基于主动热载荷管理技术的涡轮盘疲劳寿命

为降低航空发动机涡轮盘失效风险并提高使用寿命,将主动热载荷管理技术应用于预置裂纹的涡轮盘模型,采用通用权函数法计算裂纹应力强度因子进而分析轮盘寿命,研究经主动热载荷管理的轮盘上能量分布对轮盘寿命的影响,探索轮盘上热边界载荷与寿命的关联性和变化规律,并通过有限元仿真模拟初步分析其作用机理。结果表明:主动热载荷管理技术通过优化轮盘的温度分布,可以有效地降低裂纹附近的应力,延缓裂纹的扩展,显著的提高寿命和安全性,当热边界载荷系数分别取0.05和0.10时,轮盘相应的寿命分别增加12.2%和26.1%。

Fatigue life of turbine disk based on actively managed thermal loading method

In order to reduce the failure risk of turbine disk and extend its life, actively managed thermal loading method was applied to the turbine disk with pre-set crack. Meanwhile, the crack stress intensity factors were calculated by general weight function method and the life of the turbine disk was analyzed. The influence of the energy distribution based on actively managed thermal loading method on the life of the turbine disk was studied. The relationship and change trend between the thermal boundary loading and the life of the turbine disk were explored. The reason and mechanism were analyzed by finite element numerical simulation. The consequence shows that actively managed thermal loading method can effectively optimize the temperature distribution of the turbine disk, reduce the stress near the crack, delay the expansion of the crack, and significantly improve its life and safety. When the thermal boundary loading coefficient was 0.05 and 0.10 respectively, the corresponding lives increase by 12.2% and 26.1%.