壁面冷却条件下入射斜爆震波/平板边界层干扰特性

仝晓通; 王煜沣; 陈正

doi:10.7638/kqdlxxb-2025.0087

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壁面冷却条件下入射斜爆震波/平板边界层干扰特性

研究专栏——爆震流动机理与推进技术专栏Ⅰ | 更新时间：2026-05-28

- 壁面冷却条件下入射斜爆震波/平板边界层干扰特性
- Incident oblique detonation wave/boundary layer interaction on a cooled plate
- 空气动力学学报 2025年43卷第9期页码：115-126
- 作者机构：
  
  北京大学工学院,北京,100871
- 作者简介：
  
  仝晓通（1993—），男，河南南阳人，博士后，研究方向：高速吸气式动力. E-mail：tongxt@pku.edu.cn
  陈正*，教授，研究方向：燃烧学. E-mail：cz@pku.edu.cn
- 基金信息：
  
  国家自然科学基金（12402383，124B1016）
- DOI：10.7638/kqdlxxb-2025.0087
  中图分类号： V235.2
- 纸质出版：2025
- 稿件说明：
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仝晓通, 王煜沣, 陈正. 壁面冷却条件下入射斜爆震波/平板边界层干扰特性[J]. 空气动力学学报, 2025, 43(9): 115−126.

TONG Xiaotong, WANG Yufeng, CHEN Zheng. Incident oblique detonation wave/boundary layer interaction on a cooled plate[J]. 2025, 43(9): 115-126.
仝晓通, 王煜沣, 陈正. 壁面冷却条件下入射斜爆震波/平板边界层干扰特性[J]. 空气动力学学报, 2025, 43(9): 115−126. DOI： 10.7638/kqdlxxb-2025.0087

TONG Xiaotong, WANG Yufeng, CHEN Zheng. Incident oblique detonation wave/boundary layer interaction on a cooled plate[J]. 2025, 43(9): 115-126. DOI： 10.7638/kqdlxxb-2025.0087.

摘要

斜爆震发动机燃烧室壁面热流量高，需进行热防护设计。已有研究大多考虑绝热壁面，壁面冷却对燃烧与流动的影响尚不清晰。本文针对简化收缩通道，通过二维数值模拟研究了绝热和等温壁面条件下的入射斜爆震波/平板边界层干扰特性。结果表明，随着平板壁温降低，边界层内燃烧被抑制，边界层分离区尺度减小，分离激波角增大，壁面摩擦系数和壁面压力峰值升高。高静压下，在一定楔角范围内，壁面冷却可导致分离斜爆震波转变为分离斜激波；而低静压下，分离区迎风面起爆困难，且分离区尺度对壁温更敏感。气流再附导致平板热流出现峰值。高静压（高雷诺数）下，分离区与平板之间的对流传热强度存在上限。最后，本文还利用数值模拟结果校核并修正了分离区热流峰值与压力峰值之间的关联关系，建立了壁面冷却条件下的分离长度标度律，并给出了幂函数形式的工程估算公式。本文研究可为斜爆震燃烧室冷却系统设计及分离区调控提供一定的参考。

Abstract

The combustor of a practical oblique-detonation engine requires thermal protection due to the high wall heat flux. Previous studies

mostly focusing on inviscid or viscous adiabatic flow over a wedge

have not clearly elucidated the effects of wall cooling on combustion and flow characteristics within the combustor. In this study

two-dimensional viscous numerical simulations are performed across a range of wedge angles and static pressures to investigate the interaction between an oblique detonation wave (ODW) and a boundary layer developing on either an adiabatic or an isothermal flat plate. The results indicate that as the wall temperature decreases

combustion within the boundary layer is suppressed

the separation region shrinks

and the separation-shock angle increases. Meanwhile

both the skin-friction coefficient and the peak wall pressure increase. At high pressures (high Reynolds numbers)

within a limited range of wedge angles

wall cooling can convert a separation-induced oblique detonation into an oblique shock by reducing the effective aerodynamic length of the separation region; whereas at low pressures (low Reynolds numbers)

oblique-detonation initiation on the windward side of the separation region is inhibited and the separation length becomes more sensitive to wall temperature. Flow reattachment produces a local heat-flux peak; at high Reynolds numbers

the convective heat-transfer intensity between the separation region and the wall reaches an upper limit. The numerical results are used to recalibrate the classical QP85 correlation between peak heat flux and peak pressure within the separation region

and a power-law scaling for the separation length under cooled-wall conditions is proposed.

关键词

Keywords

references

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