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基于三维体积力模型的离心压气机喘振预测方法

曾翰轩 范腾博 温孟阳 魏杰 王钧莹 孙振中 郑新前

曾翰轩, 范腾博, 温孟阳, 等. 基于三维体积力模型的离心压气机喘振预测方法[J]. 航空动力学报, 2024, 39(2):20220047 doi: 10.13224/j.cnki.jasp.20220047
引用本文: 曾翰轩, 范腾博, 温孟阳, 等. 基于三维体积力模型的离心压气机喘振预测方法[J]. 航空动力学报, 2024, 39(2):20220047 doi: 10.13224/j.cnki.jasp.20220047
ZENG Hanxuan, FAN Tengbo, WEN Mengyang, et al. Surge prediction of radial compressors based on three-dimensional body-force method[J]. Journal of Aerospace Power, 2024, 39(2):20220047 doi: 10.13224/j.cnki.jasp.20220047
Citation: ZENG Hanxuan, FAN Tengbo, WEN Mengyang, et al. Surge prediction of radial compressors based on three-dimensional body-force method[J]. Journal of Aerospace Power, 2024, 39(2):20220047 doi: 10.13224/j.cnki.jasp.20220047

基于三维体积力模型的离心压气机喘振预测方法

doi: 10.13224/j.cnki.jasp.20220047
基金项目: 国家科技重大专项(2017-Ⅱ-0004-0016,J2019-Ⅰ-0011)
详细信息
    作者简介:

    曾翰轩(1994-),男,博士生,主要从事航空发动机气动稳定性研究

    通讯作者:

    郑新前(1977-),男,教授、博士生导师,博士,主要从事航空发动机气动热力学研究。E-mail:zhengxq@tsinghua.edu.cn

  • 中图分类号: V231

Surge prediction of radial compressors based on three-dimensional body-force method

  • 摘要:

    为了实现对喘振流动现象的准确、快速预测,提出了一种基于三维体积力模型的离心压气机喘振预测方法,并在一款跨声速离心压气机上进行了应用,对以叶轮进口叶尖“回流泡”、喘振中的旋转失速,以及蜗壳诱发的非对称流动为代表的典型喘振流场结构进行了捕捉。通过与经试验校核的全三维非定常雷诺平均Navier-Stokes(URANS)方法进行对比表明:本文提出的离心压气机喘振预测方法,针对主要喘振流动特征的预测具备与全三维URANS方法相当的能力,同时计算时间约为全三维URANS方法的1/20。

     

  • 图 1  后弯叶轮出口的滑移效应

    Figure 1.  Slip effect at the outlet of a back-sweep impeller

    图 2  压缩系统示意图

    Figure 2.  Sketch of the compression system

    图 3  试验压气机实物图[16]

    Figure 3.  Tested compressor geometry[16]

    图 4  体积力模型计算域及计算网格

    Figure 4.  Computational domain and mesh for the BDF model

    图 5  URANS模型计算域及计算网格

    Figure 5.  Computational domain and mesh for the UNRANS model

    图 6  网格无关性验证

    Figure 6.  Mesh independence validation

    图 7  BDF模型与URANS模型预测喘振特性对比

    Figure 7.  Comparison of the predicted surge characteristics between BDF model and URANS model

    图 8  喘振过程中压气机各截面静压变化对比

    Figure 8.  Comparison of the static pressure at several compressor stations during surge

    图 9  流动崩溃阶段压气机瞬时轴向速度云图(对应时刻见图7

    Figure 9.  Compressor axial velocity contour during the flow reversal (corresponding time is shown in Fig.7

    图 10  喘振过程中压气机瞬时马赫数云图(50%扩压器叶高截面,对应时刻见图7

    Figure 10.  Mach number contour during surge (50% diffuser blade span, corresponding time is shown in Fig.7

    图 11  失速团的周向迁移(P1和P2位置见图10

    Figure 11.  Circumferential migration of the stall cell (the locations of P1 and P2 are shown in Fig.10

    图 12  重新增压阶段压气机瞬时马赫数云图(50%扩压器叶高截面,对应时刻见图8

    Figure 12.  Mach number contour during the repressurization stage (50% diffuser blade span, corresponding time is shown in Fig.8

    表  1  压气机无量纲参数

    Table  1.   Compressor design parameters

    参数符号数值
    叶轮周期数$ {Z_{\text{i}}} $16
    进口轮毂比$ R $0.63
    扩压器周期数$ {Z_{\text{d}}} $16
    扩压器进口半径比${r_3}/{r_2}$1.18
    扩压器出口半径比${r_4}/{r_2}$1.44
    叶轮叶尖马赫数$ M{a_{\text{u}}} $1.4
    流量系数$ \phi $0.04
    压升系数$ \psi $0.47
    比转速$ {N_{\text{s}}} $0.70
    B参数$ B $1.22
    下载: 导出CSV

    表  2  URANS模型网格参数

    Table  2.   Mesh specifications for URANS model

    参数数值
    网格1网格2
    进口段流向膨胀比1.051.05
    叶轮径向网格层数5063
    叶轮流向网格层数100120
    叶轮周向网格层数(单通道)1616
    叶轮间隙网格层数1721
    扩压器径向网格层数5063
    扩压器流向网格层数5064
    扩压器周向网格层数(单通道)3548
    总网格数/万7461539
    下载: 导出CSV

    表  3  BDF网格参数

    Table  3.   Mesh specifications for BDF model

    参数数值
    网格1网格2
    径向网格层数1521
    周向网格层数100140
    进口段流向网格层数5070
    叶轮流向网格层数3040
    连接段流向网格层数810
    扩压器流向网格层数2330
    总网格数/万2252
    下载: 导出CSV
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出版历程
  • 收稿日期:  2022-01-25
  • 网络出版日期:  2023-10-16

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