航空发动机承力系统抗变形能力评估

发布时间：2018-07-20 11:09

【摘要】：针对航空发动机承力系统的结构和力学特征,基于安全性设计要求,建立了整机承力系统抗变形能力的评估方法,分别从结构固有抗变形能力、稳态载荷下的抗变形能力以及瞬态冲击载荷下的抗变形能力3方面提出了当量刚度、间隙匹配系数、冲击放大系数3个评估参数.以典型高涵道比涡扇发动机承力系统为对象进行了抗变形能力评估.结果表明:以截面的等效刚度和承力系统最大等效刚度的比值作为结构当量刚度,以稳态载荷下整机系统各个截面的最小间隙与最大间隙的比值作为间隙匹配系数和以瞬态冲击载荷与各个支点及安装节上支反力的最大峰值载荷的比值作为冲击放大系数,这3个参数均能较好地反映出整机承力结构的危险位置和极限载荷下的响应特征.最终的评估结果可以为承力系统结构方案设计和优化提供参考.
[Abstract]:According to the structural and mechanical characteristics of the aero-engine load-bearing system, based on the requirements of safety design, a method for evaluating the anti-deformation ability of the whole load-bearing system is established, which is based on the inherent anti-deformation ability of the structure, respectively. Three evaluation parameters such as equivalent stiffness, clearance matching coefficient and impact magnification factor are proposed in terms of deformation resistance under steady load and deformation resistance under transient impact load. The deformability of a typical turbofan engine with high culvert ratio is evaluated. The results show that the ratio of the equivalent stiffness of the section to the maximum equivalent stiffness of the bearing system is taken as the equivalent stiffness of the structure. The ratio of the minimum gap to the maximum clearance of each section of the whole machine system under steady load is taken as the gap matching coefficient and the ratio of the transient impact load to the maximum peak load of the supporting force at each fulcrum and the mounting node is taken as the impact magnification factor. These three parameters can well reflect the dangerous position of the whole machine bearing structure and the response characteristics under the limit load. The final evaluation results can provide a reference for the structural design and optimization of the load-bearing system.
【作者单位】：北京航空航天大学能源与动力工程学院;中国航空工业集团公司沈阳发动机设计研究所;
【分类号】：V231.9

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