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本文对航空发动机涡轮盘设计流程进行了研究和探索,基于UG二次开发和ANSYS开发一套涡轮盘快速设计平台。针对涡轮盘结构特点提出了自定义特征的参数化建模形式,在UG二次开发基础上利用VC++编写接口函数,并采用APDL编写的强度校核和优化模块,使整个设计过程更加直观、简洁,从而实现了缩短涡轮盘设计周期目的。
In this paper, aeroengine turbine disk design flow research and exploration, UG secondary development based on UG and ANSYS development of a turbine disk rapid design platform. Aiming at the structural characteristics of turbine disk, a parametric modeling form with custom features is proposed. Based on the secondary development of UG, the interface functions are written using VC ++ and the strength checking and optimization module written by APDL is adopted to make the whole design process more intuitive and concise , Thus realizing the purpose of shortening the design cycle of the turbine disk.