超声速边界层燃烧减阻技术研究进展  

Review of supersonic boundary layer combustion for skin friction drag reduction technology

作　　者：郑星 冯黎明[2] 张云天 刘远树 薛瑞 ZHENG Xing;FENG Liming;ZHANG Yuntian;LIU Yuanshu;XUE Rui(State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Aerospace,Xi'an Jiaotong University,Xi'an 710049,China;China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]西安交通大学航天航空学院机械结构强度与振动国家重点实验室,西安710049 [2]中国空气动力研究与发展中心,绵阳621000

出　　处：《固体火箭技术》2021年第4期438-447,共10页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(51706170);中国博士后科学基金(2019TQ0246,2019M663734);煤燃烧国家重点实验室基金(FSKLCCA2004);陕西省博士后科学基金(2018BSHEDZZ03);高温气体动力学国家重点实验室基金;湍流与复杂系统国家重点实验室基金;中央高校基本科研业务费专项资金(xzy012019053)。

摘　　要：超燃冲压发动机流道内摩擦阻力占高超声速飞行器总摩擦阻力的绝大部分,使推力遭受较大损失。研究表明,与其他减阻方式相比,边界层内燃料燃烧的方式可大幅降低壁面摩擦力,然而其诸多的影响因素及其内部复杂的物理化学过程,使其减阻机理至今仍未完全清楚。分别从边界层燃烧减阻基本特性、实验和数值模拟、减阻机理三方面展开当前超声速边界层燃烧减阻技术研究进展的综述。目前,国内外实验研究已经证实了边界层燃烧减阻的有效性,并开展缩比冲压发动机适用性研究,初步形成了将该减阻技术应用于高超声速飞行器的能力。数值模拟研究了不同释热、激波作用强度以及来流状态参数等真实环境下边界层燃烧减阻的变化规律。但总体而言,国内外对边界层燃烧减阻研究很少,且国外公开实验数据较少,实验研究揭示减阻机理的文章几乎没有,仍存在许多值得探讨的地方。文章在综述的同时,对下一步研究提出了相关建议。The internal frictional resistance of scramjet engine takes up the majority of the frictional resistance of hypersonic ve⁃hicle,which triggers the substantial loss of thrust.Related researches have shown that boundary layer combustion can significantly reduce wall friction compared to other drag reduction methods.However,the drag reduction mechanism of boundary layer combus⁃tion have not been thoroughly and comprehensively ascertained due to numerous influencing factors and the complex coupling be⁃tween internal physical and chemical processes.The research progress of supersonic boundary layer combustion drag reduction tech⁃nology was reviewed from three aspects:basic model of boundary layer combustion drag reduction,experimental and numerical sim⁃ulation,and drag reduction mechanism.At present,experimental studies had confirmed the effectiveness of boundary layer combus⁃tion drag reduction,and carried out the research on the applicability of scaled scramjet,as well as formed the preliminary ability to apply this drag reduction technology on supersonic aircraft.The boundary layer combustion drag reduction performance in real envi⁃ronment under different parameters such as heat release,shock wave intensity and incoming flow state was investigated by numerical simulation.However,few present studies focused on boundary layer combustion drag reduction had been conducted,and few experi⁃mental data abroad had been disclosed,as well as few papers related to the mechanism of drag reduction had been published.Despite all this,there were still numerous academic issues based on boundary layer combustion drag reduction worth being discussed.This paper comprehensively summarized the development of boundary layer drag reduction technology and puts forward some prag⁃matic suggestions for further research.

关 键 词：超燃冲压发动机 边界层燃烧减阻 壁面燃料注入 最优减阻性能 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]