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发动机短舱泄压过程瞬态仿真

王晨臣 冯诗愚 彭孝天 邓阳 陈俊

王晨臣, 冯诗愚, 彭孝天, 等 . 发动机短舱泄压过程瞬态仿真[J]. 北京航空航天大学学报, 2019, 45(11): 2284-2290. doi: 10.13700/j.bh.1001-5965.2019.0081
引用本文: 王晨臣, 冯诗愚, 彭孝天, 等 . 发动机短舱泄压过程瞬态仿真[J]. 北京航空航天大学学报, 2019, 45(11): 2284-2290. doi: 10.13700/j.bh.1001-5965.2019.0081
WANG Chenchen, FENG Shiyu, PENG Xiaotian, et al. Transient simulation on pressure relief process of engine nacelle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(11): 2284-2290. doi: 10.13700/j.bh.1001-5965.2019.0081(in Chinese)
Citation: WANG Chenchen, FENG Shiyu, PENG Xiaotian, et al. Transient simulation on pressure relief process of engine nacelle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(11): 2284-2290. doi: 10.13700/j.bh.1001-5965.2019.0081(in Chinese)

发动机短舱泄压过程瞬态仿真

doi: 10.13700/j.bh.1001-5965.2019.0081
基金项目: 

国家自然科学基金 U1933121

南京航空航天大学研究生创新基地(实验室)开放基金 kfjj20180108

江苏高校优势学科建设工程 

详细信息
    作者简介:

    王晨臣  男, 硕士研究生。主要研究方向:飞行器燃油系统

    冯诗愚  男, 博士, 副教授。主要研究方向:飞行器环境控制和燃油系统

    通讯作者:

    冯诗愚. E-mail:shiyuf@nuaa.edu.cn

  • 中图分类号: V224+.2

Transient simulation on pressure relief process of engine nacelle

Funds: 

National Natural Science Foundation of China U1933121

the Fundamental Research Funds for the Central Universities kfjj20180108

the Priority Academic Program Development of Jiangsu Higher Education Institutions 

More Information
  • 摘要:

    发动机短舱泄压门的设计会影响到短舱的安全性,泄压是一个动态变化过程,与舱内外压力、外界气流马赫数及泄压门结构有关。基于Modelica语言建立了短舱泄压过程零维瞬态仿真数学模型,并通过计算流体力学(CFD)方法得到不同开启角度下所需泄压门排放质量流量和力矩系数,并将这些系数代入零维瞬态仿真数学模型,得到了短舱泄压过程中舱内压力、泄压门开启角度等关键参数随时间的变化关系,分析了泄压门开启舱内压力阈值及最大开启角度对泄压过程的影响。研究结果显示,降低泄压门开启舱内压力阈值会使泄压过程到达平衡阶段时间减小,但是对平衡阶段舱内压力和往复摆动角度/幅度无影响。适当降低最大开启角度可有效降低泄压平衡阶段往复摆动角度/幅度,而对初始阶段的泄压速率和平衡阶段的短舱内部压力基本无影响,但是随着最大开启角度进一步降低,则会导致泄压速率下降,并使平衡阶段短舱内部压力升高。

     

  • 图 1  短舱泄压过程示意图

    Figure 1.  Schematic diagram of nacelle pressure relief process

    图 2  泄压门外形和结构示意图

    Figure 2.  Schematic diagram of PRD shape and structure

    图 3  泄压门几何模型

    Figure 3.  Geometry model of PRD

    图 4  网格划分

    Figure 4.  Mesh generation

    图 5  计算结果与试验数据对比

    Figure 5.  Comparison of calculation and test data

    图 6  计算结果与试验数据误差分析

    Figure 6.  Error analysis of calculation and test data

    图 7  排放质量流量随开启角度和舱内压力的变化

    Figure 7.  Discharge mass flow rate varies with opening angle and plenum compartment pressure

    图 8  流量系数随开启角度和舱内压力的变化

    Figure 8.  Discharge coefficient varies with opening angle and plenum compartment pressure

    图 9  力矩随开启角度和舱内压力的变化

    Figure 9.  Moment varies with opening angle and plenum compartment pressure

    图 10  不同开启阈值下舱内压力变化对比

    Figure 10.  Comparison of plenum compartment pressure changes under different opening thresholds

    图 11  不同开启阈值下开启角度变化对比

    Figure 11.  Comparison of opening angle changes under different opening thresholds

    图 12  不同最大开启角度下舱内压力变化对比

    Figure 12.  Comparison of plenum compartment pressure changes under different maximum opening angles

    图 13  不同最大开启角度下开启角度变化对比

    Figure 13.  Comparison of PRD opening angle changes under different maximum opening angles

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出版历程
  • 收稿日期:  2019-03-04
  • 录用日期:  2019-03-29
  • 网络出版日期:  2019-11-20

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