航 空 发 动 机 燃 烧 不 稳 定 性 预 测 及 控 制 研 究 进 展

The problem of combustion instability widely exists in various types of aero-engine combustion chambers. This problem is the result of the coupling between the unsteady heat release of the flame and acoustic waves. Its occurrence is accompanied by a large pressure pulsation，which seriously threatens the stable operation and structural safety of the engine. At present，all aero-engine development countries have encountered serious combustion instability problems in the development process of most engine models. The more advanced the engine is，the more complex and difficult it is to solve the problem. It is of great significance for the development of aero-engines to accurately predict and design effective control methods based on its occurrence mechanism. The research status of this problem is systematically described. The key factor of the problem is introduced，that is，the unsteady flow and flame response characteristics of the military bluff body combustion afterburner and the civil lean premixed annular combustor. Furthermore，the eigenvalue-based predictive acoustic network models commonly used in the study of this problem are reviewed. The three-dimensional combustion instability prediction model developed by our team is highlighted，which considers the acoustic soft wall control design of the combustion chamber wall. Based on this model，the research progress of the influence of the parameters and layout of the wall acoustic lining on the combustion instability mode is reviewed，providing technical reserves for improving the combustion instability troubleshooting capability.