碳氢燃料斜爆震燃烧室流动与热环境特性分析

刘晓英; 涂胜甲; 黄海; 周林; 张义宁

doi:10.7638/kqdlxxb-2025.0107

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碳氢燃料斜爆震燃烧室流动与热环境特性分析

研究专栏−爆震流动机理与推进技术Ⅱ | 更新时间：2026-05-28

- 碳氢燃料斜爆震燃烧室流动与热环境特性分析
- Flow and thermal environment characteristics in a hydrocarbon fueled oblique detonation combustor
- 空气动力学学报 2025年43卷第10期页码：106-121
- 作者机构：
  
  北京动力机械研究所冲压发动机技术全国重点实验室,北京,100074
- 作者简介：
  
  刘晓英（2000—），女，重庆垫江人，助理工程师，研究方向：爆震发动机热防护技术. E-mail：1014288715@qq.com
  周林*，高级工程师，研究方向：爆震燃烧与爆震发动机. E-mail：linxzhou@foxmail.com
  张义宁*，研究员，研究方向：新型空天动力技术. E-mail：13718931527@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0107
  中图分类号： V232
- 纸质出版：2025
- 稿件说明：
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刘晓英, 涂胜甲, 黄海, 等. 碳氢燃料斜爆震燃烧室流动与热环境特性分析[J]. 空气动力学学报, 2025, 43(10): 106−121.

LIU Xiaoying, TU Shengjia, HUANG Hai, et al. Flow and thermal environment characteristics in a hydrocarbon fueled oblique detonation combustor[J]. 2025, 43(10): 106-121.
刘晓英, 涂胜甲, 黄海, 等. 碳氢燃料斜爆震燃烧室流动与热环境特性分析[J]. 空气动力学学报, 2025, 43(10): 106−121. DOI： 10.7638/kqdlxxb-2025.0107

LIU Xiaoying, TU Shengjia, HUANG Hai, et al. Flow and thermal environment characteristics in a hydrocarbon fueled oblique detonation combustor[J]. 2025, 43(10): 106-121. DOI： 10.7638/kqdlxxb-2025.0107.

摘要

针对碳氢燃料斜爆震燃烧室开展流动与热环境特性三维数值仿真研究，通过典型工况下斜爆震燃烧试验验证仿真方法的准确性，分析非均匀来流条件下斜爆震燃烧室三维流场特性，研究燃料当量比与壁面热障涂层厚度对燃烧室流场结构及热环境特性的影响。研究发现，受来流掺混非均匀以及边界层等非理想效应影响，斜爆震燃烧室不同展向截面波系特征与燃烧特性差异显著。受斜爆震燃烧波系的主导，燃烧室壁面热流密度分布极不均匀。燃料当量比直接影响斜爆震燃烧场波系结构，使得燃烧室热环境发生改变，但不同当量比下热流密度峰值都位于斜劈前缘处，其次为侧壁面斜爆震波后区域。燃烧室侧壁面面积最大，冷却所需换热量最大，斜劈壁面次之，下壁面最小，各壁面冷却所需换热量均随当量比增大而增大。增加热障涂层对斜爆震燃烧特性影响不显著，但可有效隔绝燃烧室内高温燃气向燃烧室壁面金属基体的热量传递，显著降低燃烧室各壁面热流密度。

Abstract

This study presents a three-dimensional numerical simulation investigating the flow and thermal environment characteristics of a hydrocarbon-fueled oblique detonation combustor. The accuracy of the numerical method was validated through oblique detonation combustion experiments under typical inflow conditions. The three-dimensional flow field characteristics in the oblique detonation combustor under non-uniform inflow conditions are analyzed

with particular focus on the effects of equivalence ratio and wall thermal barrier coating thickness on the flow structures and thermal environment. Results indicate that due to non-ideal effects

such as inflow non-uniformity and boundary layer influences

the wave system and combustion characteristics exhibit significant variations across different spanwise cross-sections of the combustor. The wall thermal environment is governed by the oblique detonation combustion wave structures

leading to a highly non-uniform distribution of wall heat flux. The equivalence ratio modulates the structure of the oblique detonation combustion field

thereby altering the thermal environment. However

under various equivalence ratios

the peak wall heat flux is consistently located at the wedge leading edge and the sidewall region behind the oblique detonation wave. The sidewall has the largest area and therefore requires the most cooling

followed by the wedge wall

and then the bottom wall. The heat transfer required for cooling the combustor surface increases with the equivalence ratio. Increasing the thickness of the thermal barrier coating has negligible effects on the oblique detonation combustion characteristics but effectively insulates the metal substrate of the combustor from high-temperature combustion gases

thus significantly reducing the heat flux density at the combustor surface.

关键词

Keywords

references

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