自动优化技术在涡轮设计中的应用  

Application of Automatic Optimization Technology in Turbine Design

作　　者：陈云 宋立明[2] 王雷 殷林林 那振喆 CHEN Yun;SONG Li-ming;WANG Lei;YIN Lin-lin;NA Zhen-zhe(AECC Shenyang Engine Research Institute,Shenyang 110015,China;Institute of Turbomachinery,Xi’an Jiao tong University,Xi’an 710049,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015 [2]西安交通大学叶轮机械研究所,西安710049

出　　处：《航空发动机》2021年第4期59-66,共8页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了提升计算机辅助的自动优化设计技术在航空发动机涡轮设计中应用的有效性,基于计算机辅助设计技术、CFD仿真技术和智能优化算法,构建了集2维叶型设计优化和3维优化于一体的轴流涡轮设计优化体系。采用结合几何参数法和非均匀B样条曲线发展了鲁棒性强、适应范围广的基元叶型参数化造型方法, 结合自动结构化网格剖分、高精度CFD求解程序和智能优化算法,开发了针对工程的高效涡轮2维叶型设计优化软件, 以基元叶型为基础,发展了包括涡轮叶片3维积叠、扭转及子午流道型线调整的涡轮3维参数化方法, 耦合商业CFD软件和智能优化算法,开发了级环境下涡轮3维优化设计软件。利用3维优化设计软件开展了某单级跨声速高压涡轮和高低压涡轮过渡段优化设计,使单级高压涡轮效率提高0.62个百分点、过渡段分离流动区域大幅度减小。结果表明:涡轮自动优化技术能够满足工程应用需求,显著地提升了涡轮气动设计水平。In order to improve the application effectiveness of the computer-aided automatic optimization design technology in aeroengine turbine design,an axial turbine design optimization system integrating 2 D blade profile design optimizations and 3 D optimizations was constructed based on computer-aided design technology,CFD simulation technology and intelligent optimization algorithm.Based on the geometric parameter method and NURBS(Non-uniform B-Spline curves),a robust and widely-adaptive parameterization modeling method of elemental blade profile was developed.Combined with automatic structured mesh generation code,high-precision CFD solver and intelligent optimization algorithm,an efficient engineering-oriented 2 D turbine blade design optimization software was developed.Based on the elemental blade profile,the turbine 3 D parameterization method including blade 3 D stacking,twisting and meridional channel adjustment was developed.Coupled with commercial CFD software and intelligent optimization algorithm,a turbine 3 D optimization software was developed under stage conditions.3 D optimization design software was used to optimize the transition section of single-stage transonic high-pressure turbine and an intermediate turbine duct.The efficiency of the single-stage high-pressure turbine was increased by 0.62 percentage points,and the separation flow area in the transition section was greatly reduced.The results show that the requirements of engineering application can be met by the turbine automatic optimization technology and the level of turbine aerodynamic design can be significantly improved.

关 键 词：涡轮 自动优化设计 叶型 航空发动机 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]