多级失谐非线性叶盘复杂系统动力学特性及减振优化方法研究

Aero engine is one of the core technologies that constitute the national military strategy, and it is also one of the bottlenecks that restrict the development of the whole aviation industry in China. For aero engine bladed disc system, combined with the problem of mistuning in engineering practice, the dynamic analysis model of multistage mistuning nonlinear bladed disc complex system is established. This paper presents a dynamic response calculation method for multi-boundary structure modal synthesis super-element and multi-region implicit cooperative analysis. The problem of large-scale computation and convergence of traditional multistage complex nonlinear structures is solved. The coupling mechanism of different cascade discs is explored, and the influence of key factors to mistuning vibration are obtained. It is of great scientific significance to reveal the behavior mechanism of the mistuning structure. A multi-objective and multi-constraint taboo genetic cat group hybrid algorithm is proposed. Innovation of multi thread parallel mechanism based on CUDA is carried out, which Improves efficiency and precision. In addition, combined with CAE parameterized drive, a joint optimization method is proposed. It is contributed to realize the accurate prediction of the optimal sorting of the detuned blade with scientific and engineering significance, and enrich the theory and method of optimization analysis; Furthermore, based on the test of dynamic test, the correctness of the model, the solution method of response and the method of the optimization analysis are verified. According to the theory, the dynamic characteristics of the multistage mistuning nonlinear disc complex system and the optimization analysis process of the blade order reduction are formed, and a comprehensive and effective theoretical system is establish.

航空发动机是构成国家军事战略的核心技术之一，也是制约我国整个航空工业发展的瓶颈问题之一。针对航空发动机叶盘系统，结合工程实际中的失谐问题，建立多级失谐非线性叶盘复杂系统动力学分析模型，提出多界面子结构模态综合超单元技术与多区域显隐式协同分析的动力学响应计算方法，突破传统多级复杂非线性结构的大规模计算与收敛难题，探究不同级叶盘结构间耦合机理，获得失谐振动关键因素影响规律，对于揭示失谐结构行为机理具有十分重要的科学意义；提出多目标多约束禁忌遗传猫群混合算法，基于CUDA的多线程并行机制改造创新，提高效率与精度，结合CAE参数化驱动提出联合优化方法，实现具有科学与工程意义的失谐叶片最优排序准确预测，丰富优化分析的理论与方法；基于动测试验验证课题建模、响应求解方法、优化分析方法的正确性；由此形成多级失谐非线性叶盘复杂系统动力学特性及叶片排序减振优化分析流程，建立系统、有效的理论体系与分析方法。

航空发动机是精密、复杂的高科技产品，日益向高负荷、高效率和高可靠性的趋势发展，以满足高性能要求，确保安全可靠的运行。叶盘系统作为航空发动机的关键零部件，其工作条件十分复杂，承受着气动力、离心力、振动等综合作用，同时叶片的材料越来越轻薄，非常容易出现故障，导致叶盘系统的振动问题越来越显著，这极大地影响了航空发动机的稳定运行，并限制了新型航空发动机的发展。针对叶盘系统进行动力学特性及优化方法研究是实现结构可靠运行的关键途径，具有重要的研究意义。本课题针对航空发动机压气机等结构中的叶盘系统，结合工程实际中的失谐问题，建立了失谐非线性叶盘复杂系统动力学分析模型，提出了基于多界面预应力 CMS 超单元技术与显隐式相结合的动力学分析方法，突破了传统复杂非线性结构的大规模计算与收敛难题，获得了失谐振动关键因素影响规律；提出了基于CUDA多线程并行机制的多目标多约束禁忌遗传猫群混合算法，结合CAE参数化驱动提出联合优化方法，实现了具有科学与工程意义的失谐叶片最优排序准确预测；自主搭建了失谐叶盘振动实验测试系统，完成了失谐叶盘系统失谐识别与振动测试分析，并拓展了随机失谐叶盘分析方法。针对上述研究成果，申请人以第一/通讯作者身份发表相关SCI检索论文21篇，其中ESI高倍引论文3篇，以副主编身份出版《失谐叶盘针对分析与优化方法》专著1部，并获批中央军委装备发展部国防出版基金，进一步申请获批主持航空发动机及燃气轮机重大专项基础研究项目子课题1项，国家重点研发计划子课题1项，参加非线性振动、转子动力学、多体动力学等相关国内外学术会议5次。