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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.
Aiming at the structural and mechanical characteristics of aeroengine bearing system, based on the design requirements of safety, a method of evaluating the deformation resistance of the whole bearing system is established. From the inherent deformation resistance of the structure, the deformation resistance under steady load, Three equivalent parameters of equivalent rigidity, clearance matching coefficient and impact amplification factor are put forward in terms of the anti-deformability under state impact load. The anti-deformation capability of the typical high bypass ratio turbofan engine bearing system is evaluated. The results show that: Section equivalent stiffness and the ratio of the maximum equivalent stiffness of the load-bearing system as the equivalent stiffness of the structure, the ratio of the minimum clearance to the maximum clearance of each section of the whole system under steady load is taken as the clearance matching coefficient and the ratio of the transient impact load to each And the ratio of the maximum peak load on the upper support and the upper support is taken as the impact amplification factor.These three parameters can well reflect the dangerous position of the whole load-bearing structure and the response characteristics under the ultimate load.The final evaluation result It can provide a reference for the design and optimization of the structural design of load-bearing system.