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基于Isight的二元进气道压缩楔射流控制参数优化

孙冯涛 史志伟 张伟麟 丁保政 舒彦淋

孙冯涛, 史志伟, 张伟麟, 丁保政, 舒彦淋. 基于Isight的二元进气道压缩楔射流控制参数优化[J]. 气体物理, 2024, 9(1): 21-35. doi: 10.19527/j.cnki.2096-1642.1080
引用本文: 孙冯涛, 史志伟, 张伟麟, 丁保政, 舒彦淋. 基于Isight的二元进气道压缩楔射流控制参数优化[J]. 气体物理, 2024, 9(1): 21-35. doi: 10.19527/j.cnki.2096-1642.1080
SUN Fengtao, SHI Zhiwei, ZHANG Weilin, DING Baozheng, SHU Yanlin. Parameter Optimization of Jet Control for Compression Ramps of Two-DimensionalInlet Based on Isight[J]. PHYSICS OF GASES, 2024, 9(1): 21-35. doi: 10.19527/j.cnki.2096-1642.1080
Citation: SUN Fengtao, SHI Zhiwei, ZHANG Weilin, DING Baozheng, SHU Yanlin. Parameter Optimization of Jet Control for Compression Ramps of Two-DimensionalInlet Based on Isight[J]. PHYSICS OF GASES, 2024, 9(1): 21-35. doi: 10.19527/j.cnki.2096-1642.1080

基于Isight的二元进气道压缩楔射流控制参数优化

doi: 10.19527/j.cnki.2096-1642.1080
详细信息
    作者简介:

    孙冯涛(1998—) 男,硕士,主要研究进气道流动控制与参数优化。E-mail: 578739321@qq.com

  • 中图分类号: V211.7

Parameter Optimization of Jet Control for Compression Ramps of Two-DimensionalInlet Based on Isight

  • 摘要: 二元进气道常用于宽速域吸气式飞行器。宽速域飞行器的飞行速域较大, 进气道要兼顾高低速条件下的飞行要求, 这存在一定的困难。利用射流进行前体激波控制, 在一定程度上可以改善流场, 并提升进气道性能, 但现有的射流激励方案仅是将激波推至唇口, 不一定使得进气道达到最优性能或造成射流流量过多损失, 因此射流控制参数的优化是一个重要问题。基于Isight软件搭建优化流程, 采用Hooke-Jeeves优化方法, 以射流角度、射流宽度以及射流位置作为优化变量, 流量系数作为约束条件, 总压恢复系数最大作为目标函数进行优化, 探究了来流Mach数为6时不同射流参数对进气道性能的影响。结果表明, Hooke-Jeeves优化方法可以应用于进气道前体射流控制参数优化问题, 优化后的进气道能够满足流量系数的要求, 射流角度优化后的总压恢复系数相对于无射流方案提升18%, 综合优化后的总压恢复系数相对于仅优化射流角度提升2.82%。

     

  • 图  1  进气道模型

    Figure  1.  Inlet model

    图  2  唇口附近局部网格

    Figure  2.  Local grid near the lip

    图  3  数值仿真密度梯度图和实验纹影图

    Figure  3.  Contour of density gradient magnitude and experimental schlieren

    图  4  数值仿真和实验内通道下壁面压力系数分布

    Figure  4.  Comparison of lower-wall pressure coefficient between simulation and experiment

    图  5  射流激励器参数

    Figure  5.  Parameters of jet exciter

    图  6  Isight优化流程

    Figure  6.  Optimization process of Isight

    图  7  优化过程中网格划分及数值计算结果

    Figure  7.  Grid and simulation results in the process of optimization

    图  8  目标函数及各优化变量收敛过程

    Figure  8.  Convergence process of objective function and optimization variables

    图  9  优化过程中点集分布

    Figure  9.  Distribution of point sets during the process of optimization

    图  10  总压恢复系数和射流角度及射流压比拟合云图

    Figure  10.  Fitting contour of total pressure recovery coefficient with jet angle and pressure ratio

    图  11  射流角度优化过程中不同样本点流场

    Figure  11.  Flow fields of different examples when optimizing jet angle

    图  12  射流位置优化时各优化变量收敛过程

    Figure  12.  Convergence process of optimization variables when optimizing jet position

