结构边界受扰动下翼柱与环槽型固体火箭发动机燃烧室压力振荡特性研究  

Pressure oscillation characteristics of flow field infinocyl and axil configuration solid rocket motorswith structural boundary disturbed

作　　者：陈林君 曹军 程书 石钦 明爽 郜冶[3] 侯凯宇 CHEN Linjun;CAO Jun;CHENG Shu;SHI Qin;MING Shuang;GAO Ye;HOU Kaiyu(The 41st Institute of the Fourth Academy of CASC,Xi’an 710025,China;The Fourth Academy of CASC,Xi’an 710025,China;College of Aerospace and Civil Engineering,Harbin Engineering University,Harbin 150000,China;Shanghai Academy of Spaceflight Technology,Shanghai 201109,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所,西安710025 [2]中国航天科技集团有限公司第四研究院,西安710025 [3]哈尔滨工程大学航天与建筑工程学院,哈尔滨150000 [4]上海航天技术研究院,上海201100

出　　处：《固体火箭技术》2023年第1期67-78,共12页Journal of Solid Rocket Technology

摘　　要：为研究固体火箭发动机结构振动和燃烧室压力振荡耦合作用下的不稳定燃烧现象,通过考虑结构振动对推进剂燃速的影响,将结构振动和压力振荡进行耦合。使用数值方法研究了两种典型装药(翼柱和环槽型装药)的固体火箭发动机在结构边界受扰动作用下的燃烧室内的压力振荡特性。计算结果表明,在结构脉冲加速度载荷的激励下,燃烧室中产生的压强振荡以一阶声频为主,发动机结构振动也表现出相似的特性。发动机结构的呼吸模态频率同燃烧室声模态频率的相接近会导致自激振荡现象的发生,从而大幅增强压力和结构振动的幅度。因而避免燃烧室声频同结构呼吸模态频率相接近,可以抑制不稳定燃烧现象的发生。此外,燃烧室的特殊几何结构可以对压力振荡起到明显的阻尼作用。使用环向开槽结构替代翼柱结构可以明显提高燃烧室的稳定性。To study instability combustion of solid rocket motor with the coupling between structural vibration and combustion chamber pressure oscillation,the structural vibration and pressure oscillation are coupled by considering the influence of structural vibration on the burning rate of propellant.In this paper,the numerical simulation methods were used to analyze the characteristics of the pressure oscillation in the two kinds of typical solid rocket motor chamber(finocyl and axil grain)with the structural excitation.The results show that with the excitation of the impulse structural acceleration load,the pressure oscillation of the first-order acoustic frequency is dominant,and the structural vibration characteristics of motor are also similar.The closeness of the structure breathing modal frequency to the acoustic frequency of the chamber can lead to a resonance phenomenon that greatly increases the amplitude of the pressure and structural vibrations.Therefore,it is possible to suppress the occurrence of combustion instability in the chamber from avoiding the closeness between the acoustic frequency and the structural breathing mode frequency.In addition,the special geometry of the chamber can significantly dampen pressure oscillations.At the same time,various calculation results show that the using the axil to replace the finocyl in the grain can improve the stability of chamber.

关 键 词：不稳定燃烧 压力振荡 振荡流场 结构边界扰动 固体火箭发动机 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]