Numerical investigation of three-dimensional oblique detonation structures in a combustor with sidewall confinement

LU Yahui; NIU Shuzhen; ZHANG Zijian; TENG Honghui

doi:10.7638/kqdlxxb-2025.0127

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Numerical investigation of three-dimensional oblique detonation structures in a combustor with sidewall confinement

更新时间：2026-05-28

- Numerical investigation of three-dimensional oblique detonation structures in a combustor with sidewall confinement
- Vol. 43, Issue 10, Pages: 70-84(2025)
- 作者机构：
  
  1. 北京理工大学空天科学与技术学院,北京,100081
  2. 临近空间环境特性及效应全国重点实验室,北京,100081
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0127
  CLC： V231;O381
- Published：2025
- 稿件说明：
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陆亚辉, 牛淑贞, 张子健, 等. 侧壁约束下三维燃烧室斜爆轰结构的数值研究[J]. 空气动力学学报, 2025, 43(10): 70−84.

LU Yahui, NIU Shuzhen, ZHANG Zijian, et al. Numerical investigation of three-dimensional oblique detonation structures in a combustor with sidewall confinement[J]. 2025, 43(10): 70-84.
陆亚辉, 牛淑贞, 张子健, 等. 侧壁约束下三维燃烧室斜爆轰结构的数值研究[J]. 空气动力学学报, 2025, 43(10): 70−84. DOI： 10.7638/kqdlxxb-2025.0127

LU Yahui, NIU Shuzhen, ZHANG Zijian, et al. Numerical investigation of three-dimensional oblique detonation structures in a combustor with sidewall confinement[J]. 2025, 43(10): 70-84. DOI： 10.7638/kqdlxxb-2025.0127.

摘要

超声速气流中爆轰波与边界层相互作用是影响斜爆轰发动机高效、稳定燃烧组织的关键因素，然而此前更多关注燃烧室上下壁面对斜爆轰结构的影响。本文通过求解带化学反应的雷诺平均纳维-斯托克斯方程，开展了燃烧室侧壁约束下三维斜爆轰波结构特征的数值模拟研究。结果表明，激波/爆轰波与侧壁边界层的相互作用导致局部边界层分离并诱发分离激波、拐角激波等流动结构。拐角激波逐步向展向中心区域汇聚，并在中心区域交汇，最终形成类“X”形的三维斜爆轰波面结构。“X”形波面展向上的形态取决于拐角激波相交点与喉道的相对位置：当相交点位于喉道下游，波面在展向上呈现 “M”形特征；当相交点在喉道上游，则转化为以中心波面为主导的“Ω”形结构。对失稳斜爆轰波系的分析表明，分离区的展向扩展是诱发斜爆轰波系整体结构失稳的关键机制。本研究首次揭示了侧壁约束下三维复杂斜爆轰波系的形成与失稳机制，可为斜爆轰发动机燃烧室流道的优化设计提供参考。

Abstract

The interaction between detonation waves and boundary layers in supersonic flows plays a critical role in achieving efficient and stable combustion in oblique detonation engines (ODEs)

directly affecting their thrust performance and operational reliability. Previous studies have shown that interactions between oblique detonation waves (ODWs) and the upper wall of the combustor can trigger local flow blockage

resulting in flow field instability. In practical ODE configurations

the combustor is typically confined by sidewalls

introducing combined effects from both upper and lateral boundary layers. In this study

three-dimensional numerical simulations are conducted by solving the Reynolds-averaged Navier-Stokes equations with chemical reactions to investigate the structure and instability mechanisms of ODWs under sidewall constraints. The results reveal that the interaction between shock/detonation waves and boundary layers induces local boundary layer separation and generates complex flow structures such as separation shocks and corner shocks. As the corner shocks converge toward the center in the spanwise direction and intersect near the channel centerline

an "X-shaped" three-dimensional detonation front is ultimately formed. The spanwise morphology of the X-shaped front depends on the relative position between the shock intersection point and the throat: when the intersection occurs downstream of the throat

an "M-shaped" wavefront forms; conversely

when the intersection is upstream

the structure transitions to a central "Ω-shaped" pattern. Further analysis of unstable ODWs reveals that the spanwise expansion of the separation region is the key mechanism leading to global instability of the detonation wave system. This study

for the first time

elucidates the formation and destabilization mechanisms of complex three-dimensional ODWs under sidewall confinement

providing insights for the optimized design of ODE combustor flow paths.

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references

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