高压涡轮轴安装边倒角低应力设计方法

A low stress design method on chamfer of installation edge of high pressure turbine shaft

航空发动机涡轮鼓筒轴承受着复杂的外载荷,在涡轮轴的安装边倒角处会产生应力集中,影响涡轮轴的整体寿命和性能。本文研究在扭矩、轴向力、离心力以及热应力4个载荷作用下涡轮轴安装边附近倒圆角的应力场分布,设计了单圆弧倒角方案、双圆弧倒角方案,并运用ANSYS Workbench软件对双圆弧设计方案进行优化。通过比较三种结构的应力场分布,得到涡轮轴安装边倒角的低应力设计方案。本文得到的最优双圆弧设计方案相比单圆弧设计方案,倒角处的最大等效应力降低了13.97%。

The turbine shaft of aero - engine bears complex external load, which produces stress concentration on the installation edge chamfer, thus influences the service life and performance of the turbine shaft. This paper studies the fillet stressfield distribution near the installation edge under four types of loading including torque, axial force, centrifugal force and thermal stress. Based on the result, a single circular arc chamfering scheme and a double circular arc chamfering schemeare designed, and optimization is carried on the double arc scheme using ANSYS Workbench software. By comparing stress field distribution of the three kinds of structures, a low stress design scheme for installation edge chamfer of turbine shaft isworked out. The optimal design of double circular arc in this paper reduces maximum equivalent stress of the chamfer by 13.97% compared with single arc design scheme.