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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2013年第1期101-108,共8页
Journal of Propulsion Technology
关键词
液体火箭发动机
中频耦合振荡
机理分析
节流圈
Liquid rocket engine
Medium frequency coupled oscillation
Mechanism analysis
Throttle orifice