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涡轮机匣热辐射⁃对流耦合换热特性数值计算与实验测试

陈皓 李嘉伟 史航 汪彤 宋方舟 王天壹 刘向雷

陈皓,李嘉伟,史航,等.涡轮机匣热辐射⁃对流耦合换热特性数值计算与实验测试[J].航空动力学报,2022,37(8):1597‑1606. doi: 10.13224/j.cnki.jasp.20210529
引用本文: 陈皓,李嘉伟,史航,等.涡轮机匣热辐射⁃对流耦合换热特性数值计算与实验测试[J].航空动力学报,2022,37(8):1597‑1606. doi: 10.13224/j.cnki.jasp.20210529
CHEN Hao,LI Jiawei,SHI Hang,et al.Numerical calculation and experimental test of heat radiation⁃convection coupling heat transfer characteristics of turbine casing[J].Journal of Aerospace Power,2022,37(8):1597‑1606. doi: 10.13224/j.cnki.jasp.20210529
Citation: CHEN Hao,LI Jiawei,SHI Hang,et al.Numerical calculation and experimental test of heat radiation⁃convection coupling heat transfer characteristics of turbine casing[J].Journal of Aerospace Power,2022,37(8):1597‑1606. doi: 10.13224/j.cnki.jasp.20210529

涡轮机匣热辐射⁃对流耦合换热特性数值计算与实验测试

doi: 10.13224/j.cnki.jasp.20210529
基金项目: 

国家科技重大专项(2017⁃Ⅲ⁃0010⁃0036) 

详细信息
    作者简介:

    陈皓(1988-),男,工程师,主要从事航空发动机热分析的研究。

    通讯作者:

    刘向雷(1989-),男,教授、博士生导师,博士,主要从事航空航天器热推进与热管理以及先进储能技术的研究。E⁃mail:xliu@nuaa.edu.cn

  • 中图分类号: V231.1

Numerical calculation and experimental test of heat radiation⁃ convection coupling heat transfer characteristics of turbine casing

  • 摘要:

    开展了整环机匣的热辐射⁃对流耦合计算,获得了综合传热系数拟合关系式,并进行了实验测试验证。研究发现:封闭腔内,热辐射的存在大幅强化了壁面换热,辐射热流占总换热量比值可达90%以上。在3层机匣结构中,当发射率在0.3~0.8变化时,机匣沿径向方向上的温度梯度减小,主流区域的对流换热得到加强,半封闭区域对流强度降低。发射率为0.8时,外机匣流体侧壁面的辐射热流占总换热量的33.3%。

     

  • 图 1  机匣模型轴向截面图(单位:mm)

    Figure 1.  Axial section diagram of casing model (unit:mm)

    图 2  实验件管路连接示意图

    Figure 2.  Schematic diagram of pipeline connection of experiment piece

    图 4  温度控制系统逻辑图

    Figure 4.  Logic diagram of temperature control system

    图 6  网格划分局部视图

    Figure 6.  Meshes local views

    图 7  不同网格数量下加热面热流

    Figure 7.  Heat flow of heating surface under different mesh numbers

    图 8  壁面边界条件说明

    Figure 8.  Illustration of wall boundary conditions

    图 9  工况1实验与仿真温度对比图

    Figure 9.  Comparison diagram of experimental and simulated temperature in working condition 1

    图 10  不同热处理时间下的合金单色发射率

    Figure 10.  Monochromatic emissivity of alloy at different heat treatment times

    图 11  腔5横向截面速度云图

    Figure 11.  Velocity cloud of transverse section of cavity 5

    图 12  线1的局部努塞尔数分布

    Figure 12.  Local Nusselt number distribution of line1

    图 13  线2相比于线1的平均努塞尔数增加百分比

    Figure 13.  Percentage increase in the mean Nusselt number of line 2 compared to line 1

    图 14  轴向截面流线图

    Figure 14.  Axial section flow line diagram

    图 16  不同发射率下机匣轴向截面温度云图

    Figure 16.  Temperature cloud of casing axial section under different emissivities

    图 17  不同发射率下S3截面径向方向的温度变化图

    Figure 17.  Temperature variation diagram of S3 section in radial direction under different emissivities

    图 18  面C上线3位置示意图

    Figure 18.  Line 3 position schematic diagram on surface C

    图 19  不同发射率下线3上的Nu变化图

    Figure 19.  Nusselt number variation diagram at line 3 with different emissivities

    图 20  综合传热系数随σTm3变化图

    Figure 20.  Variation diagram of comprehensive heat transfer coefficient with σTm3

    表  1  机匣内部通孔尺寸

    Table  1.   Through hole size inside the casing

    孔道名称尺寸/mm个数
    孔A34(直径)10
    孔B4(直径)20
    孔C2(直径)20
    孔D7×1(长×宽)20
    下载: 导出CSV

    表  2  实验测量工况

    Table  2.   Experimental measurement condition

    工况编号进口流量/(kg/s)内壁面加热温度/K进口平均温度/K
    10.07600285.7
    20.07700287.4
    30.1600285.6
    40.1700287.8
    下载: 导出CSV

    表  3  不确定度分量汇总表

    Table  3.   Summary of uncertainty components

    不确定度不确定度来源不确定度评定方式标准不确定度/K
    标准不确定度u1热电偶B类2.53=1.44
    u2数据采集系统B类1.03=0.58
    合成不确定度u12+u22=1.55
    下载: 导出CSV

    表  4  强迫对流区域的相关参数随发射率的变化

    Table  4.   Variation of relative parameters with emissivity in the forced convection region

    发射率Th/KTl/KΔq/(W/m2Ktot/(W/(m2K))
    0.3619.0478.42 976.621.2
    0.4621.8483.73 055.822.1
    0.5624.8489.43 141.023.2
    0.6627.7495.13 225.824.3
    0.7631.0501.23 317.825.6
    0.8634.4507.53 413.126.9
    下载: 导出CSV
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  • 收稿日期:  2021-09-22

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