涡轮叶片冷却内腔扰流肋参数化建模方法  

Parameterized modeling method of turbine blade cooling inner cavity turbulence rib

作　　者：郝旭生 李洋 余毅 赵尊盛 HAO Xusheng;LI Yang;YU Yi;ZHAO Zunsheng(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;Hunan Key Laboratory of Turbomachinery on Medium and Small Aero-Engine,Zhuzhou 412002,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]中小型航空发动机叶轮机械湖南省重点实验室,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2024年第5期32-38,共7页Gas Turbine Experiment and Research

摘　　要：扰流肋是涡轮叶片内腔强化对流冷却的核心结构。为实现复杂冷却涡轮叶片扰流肋的参数化建模,提出了扰流肋参数化建模方法。首先用隔板等距面和叶盆或叶背等距面修剪扰流肋实体,保证了扰流肋的深度均匀一致;其次提出了曲线识别算法,建立扰流肋与叶身内型的联系;然后通过设计参数到建模参数的转换提高了扰流肋建模的精度和建模效率;最后采用UG Open API工具开发了扰流肋参数化建模程序,并验证了所提方法的可行性。The turbulence rib is the core structure for enhancing convective cooling in the inner cavity of turbine blades.In order to realize parameterized modeling of complex cooling turbine blade turbulence ribs,a parameterized modeling method for turbulence ribs was proposed.Firstly,the baffle isometric surface and the convex or concave isometric surface were used to trim the rib to ensure the uniform depth of the turbulence ribs.Secondly,a curve recognition algorithm was proposed to establish the relation between the turbulence ribs and the blade inner profile.Then,through the conversion of design parameters to modeling parameters,the precision and efficiency of the turbulence ribs modeling was improved.Finally,UG Open API tool was used to develop a parameterized modeling program for turbulence ribs,and the feasibility of the proposed method was verified.

关 键 词：航空发动机 扰流肋 参数化设计 涡轮叶片 内腔 建模 UG Open API 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]