    图  13  总压恢复系数随射流位置和射流压比变化拟合云图

    Figure  13.  Fitting contour of total pressure recovery coefficient with jet position and pressure ratio

    图  14  射流位置优化过程中不同样本点流场

    Figure  14.  Flow fields of different examples when optimizing jet position

    图  15  综合优化各优化变量收敛过程

    Figure  15.  Convergence process of objective function and optimization variables of combination optimization

    图  16  总压恢复系数和优化变量拟合云图

    Figure  16.  Fitting contour of total pressure recovery coefficient with optimization variables

    图  17  综合优化过程中不同样本点流场对比

    Figure  17.  Flow fields of different examples in the process of combination optimization

    图  18  不同射流参数下进气道流场

    Figure  18.  Flow fields of inlet at different jet parameters

    图  19  内通道截面示意图

    Figure  19.  Sketch of inner channel cross-section

    图  20  内通道中各截面参数

    Figure  20.  Parameters of each section in the inner channel

    图  21  角度优化和综合优化流场Mach数云图

    Figure  21.  Contour of Mach number of angle optimization and combination optimization

    图  22  角度优化和综合优化流场总压恢复系数分布

    Figure  22.  Contour of total pressure recovery coefficient of angle optimization and combination optimization

    图  23  角度优化和综合优化流场密度梯度云图

    Figure  23.  Contour of density gradient of angle optimization and combination optimization

    图  24  角度优化和综合优化流场压力梯度云图

    Figure  24.  Contour of pressure gradient of angle optimization and combination optimization

    表  1  进气道主要设计参数

    Table  1.   Main design parameters of inlet

    parameter value
    l1/mm 160
    l2/mm 200
    α1/(°) 7
    α2/(°) 13
    h/mm 136
    h1/mm 76
    下载: 导出CSV

    表  2  射流角度优化变量取值范围

    Table  2.   Value range of optimization variables when optimizing jet angle

    variable valuemin valueinitial valuemax
    θ1/(°) 30 90 150
    θ2/(°) 30 90 150
    Pr1 2 2.85 6
    Pr2 2 3.15 6
    下载: 导出CSV

    表  3  射流角度和压比最优值

    Table  3.   Optimal values of jet angle and pressure ratio

    θ1/(°) θ2/(°) Pr1 Pr2
    150 82.5 4 4
    下载: 导出CSV

    表  4  优化前后进气道性能对比

    Table  4.   Comparison of inlet performance before and after optimization

    method total pressure recovery coefficient flow cofficient Mach number of outlet
    without jet 0.420 1.00 3.9
    optimal jet angle 0.496 1.01 3.89
    relative variation/(%) 18 1 0.25
    下载: 导出CSV

    表  5  射流位置优化变量取值范围

    Table  5.   Value range of optimization variables when optimizing jet position

    variable valuemin valueinitial valuemax
    D1/mm 5 5 80
    D2/mm 5 5 80
    Pr1 2 2.85 6
    Pr2 2 3.15 6
    下载: 导出CSV

    表  6  射流位置和压比最优值

    Table  6.   Optimal values of jet position and pressure ratio

    D1/mm D2/mm Pr1 Pr2
    6.8 15.3 2.85 4.15
    下载: 导出CSV

    表  7  综合优化变量取值范围

    Table  7.   Variable value range of combination optimization

    variable valuemin valueinitial valuemax
    θ1/(°) 30 90 150
    θ2/(°) 30 90 150
    W1/mm 5 10 20
    W2/mm 5 10 20
    Pr1 2 2.85 6
    Pr2 2 3.15 6
    下载: 导出CSV

    表  8  综合优化变量最优值

    Table  8.   Optimal values of variables of combination optimization

    θ1/(°) θ2/(°) W1/mm W2/mm Pr1 Pr2
    60 91.875 18.47 19.88 2.85 3.21
    下载: 导出CSV

    表  9  综合优化后进气道性能

    Table  9.   Inlet performance after combination optimization

    optimization total pressure recovery coefficient flow cofficient Mach number of outlet
    optimal angle 0.496 1.01 3.89
    combination optimization 0.51 1.02 3.90
    relative variation/(%) 2.82 1 0.2
    下载: 导出CSV
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  • 收稿日期:  2023-08-28
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