为支撑航空发动机关于CCAR33.63条款的适航取证，识别潜在的叶片-机匣碰摩耦合振动危险工况，建立了基于三维接触动力学的风扇叶片-柔性机匣碰摩动力学计算模型：通过模态缩减，降低计算模型规模；利用三次B样条曲面拟合机匣内表面，提升离散精度；采用双线性弹塑性模型描述可磨涂层碰摩力学特性；基于涂层磨损深度、叶片厚度和单元形函数计算叶片与机匣间的碰摩接触力。基于本模型，研究了风扇叶片与柔性机匣的碰摩响应特性。结果显示，叶片阻尼是影响碰摩振动响应的关键因素：对于阻尼较小风扇叶片碰摩，存在机匣多节径模态行波振动导致的叶片-机匣耦合振动，碰摩过程中接触强度变化引起的叶片与机匣动力学特性的改变是造成该类耦合振动产生的原因。本文建立的动力学模型为叶片-机匣碰摩耦合振动的识别与评估提供了一种新思路。

To support the airworthiness certification of aircraft engines regarding CCAR 33.63 provisions, a three-dimensional contact dynamics-based computational model for fan blade-flexible casing rubbing vibration was established. Modal reduction was employed to reduce the size of the computational model, and a cubic B-spline surface fitting technique was used to enhance the discretization accuracy of the casing inner surface. A bilinear elastic-plastic model was adopted to describe the rubbing mechanical properties of the abradable coating, and contact forces between blades and casings were calculated based on coating wear depth, blade thickness, and element shape functions. Using this model, the rubbing response characteristics between fan blades and flexible casings were investigated. The results showed that blade damping is a key factor affecting rubbing vibration response: for blades with lower damping, in addition to coupling vibrations between bladecasing single nodal diameter modes during rubbing process, there also exist blade-casing coupled vibrations caused by traveling waves associated with multi-nodal diameter modes of casings. The variations in contact strength during rubbing process leading to changes in dynamic characteristics of components caused the above interactions. The dynamic model established in this study provides a new approach for identifying and evaluating blade-casing rubbing coupled vibrations.