摘要
近年来,旋转爆震成为航空推进技术领域的重要发展方向,射流冷却可作为缓解旋转爆震燃烧室热保护挑战的措施之一。针对旋转爆震燃烧室在运行过程中存在较大热负荷问题,设计了射流冷却通道并通过实验的方法研究了射流冷却通道结构的H2/Air旋转爆震波传播特性。H2作为燃料,从120个小孔喷入燃烧室,空气在燃烧室前端分流,一部分作为氧化剂由径向环缝进入燃烧室,一部分作为冷却气进入冷却通道。通过控制氢气的质量流率来改变来流反应物的总当量比,在0.3~1.2的范围内依次得到了锯齿波、双波对撞、单波和双波4种模态。实验得到的4种模态中,单波模态下得到的压力波幅值最大,最大值约为7 bar,且随着当量比的增加,波峰压力和压力波速度也随之增加。锯齿波模态下波峰压力最小,最大值小于1 bar。通过对射流冷却条件下的旋转爆震发动机进行实验研究,得到了4种压力波模态以及爆震波的传播特性,研究结果可用来评估旋转爆震燃烧室射流冷却的效果,并为后续与涡轮组合做铺垫。
In recent years,rotating detonation has become an important development direction in aviation propulsion technology.Jet cooling can be used as one of the measures to alleviate the challenges of thermal protection of rotating detonation combustors.During operation,rotating detonation combustors experience a significant thermal load.This paper experimentally investigates the propagation characteristics of H 2/Air rotating detonation waves in a combustor with jet cooling channels.H 2 is used as fuel and sprayed into the combustor from 120 small holes.The air is split at the front end of the combustor.Part of it enters the combustor through the radial annular gap as an oxidant,and the other enters the cooling channel as a cooling gas.By controlling the mass flow rate of H 2 to change the total equivalence ratio of the incoming reactants,four modes of sawtooth wave,dual-wave collision,single wave and dual-wave are obtained in the range of 0.3~1.2.The pressure wave amplitude obtained in the single-wave mode is the largest,maximum value of about 7 bar,with the increase of the equivalence ratio,the peak pressure and pressure wave velocity also increase accordingly.Through experimental research on rotating detonation engines under jet cooling conditions,four pressure wave modes and the propagation characteristics of detonation waves were obtained.The research results can be used to evaluate the effect of jet cooling in rotating detonation combustors and pave the way for subsequent combinations with turbines.
作者
杨成龙
汪瑞
周胜兵
YANG Chenglong;WANG Rui;ZHOU Shengbing(AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,China;College of Aerospace Engineering,Chongqing University,Chongqing 400044,China)
出处
《兵器装备工程学报》
北大核心
2025年第8期176-184,共9页
Journal of Ordnance Equipment Engineering
基金
国家自然科学基金项目(12302434)
中央高校基本业务费(2024CDJXY009)。
关键词
旋转爆震
射流冷却
爆震波模态
爆震波传播特性
当量比
rotating detonation
jet cooling
detonation wave mode
propagation characteristics of detonation waves
equivalence ratio
作者简介
杨成龙(1988—),男,博士,工程师;通信作者:周胜兵(1992—),男,博士,讲师ꎬE-mail:zhounjust@163.com.
