超声速燃烧室凹腔构型优化研究进展

doi:10.7527/S1000-6893.2026.33007

Abstract

Abstract:

In air-breathing hypersonic vehicles， scramjet propulsion systems face core challenges such as fast and adequate fuel-supersonic airflow mixing， effective combustion， and robust flame stabilization. As one of the most widely used flame stabilization devices in scramjet combustors， the cavity shows a profound influence on the fuel mixing and combustion process， as well as the combustor performance. This paper systematically reviews research progress on the effects of cavity configurations on flow characteristics and combustor performance in supersonic combustors. First， a concise overview of the supersonic cavity is introduced， including the basic configurations， the typical flow structures， and physical effects of the supersonic cavity. Second， the influence of fundamental cavity configuration parameters， including cavity length， depth， length-to-depth ratio， rear-wall inclination angle， and front-wall inclination angle， on flow and combustion characteristics such as cavity recirculation zone structures， fuel residence time and flame stability is summarized and analyzed. Third， the optimization of two-dimensional cavity configurations is systematically elaborated on the basis of three physical mechanisms： extension of recirculation zones/vortical structures； reconstruction of shock/expansion wave systems； and modulation of shear layer dynamics. Furthermore， three-dimensional cavity optimization is discussed， with a focus on the streamwise vortex enhancement and lateral mass exchange. Finally， recommendations are proposed for the configuration optimization and design of cavity flameholders， taking into account the current research status and technical bottlenecks.

Key words: scramjet, cavity configuration, combustor performance, mixing enhancement, flame stability

CLC Number:

V231.2

Zixuan ZHOU, Lin ZHANG, Mingbo SUN, Weiqi YANG, Hongwei QIAO, Yuqiao CHEN, Tong ZHANG. Research progress on cavity configuration optimization for supersonic combustors[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(13): 533007.

Figures/Tables 28

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Table 1

Influence of several basic cavity configuration parameters on supersonic combustor performance

影响因素	典型特征参数范围	研究结论
长度/mm	20 $~$ 180	长度影响凹腔卷吸燃料的速率^［66］长度影响剪切层在流向上的扩展及流体掺混速率^［66］长度过长会使原先的主涡进一步分裂为多个次生涡^［73-75］长度的增加会一定程度地延长燃料在凹腔中的停留时间，提升混合效率^［80］
深度/mm	5 $~$ 30	深度影响燃料在凹腔中的驻留时间^［80］深度较小凹腔的剪切层厚度更大，并且在横向上振荡更为显著^［69］
长深比	3 $~$ 10	长深比对剪切层流动不稳定性的调控尤为显著^［66-67］长深比对燃烧室的阻力有重要影响^［81］在一定范围内增加凹腔的长深比可以增强动量和热量的交换，促进燃烧^［84］
后缘倾角/（°）	30 $~$ 90	在一定范围内，后缘倾角越小，凹腔剪切层越偏向凹腔内部^［70］后缘倾角越小，凹腔内部回流区流动越稳定，燃料驻留时间越长，稳焰效果越好^{［76-78，80］}
前缘倾角/（°）	30 $~$ 90	减小前缘倾角会促使剪切层提前分离，使燃料更容易被卷吸至凹腔，从而促进火焰稳定^［82］

Table 1

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来源	研究对象	方法	研究发现
Kummitha等^［94］	阶梯凹腔	RANS	多步阶梯结构能生成串列式的回流区，从而增强燃料与空气的掺混效果
Luo等^［96］	三角形凹腔	RANS	三角形凹腔可产生更强的后缘激波，进而显著提高湍流燃烧强度
Kummitha等^［95］	波纹底壁凹腔	RANS	波纹底壁通过几何扰动使得剪切层失稳，促进涡旋产生，达到增混促燃的效果
Gruber等^［76］ Cai等^［98-99］	后缘突扩凹腔	实验； RANS/LES	较低的凹腔后缘高度改变了燃烧室内的激波/膨胀波系结构，从而影响凹腔内部的流场结构和湍流燃烧过程
Landsberg等^［100］	前壁倾斜凹腔	实验； RANS	倾斜的凹腔前壁面改变了流动分离点的位置，形成一个更为稳定的剪切层，并有效减小了剪切层的振荡
Krishna等^［101］	双斜坡凹腔；部分圆弧凹腔	实验	后壁面的分段斜坡和部分圆弧构型能够降低剪切层对后壁的撞击强度，从而显著降低燃烧室整体的声压级和压力扰动水平

来源	研究对象	方法	研究发现
Oamjee和Sadanandan^{［103-104］}	塔门凹腔	实验； RANS	塔门构型在增加燃料射流穿透力和增强燃料与空气混合的同时，产生了一对反转涡
Dan等^［108］	前缘斜坡凹腔	RANS	前缘斜坡诱导产生流向涡，从而加速了射流下部的氧气供应和火焰传播
Roos等^{［109-110］}	新月形凹腔	URANS	新月形凹腔前缘三维曲率产生的强流向涡增强了燃料与空气的混合
Handa^［115］和 Anyoji^［117］等	后缘斜坡凹腔	实验； IDDES	后缘斜坡诱导形成的发卡涡使剪切层发生偏转，其产生的波系结构沿斜坡传播至燃料喷射孔附近区域，从而增强燃料与空气的混合
Zhang等^［119］	后缘开槽凹腔	实验	开槽构型驱动横向空腔流动，使高温产物通过缝隙进入核心气流并形成热点，从而加速链式反应

Research progress on cavity configuration optimization for supersonic combustors

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