火箭推进2026，Vol.52Issue(4)：78-91,14.DOI:10.3969/j.issn.1672-9374.2026.04.008
燃烧室构型对自燃推进剂旋转爆震流场及特性的影响
Influence of combustion chamber configuration on the flow field and characteristics of rotating detonation with hypergolic propellants
摘要
Abstract
To investigate the influence of combustion chamber configuration on the flow field characteristics of rotating detonation with liquid hypergolic propellants,numerical simulations of rotating detonation using MMH/NTO as propellants was conducted based on a three-dimensional Euler-Lagrangian approach,coupled with a RANS/LES hybrid turbulence model and a simplified chemical reaction mechanism.By comparison with experimental data,the numerical simulation results show that the error in the dominant frequency of detonation pressure oscillation is extremely small,which validates the accuracy and reliability of the model.On this basis,the effects of three key structural parameters,namely the combustion chamber annular gap width,throat contraction ratio,and combustion chamber length,on the propagation mode of the rotating detonation wave,pressure oscillation characteristics,and flow field structure were systematically studied.The results indicate that when the annular gap width is too small,stable detonation cannot be formed,and only medium-frequency pressure oscillations occur.As the annular gap width increases,the detonation frequency first decreases and then increases.The accuracy of traditional rocket engine design methods decreases under high contraction ratio and high chamber pressure conditions for liquid hypergolic propellant rotating detonation engines.An increase in the contraction ratio helps to raise the combustion chamber pressure and oscillation amplitude,and under the design point with a chamber pressure of 0.6 MPa,the stable self-sustaining detonation wave gradually transitions from a single-wave mode to a dual-wave mode.In the internal flow field of the combustion chamber,the detonation wave is hindered by propellant droplets,causing its morphology to exhibit irregular characteristics.Shortening the combustion chamber length reduces the mean pressure,peak pressure,and detonation wave velocity,weakening thrust performance,while also leading to blurred pressure discontinuities ahead of the detonation wave and a more dispersed heat release distribution.关键词
旋转爆震/自燃推进剂/燃烧室构型/数值仿真Key words
rotating detonation/hypergolic propellants/combustion chamber configuration/numerical simulation分类
航空航天引用本文复制引用
顾福涛,熊云灏,米力,郭康康,林伟,李晓亮..燃烧室构型对自燃推进剂旋转爆震流场及特性的影响[J].火箭推进,2026,52(4):78-91,14.基金项目
国家自然科学基金(1250022397) （1250022397）
北京市自然科学基金(L258019) （L258019）
实验室开放基金(cxzx-25-01-04). （cxzx-25-01-04）
