论文部分内容阅读
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 study the problem of medium frequency flow coupling oscillation in the development of conventional liquid propellant rocket engine, a linearized frequency domain model satisfying the acoustic analysis was established for each link in the engine coupling system. By comparing the amplitude-frequency response of the supply system with the combustion chamber and analyzing the free-oscillation complex frequency of the coupled system to determine the coupling stability of the engine. The calculation result accords with the engine test law, which can effectively reflect the unstable characteristics of this type. The effects of combustion delay, injection pressure drop, pipe length and the installation of choke ring on the instability of the system are further discussed. The instability mechanism of this type is also revealed.