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飞行包线下燃油箱耗氧型催化惰化系统性能研究

彭孝天 冯诗愚 任童 张瑞华 潘俊 王洋洋

彭孝天, 冯诗愚, 任童, 等 . 飞行包线下燃油箱耗氧型催化惰化系统性能研究[J]. 北京航空航天大学学报, 2021, 47(8): 1565-1570. doi: 10.13700/j.bh.1001-5965.2020.0283
引用本文: 彭孝天, 冯诗愚, 任童, 等 . 飞行包线下燃油箱耗氧型催化惰化系统性能研究[J]. 北京航空航天大学学报, 2021, 47(8): 1565-1570. doi: 10.13700/j.bh.1001-5965.2020.0283
PENG Xiaotian, FENG Shiyu, REN Tong, et al. Performance of oxygen-consuming catalytic inerting system of fuel tank under flight envelope[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(8): 1565-1570. doi: 10.13700/j.bh.1001-5965.2020.0283(in Chinese)
Citation: PENG Xiaotian, FENG Shiyu, REN Tong, et al. Performance of oxygen-consuming catalytic inerting system of fuel tank under flight envelope[J]. Journal of Beijing University of Aeronautics and Astronautics, 2021, 47(8): 1565-1570. doi: 10.13700/j.bh.1001-5965.2020.0283(in Chinese)

飞行包线下燃油箱耗氧型催化惰化系统性能研究

doi: 10.13700/j.bh.1001-5965.2020.0283
基金项目: 

国家自然科学基金 U1933121

南京航空航天大学研究生拔尖创新人才培养“引航计划”跨学科创新基金 KXKCXJJ202004

江苏省研究生科研与实践创新计划 KYCX19_0198

江苏高校优势学科建设工程 

详细信息
    通讯作者:

    冯诗愚, E-mail: shiyuf@nuaa.edu.cn

  • 中图分类号: V37;V219

Performance of oxygen-consuming catalytic inerting system of fuel tank under flight envelope

Funds: 

National Natural Science Foundation of China U1933121

Interdisciplinary Innovation Fundation for Graduates, NUAA KXKCXJJ202004

Postgraduate Research & Practice Innovation Program of Jiangsu Province KYCX19_0198

Priority Academic Program Development of Jiangsu Higher Education Institutions 

More Information
  • 摘要:

    为给新型耗氧催化惰化系统部件设计提供输入参数,在提出低温可控耗氧催化惰化系统流程基础上,以燃油箱出口抽吸流量为基准,基于质量守恒和能量守恒方程,建立了系统流程模型。以中央燃油箱为对象,仿真研究了全飞行包线下惰化系统的重要性能变化,以及关键参数对其影响。结果表明:惰化系统可以有效降低氧体积分数,如在初始满载、催化效率0.5、风机抽吸流量60 L/min条件下,24 min后氧体积分数即降至12%以下;在飞行过程中,燃油箱气相氧氧体积分数在下降及进场阶段上升,其他阶段均呈下降趋势;催化效率越高、风机抽吸流量越大,所需惰化时间越小,且催化效率一定时,达到相同惰化时间,初始空载时所需风机抽吸流量最大。应按最不利的空载工况来设计耗氧型催化惰化系统。

     

  • 图 1  3CIS系统主要部件示意图

    Figure 1.  Schematic diagram of main components of 3CIS system

    图 2  飞行马赫数和不同初始载油情况下载油率随飞行时间的变化

    Figure 2.  Variation of Mach number and fuel load rate with flight time under different initial fuel load conditions

    图 3  气相空间氧体积分数随飞行时间的变化

    Figure 3.  Variation of oxygen volume fraction on ullage with flight time

    图 4  气相空间各气体组分体积分数随飞行时间的变化

    Figure 4.  Variation of volume fraction of each gas component on ullage with flight time

    图 5  燃油箱与外界交换氧气量随飞行时间的变化

    Figure 5.  Variation of exchange of oxygen between fuel tank and environment with flight time

    图 6  惰化时间随风机抽吸流量的变化

    Figure 6.  Relationship between inerting time and fan flow

    图 7  可燃性暴露时间与飞行时间比值随风机抽吸流量的变化

    Figure 7.  Variation of flammability exposure time to flight time ratio with fan flow

    图 8  惰化系统所需冷却热量

    Figure 8.  Cooling heat required for inerting system

    图 9  惰化系统析出液态水量

    Figure 9.  Liquid water removed from inerting system

    表  1  飞行包线信息

    Table  1.   Flight envelope information

    状态 轮档时间/min 高度/m 轮档耗油/kg
    滑出 7 0 189
    起飞 2 0→457 630
    爬升 29 457→12 000 4 992
    巡航 755 12 000 67 987
    下降 21 120 00→457 373
    进场 6 457 240
    滑入 5 0 135
    下载: 导出CSV
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出版历程
  • 收稿日期:  2020-06-19
  • 录用日期:  2020-08-14
  • 网络出版日期:  2021-08-20

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