Film cooling and its combination with thermal barrier coating for hypersonic engine

IF 5 2区工程技术 Q1 ENGINEERING, MECHANICAL

International Journal of Thermal Sciences Pub Date : 2025-06-13 DOI:10.1016/j.ijthermalsci.2025.110078

Huikun Cai , Haorui Liao , Haiping Li , Chengxiang Zhu , Yancheng You

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Abstract

Hypersonic aircraft engine and the related vehicles are believed to be the future development due to its advantages in terms of faster response time, higher penetration capability and better system survivability compared with traditional aircraft engine. However, its exhaust nozzle suffers a super high thermal load and needs a powerful thermal protection for system structural strength and electron device safety. Therefore, this paper addresses to film cooling and its combination with thermal barrier coating as thermal protection strategy for hypersonic aircraft engine. The experiments are conducted to study the effect of cooling gas rate, mainstream inlet temperature, convention and compound gas film hole on film cooling performance. It is found that small hole injection angle and large cooling gas rate provide a better cooling efficiency, which can be up to 46 %. The numerical analyses are carried out to study the influence of different cooling methods. It is found that thermal barrier coating performs well in all the three types exhaust nozzles, whereas film cooling exhibits excellent nearby gas inlet and gradually gets worse away from inlet due to its growing gas temperature heated by mainstream gas. Combined cooling can further reduce the temperature on the basis of film cooling or thermal barrier coating, and maintains a temperature drop by the percentage of about 20–30 %, which proves that coupled thermal protection is quite effective to hypersonic aircraft engine.

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高超声速发动机的膜冷却及其与热障涂层的结合

与传统飞机发动机相比，高超声速飞机发动机具有更快的响应时间、更高的突防能力和更好的系统生存能力等优势，被认为是未来的发展方向。然而，其排气喷嘴承受超高的热负荷，需要对系统结构强度和电子器件安全进行强大的热保护。因此，本文研究了气膜冷却及其与热障涂层的结合作为高超声速飞机发动机的热防护策略。通过实验研究了冷却气量、主流入口温度、常规气膜孔和复合气膜孔对气膜冷却性能的影响。结果表明，较小的喷孔角度和较大的冷却气量可获得较好的冷却效率，冷却效率可达46%。通过数值分析，研究了不同冷却方式的影响。研究发现，热障涂层在三种排气喷嘴中均表现良好，而气膜冷却在进口附近表现优异，在远离进口的地方由于主流气体加热的气体温度升高而逐渐变差。复合冷却可以在膜冷却或热障涂层的基础上进一步降低温度，并保持20 - 30%左右的温度下降百分比，证明耦合热防护对高超声速飞机发动机是相当有效的。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Thermal Sciences 工程技术-工程：机械

CiteScore

8.10

自引率

11.10%

发文量

531

审稿时长

55 days

期刊介绍： The International Journal of Thermal Sciences is a journal devoted to the publication of fundamental studies on the physics of transfer processes in general, with an emphasis on thermal aspects and also applied research on various processes, energy systems and the environment. Articles are published in English and French, and are subject to peer review. The fundamental subjects considered within the scope of the journal are: * Heat and relevant mass transfer at all scales (nano, micro and macro) and in all types of material (heterogeneous, composites, biological,...) and fluid flow * Forced, natural or mixed convection in reactive or non-reactive media * Single or multi–phase fluid flow with or without phase change * Near–and far–field radiative heat transfer * Combined modes of heat transfer in complex systems (for example, plasmas, biological, geological,...) * Multiscale modelling The applied research topics include: * Heat exchangers, heat pipes, cooling processes * Transport phenomena taking place in industrial processes (chemical, food and agricultural, metallurgical, space and aeronautical, automobile industries) * Nano–and micro–technology for energy, space, biosystems and devices * Heat transport analysis in advanced systems * Impact of energy–related processes on environment, and emerging energy systems The study of thermophysical properties of materials and fluids, thermal measurement techniques, inverse methods, and the developments of experimental methods are within the scope of the International Journal of Thermal Sciences which also covers the modelling, and numerical methods applied to thermal transfer.