液氨/航油双冷却剂预冷器流动换热特性数值研究

  • 王彦红 ,
  • 翟士博 ,
  • 东明
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  • 1. 东北电力大学
    2. 大连理工大学

收稿日期: 2026-02-26

  修回日期: 2026-04-29

  网络出版日期: 2026-04-30

基金资助

国家自然科学基金项目

Numerical Research on Flow and Heat Transfer Characteristics of Liquid Ammonia/Aviation Kerosene Dual-Coolant Precooler

  • WANG Yan-Hong ,
  • DI Shi-Bo ,
  • DONG Ming
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Received date: 2026-02-26

  Revised date: 2026-04-29

  Online published: 2026-04-30

Supported by

National Natural Science Foundation of China

摘要

针对高飞行马赫数下涡轮基组合循环(TBCC)发动机面临进气高温导致的功率严重缺失问题,提出了液氨/航空煤油双冷却剂预冷器方案,开展了双冷却剂预冷器流动与换热特性数值研究,探讨了空气进口速度、进口温度和非均匀进气条件对预冷性能的影响。考察了空气侧温度场、速度场和湍动能的分布特征。通过场协同理论阐述了空气侧的换热和流阻情况。进行了流线和涡量分析,揭示了预冷通道壁面温度与热流密度的空间分布机制。通过努塞尔数对液氨侧和航油侧预冷通道的换热进行分析。引入(火积)耗散量和空气侧换热系数对预冷性能开展量化评估。数值结果表明:因为液氨比热容远高于航油,液氨侧空气温度低于航油侧。液氨通道下游具有更小的回流涡系,对应的湍动能显著低于航油侧。液氨通道分配的热流更多,其空气侧换热系数和不可逆损失更高。航油侧场协同性对空气进口参数改变敏感,空气先经历换热好流阻大的剧烈换热过程,随后经历换热差流阻小的平稳换热过程;而液氨侧场协同性受空气进口参数影响较弱,空气的沿程换热和流阻都相对稳定。

本文引用格式

王彦红 , 翟士博 , 东明 . 液氨/航油双冷却剂预冷器流动换热特性数值研究[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33519

Abstract

To address the issue of severe power loss caused by high air inlet temperature faced by the Turbine-Based Combined Cycle (TBCC) engine under high flight Mach numbers, the scheme of liquid ammonia/aviation kerosene dual-coolant precooler was proposed. Numerical research on the flow and heat transfer characteristics of dual-coolant precooler was carried out, investigating the effects of air inlet velocity, inlet temperature, and non-uniform inlet condition on precooling performance. The distribution characteristics of air-side temperature field, velocity field, and turbulent kinetic energy were investigated. The air-side heat transfer and flow resistance were elucidated through field synergy theory. The streamline and vorticity analysis were conducted, and the spatial distribution mechanisms of wall temperature and heat flux in precooling channels were revealed. The heat transfer of precooling channels on the liquid ammonia side and the aviation kerosene side were analyzed using the Nusselt number. Quantitative evaluation of precooling performance was conducted by introducing entransy dissipation and air-side heat transfer coefficient. The numerical results indicate that due to the much higher specific heat capacity of liquid ammonia compared to aviation kerosene, the air temperature on the liquid ammonia side is lower than that on the aviation kerosene side. The downstream of liquid ammonia channel has a smaller reflux vortex system, corresponding to significantly lower turbulent kinetic energy than the aviation kerosene side. The liquid ammonia channel distributes more heat flux, resulting in higher air-side heat transfer coefficient and irreversible loss. The field synergy of aviation kerosene side is sensitive to changes in air inlet parameters. The air undergoes a severe heat transfer process with good heat transfer and high flow resistance, followed by a stable heat transfer process with poor heat transfer and low flow resistance; The influence of air inlet parameters on the field synergy of liquid ammonia side is relatively weak, and the heat transfer and flow resistance along the air flow direction are relatively stable.

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