液体火箭发动机中频耦合振荡初步研究  

Preliminary Study of Medium Frequency Coupled Oscillation in Liquid Rocket Engine

作　　者：刘上[1] 刘红军[1] 孙宏明[1] 陈宏玉[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《推进技术》2013年第1期101-108,共8页Journal of Propulsion Technology

摘　　要：为了研究常规液体火箭发动机研制中出现的中频流量型耦合振荡问题,对发动机耦合系统中各环节建立了满足声学分析的线性化频域模型。通过比较供应系统和燃烧室的幅频响应,并分析耦合系统的自由振荡复频率,以判断发动机的耦合稳定性。计算结果符合发动机试车规律,能够有效地反映该类型不稳定的特征。进一步讨论了燃烧时滞、喷注压降、管路长度和安装节流圈对系统耦合不稳定的影响规律,并揭示了该类型不稳定的机理。In order to investigate the medium frequency coupled oscillation encountered during the stor- able liquid propellant rocket engine development, the linear frequency-domain models for every component satisfying acoustics analysis were established. By comparing the response of feed system and chamber, and analyzing the natural oscillation complex frequency of the coupled system, the engine system coupled stabili- ty at different conditions was estimated. The calculated results accord with the engine test phenomena, by which the characteristics of this kind instability can be described effectively. Moreover, the influence of combustion time lag, injection pressure drop, feed pipe length and throttle orifice on the system coupled in- stability was discussed. Thus the mechanism of the instability was identified.

关 键 词：液体火箭发动机 中频耦合振荡 机理分析 节流圈 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]