J]. Journal of Aerospace Power, 2024, 39(7):20220069 doi: 10.13224/j.cnki.jasp.20220069

轴流压气机叶片与机匣处理一体化优化设计

doi: 10.13224/j.cnki.jasp.20220069
基金项目: 国家自然科学基金(51922098); 国家重大科技专项(2017-Ⅱ-0004-0017,J2019-Ⅱ-0020-0041)
详细信息
    作者简介:

    范忠岗(1998-),男,博士生,主要从事压气机流动稳定性研究

    通讯作者:

    杜娟(1983-),女,研究员,博士,主要从事压气机内部流动失稳机理、稳定性调控策略及实验测量方面研究。E-mail:dujuan@iet.cn

  • 中图分类号: V231.3

Integrated design optimization of blade and casing treatment in axial compressor

  • 摘要:

    针对一台低速轴流压气机搭建了叶片与机匣处理一体化优化设计平台,基于自由变形技术关联设计参数与工程参数,实现多目标优化。综合考虑效率和裕度指标,在峰值效率不降的情况下获得了7.21%的裕度拓宽量。针对最优方案,分析了叶顶堵塞及损失分布,探讨了叶片与机匣处理一体化优化设计的扩稳机理。研究发现:叶片弯掠和机匣处理组合作用下,最大堵塞位置由24.7%叶顶轴向弦长后移至33.6%叶顶轴向弦长,最大损失位置由21.4%叶顶轴向弦长后移至30.6%叶顶轴向弦长,叶顶泄漏涡的抑制和低能堵塞区的消除是一体化优化设计扩稳的主要原因。

     

  • 图 1  网格无惯性验证

    Figure 1.  Grid-dependency test

    图 2  计算域及边界条件

    Figure 2.  Computational domain and boundary conditions

    图 3  数值和实验气动性能对比

    Figure 3.  Comparison of numerical and experimental aerodynamic performance

    图 4  FFD控制体

    Figure 4.  FFD control volume

    图 5  优化流程示意图

    Figure 5.  Optimization process diagram

    图 6  优化数据库

    Figure 6.  Optimization database

    图 7  最优设计

    Figure 7.  Optimal design

    图 8  优化前后叶片形状对比

    Figure 8.  Comparison of blade shape before and after optimization

    图 9  优化前后进口攻角对比

    Figure 9.  Comparison of inlet incidence before and after optimization

    图 10  Pareto图

    Figure 10.  Pareto diagram

    图 11  回归分析与相关性分析

    Figure 11.  Regression analysis and correlation analysis

    图 12  优化前后压气机特性线对比

    Figure 12.  Comparison of compressor performance before and after optimization

    图 13  优化前后轴向速度对比

    Figure 13.  Comparison of axial velocity before and after optimization

    图 14  不同工况下堵塞因子轴向分布对比

    Figure 14.  Axial distribution comparison of blockage factor at different conditions

    图 15  优化前后堵塞因子轴向分布对比

    Figure 15.  Axial distribution comparison of blockage factor before and after optimization

    图 16  优化前后叶顶涡量分布对比

    Figure 16.  Comparison of vorticity magnitude before and after optimization

    图 17  优化前后叶顶载荷对比

    Figure 17.  Comparison of rotor tip blade loading before and after optimization

    图 18  优化前后损失轴向分布对比

    Figure 18.  Axial distribution comparison of loss before and after optimization

    图 19  优化前后压气机特性线对比

    Figure 19.  Comparison of compressor performance before and after optimization

    表  1  压气机单转子设计参数

    Table  1.   Design parameters of the compressor single rotor

    参数 数值
    设计转速/(r/min) 2400
    设计流量/(kg/s) 2.9
    马赫数 0.19
    转子数 60
    叶顶弦长/mm 36.3
    叶顶间隙/mm 0.8
    叶顶轴向弦长/mm 22.8
    轮毂比 0.75
    下载: 导出CSV

    表  2  设计参数的变化范围

    Table  2.   Range of design parameters

    设计变量 控制点 范围
    叶片控制体 叶片前缘弯(LE bend) Pijki=0~2; j=0; k=2) −0.1~0.25Cax
    叶片尾缘弯(TE bend) Pijki=0~2; j=2; k=2) −0.1~0.25Cax
    叶片前缘掠(LE sweep) Pijki=0~2; j=0; k=2) −0.1~0.25Cax
    叶片尾缘掠(TE sweep) Pijki=0~2; j=2; k=2) −0.1~0.25Cax
    叶片旋转(Rotation) Pijki=0~2; j=0~2; k=2; except i=j=1) −10°~10°
    轴向缝控制体 轴向缝弯(Slot bend) Pijki =0~2; j=0~2; k=2) −0.15~0.15Cax
    轴向缝掠(Slot sweep) Pijki =0~2; j=0~2; k=2) −0.15~0.15Cax
    轴向缝扭(Slot twist) Pijki=0~2; j=1,2; k=0~2; except i=j=1) −60°~60°
    轴向缝高(Slot height) Pijki=0~2; j=0~2; k=2) −0.05~0.2Cax
    周向槽 周向槽缩放(Groove scale) 0.044~0.178Cax
    下载: 导出CSV
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  • 收稿日期:  2022-02-14
  • 网络出版日期:  2024-03-04

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