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二元塞式喷管塞锥气膜冷却特性研究

陈静 单勇 张序墉 征建生

陈静, 单勇, 张序墉, 等. 二元塞式喷管塞锥气膜冷却特性研究[J]. 航空动力学报, 2024, 39(8):20220080 doi: 10.13224/j.cnki.jasp.20220080
引用本文: 陈静, 单勇, 张序墉, 等. 二元塞式喷管塞锥气膜冷却特性研究[J]. 航空动力学报, 2024, 39(8):20220080 doi: 10.13224/j.cnki.jasp.20220080
CHEN Jing, SHAN Yong, ZHANG Xuyong, et al. Study of film cooling characteristics on plug of two-dimensional (2-D) plug nozzle[J]. Journal of Aerospace Power, 2024, 39(8):20220080 doi: 10.13224/j.cnki.jasp.20220080
Citation: CHEN Jing, SHAN Yong, ZHANG Xuyong, et al. Study of film cooling characteristics on plug of two-dimensional (2-D) plug nozzle[J]. Journal of Aerospace Power, 2024, 39(8):20220080 doi: 10.13224/j.cnki.jasp.20220080

二元塞式喷管塞锥气膜冷却特性研究

doi: 10.13224/j.cnki.jasp.20220080
详细信息
    作者简介:

    陈静(1995-),女,硕士生,主要从事航空发动机传热方面的研究。E-mail:2668065263@qq.com

    通讯作者:

    单勇(1978-),男,教授、博士生导师,博士,主要从事飞行器红外隐身和航空发动机传热方面的研究。E-mail:nuaasy@nuaa.edu.cn

  • 中图分类号: V231.1

Study of film cooling characteristics on plug of two-dimensional (2-D) plug nozzle

  • 摘要:

    加力状态使得二元塞式喷管热负荷急剧升高,势必需要引入冷气对塞锥进行冷却。在缩比模型试验验证的基础上,采用全尺寸模型数值仿真,对比分析了入口总压比、开孔率和气膜孔径对二元塞式喷管流动和冷却特性的影响。结果表明:在研究参数范围内,气膜冷却能够显著降低塞锥表面温度,对喷管推力系数影响甚微;以无冷却为基准,入口总压比从1.02增至1.20,塞锥表面温度降低了20%~45%,总压恢复系数降低了0.22%~1.26%;增大开孔率会导致冷却通道压力降低、气膜出流阻力增大,在塞锥尾部甚至出现热气倒灌,综合考虑整个塞锥表面的冷气出流状况,小开孔率结构更具优势;减小气膜孔径意味着气膜孔数目增加、气膜覆盖范围增大,使得塞锥冷却效果有微弱的改善。

     

  • 图 1  二元塞式喷管模型

    Figure 1.  Model of 2-D plug nozzle

    图 2  二元塞式喷管冷却结构示意图

    Figure 2.  Sketch map of cooling structure of 2-D plug nozzle

    图 3  计算域示意图

    Figure 3.  Sketch map of computational region

    图 4  验证模型

    Figure 4.  Verification model

    图 5  二元塞锥冷却结构

    Figure 5.  Cooling structure of 2-D plug

    图 6  二元塞锥试验件

    Figure 6.  Experimental specimen of 2-D plug

    图 7  试验系统示意图

    Figure 7.  Sketch map of experimental system

    图 8  塞锥后体综合冷效对比

    Figure 8.  Comparison of comprehensive cooling effect on plug rear surface

    图 9  入口总压比对推力和总压恢复系数的影响

    Figure 9.  Effect of total pressure ratio of inlets on total pressure recovery and thrust coefficients

    图 10  入口总压比对塞锥表面静温分布的影响

    Figure 10.  Effect of total pressure ratio of inlets on temperature distribution on plug surface

    图 11  入口总压比对特征点附近流线与静压分布的影响

    Figure 11.  Effect of total pressure ratio of inlets on streamline and static pressure distributions around feature points

    图 12  入口总压比对塞锥表面热流密度的影响

    Figure 12.  Effect of total pressure ratio of inlets on density of heat flux on plug surface

    图 13  开孔率对推力和总压恢复系数的影响

    Figure 13.  Effect of perforated percentage of film holes on total pressure recovery and thrust coefficients

    图 14  开孔率对塞锥表面静温分布的影响

    Figure 14.  Effect of perforated percentage of film holes on temperature distribution on plug surface

    图 15  开孔率对特征点附近流线与静压分布的影响

    Figure 15.  Effect of perforated percentage of film holes on streamline and static pressure distributions around feature points

    图 16  开孔率对塞锥表面热流密度的影响

    Figure 16.  Effect of perforated percentage of film holes on density of heat flux on plug surface

    图 17  气膜孔径对推力和总压恢复系数的影响

    Figure 17.  Effect of diameter of film holes on total pressure recovery and thrust coefficients

    图 18  气膜孔径对塞锥表面静温分布的影响

    Figure 18.  Effect of diameter of film holes on temperature distribution on plug surface

    图 19  气膜孔径对塞锥表面热流密度的影响

    Figure 19.  Effect of diameter of film holes on density of heat flux on plug surface

    表  1  气膜孔结构和冷气参数

    Table  1.   Parameters of film structure and cooling air

    参数模型
    s/mm15.7115.7110.477.85
    p/mm10555
    φ/%0.51.01.52.0
    d/mm0.6,0.8,1.0
    ζ1.02,1.05,1.10,1.15,1.20
    下载: 导出CSV

    表  2  不同入口总压比下塞锥冷却流量比

    Table  2.   Plug cooling flow ratio under different total pressure ratio of inlets

    ζχ/%
    1.023.63
    1.054.54
    1.105.40
    1.156.07
    1.206.67
    下载: 导出CSV

    表  3  不同开孔率下塞锥冷却流量比

    Table  3.   Plug cooling flow ratio under different perforated percentage %

    φ χ
    0.5 4.54
    1.0 4.91
    1.5 4.95
    2.0 5.15
    下载: 导出CSV

    表  4  不同气膜孔径下塞锥冷却流量占比

    Table  4.   Plug cooling flow ratio vs diameter of film holes

    d/mm χ/%
    0.6 4.23
    0.8 4.44
    1.0 4.54
    下载: 导出CSV
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出版历程
  • 收稿日期:  2022-02-23
  • 网络出版日期:  2024-03-27

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