This study focuses on a mixed mode crack growth analysis of an aviation gas turbine engine (GTE) compressor disk based on simulation principles. The operation damages occur via inclined surface cracks in a “dovetail type” disk-and-blade attachment. Based on the sizes and configuration of this attachment, three geometries for simulation models of the GTE compressor disk are proposed. The biaxial loading conditions of the simulation models are determined and numerically verified to reproduce the stress-strain state in critical zones of the compressor disk during operation. To determine the elastic-plastic fracture mechanical parameters, a 3D full-size finite element method (FEM) analysis is conducted for the GTE compressor disk and simulation models, based on operating loading conditions. As a result, the distributions of the new mixed-mode fracture resistance parameters in the form of equivalent elastic and plastic stress intensity factors along the crack front in the disk-and-blade dovetail-type attachment are applied to the experimental uniaxial and biaxial data for crack growth rate interpretation. The possibility of using the proposed simulation principles for an assessment of the structural integrity of GTE rotating disks is discussed.

这项研究的重点是基于模拟原理的航空燃气涡轮发动机（GTE）压缩机盘的混合模式裂纹扩展分析。操作损坏是通过“燕尾型”磁盘和刀片附件中的倾斜表面裂纹产生的。基于此附件的尺寸和配置，提出了用于GTE压缩机盘模拟模型的三种几何形状。确定仿真模型的双轴加载条件，并进行数值验证，以重现运行过程中压缩机盘关键区域的应力应变状态。为了确定弹塑性断裂力学参数，基于运行载荷条件，对GTE压缩机盘和仿真模型进行了3D全尺寸有限元方法（FEM）分析。因此，将新的混合模式抗断裂参数以等效的弹性和塑性应力强度因子的形式沿磁盘-叶片燕尾型附件的裂纹前沿分布，用于实验单轴和双轴数据的裂纹扩展速率解释。讨论了使用拟议的仿真原理评估GTE转盘结构完整性的可能性。