基于网格变形的涡轮盘挡板结构形状优化方法

Turbine disk baffle structure shape optimization method based on mesh deformation

中文关键词: 形状优化  网格变形  航空发动机  无螺栓挡板  配合间隙

英文关键词: shape optimization  mesh deformation  aero-engine  boltless baffle  fit clearance

中文摘要:

      为了实现涡轮盘挡板结构的形状优化，需要对其形状进行参数化描述和设计，而传统的基于几何模型的参数化方法需要在优化过程中重复生成网格模型，不仅耗时而且难以保证网格质量，难以满足形状优化设计要求。因此，提出了一种基于网格变形技术的挡板结构形状优化方法。首先，建立了一种基于少量控制点驱动的网格变形技术，该技术在不改变CAD模型的情况下，通过控制点移动单元节点产生新的有限元模型。然后，以控制点位移作为设计变量，采用网格变形技术驱动挡板结构形状改变，高效地实现结构形状优化设计。最后，开展了航空发动机涡轮盘挡板结构形状优化设计，验证了所提出方法的有效性，数值结果表明，所提出的方法能够有效避免优化过程中的网格重剖分，提高了结构形状优化效率，获得了满足配合间隙要求的低应力涡轮盘挡板结构设计方案。

英文摘要:

      In order to carry out the shape optimization for the baffle structure of the turbine disk, the shape needs to be de-scribed parametrically. The classical geometry-based parametric method requires repeated generation of FE mesh models in the optimization. This is not only time consuming but also difficult to guarantee the mesh quali-ty for shape optimization. Therefore, a shape optimization method for baffle structure based on mesh defor-mation is proposed in this paper. First, a mesh deformation technique driven by a small number of control points is established, which generates a new FE model by moving element nodes without changing the CAD model. Then, with the control point displacement as the design variables, the mesh deformation is used to drive the shape change of the baffle structure and achieve the structural shape optimization efficiently. Finally, the effec-tiveness of the pro-posed method is verified by the baffle structure of the turbine disk in aero-engine. The nu-merical result shows that the proposed method can avoid the re-meshing in the optimization, improve the effi-ciency of shape optimization, and obtain the low-stress design of the baffle structure of the turbine disk that meets the fit clearance requirements.