涡轮盘/榫整体结构优化设计方法
Method of structural optimization design for turbine disk/tenon
-
摘要: 考虑到榫联接和轮盘子午面在结构设计时的相互影响,针对典型的枞树型榫联接,提出了通用的榫联结构/轮盘子午面分步优化设计、总体协调的涡轮盘/榫整体结构优化设计方法.基于ANSYS优化平台及参数化建模技术,筛选了优化设计变量,以涡轮盘/榫整体结构总质量最小为优化目标,以涡轮盘/榫联结构关键应力为约束,建立了涡轮盘/榫整体结构优化设计的数学模型.通过对某型发动机涡轮盘和榫联结构设计方案进行结构优化设计,在满足所有几何约束及强度要求的条件下,二齿及三齿盘/榫结构优化后总质量都有明显降低,说明涡轮盘/榫整体结构优化设计方法的合理性;且二齿盘/榫结构的总质量较三齿盘/榫结构明显减小,榫槽底部最大第一主应力也明显降低.任意榫齿数可选的通用涡轮盘/榫整体结构优化设计方法及平台可适用于不同涡轮的结构设计,具有较强的工程实用性.Abstract: Considering the effect between tenon joints and meridional section of disk in structure design,a general method of structural optimization design for turbine disk/tenon was presented,including designing tenon joints/meridional section of disk in stages and synthetically optimizing with coordination.Based on ANSYS platform and parametric modeling technique,optimization design variables were chosen and a mathematic model of structural optimization design for turbine disk/tenon was established for the purpose of getting minimum masses with all constrained stresses of turbine disk and tenon joints being met.The results of the structural optimization designs of turbine disk and tenon joints for an aero-engine show that the mass of two-tooth and three-tooth disk/tenon are both decreased obviously after optimization under the condition of meeting geometry and strength requirements,which verifies the rationality of the method;the results also reveal that the structure of two-tooth disk/tenon is less mass and the maximum first principle stress lower than that of three-tooth disk/tenon.This method and platform of structural optimization design for turbine disk/tenon with any number of teeth were applied to structure designs of different turbines,which demonstrated a high engineering application.
-
[1] 陈开军,马枚.航空发动机叶片榫头优化设计研究[J].航空动力学报,1995,10(2):190-192,204. CHEN Kaijun,MA Mei.Optimization of turbine blade fir-tree roots[J].Journal of Aerospace Power,1995,10(2):190-192,204.(in Chinese) [2] Meguid S A,Kanth P S,Czekanski A.Finite element analysis of fir-tree region in turbine discs[J].Finite Elements in Analysis and Design,2000,35(4):305-317. [3] Song W,Keane A J,Rees J,et al.Local shape optimisation of turbine disc firtrees using NURBS .AIAA Paper 2002-5486,2002. [4] Song W,Keane A J.An efficient evolutionary optimisation framework applied to turbine blade firtree root local profiles[J].Structural and Multidisciplinary Optimization,2005,29(5):382-390. [5] Gean M C,Farris T N.Mechanics modeling of firtree dovetail contacts .AIAA Paper 2008-2176,2008. [6] 赵海.涡轮榫头/榫槽结构设计方法研究 .南京:南京航空航天大学,2005. ZHAO Hai.Research on design method of turbine tenon/ mortise .Nanjing:Nanjing University of Aeronautics and Astronautics,2005.(in Chinese) [7] 岳承熙,吕文林.航空涡喷、涡扇发动机结构设计准则:第二册 轮盘[M].北京:中国航空工业总公司发动机系统工程局,1997. [8] 航空发动机设计手册编委会.航空发动机设计手册:第18册 叶片轮盘及主轴强度分析[M].北京:航空工业出版社,1999. [9] 罗尔斯·罗伊斯公司.EGD-3 Spey MK202 发动机应力标准[M].丁爱祥,吴君,译.北京:国际航空编辑部,1979. [10] 吕文林.航空发动机强度计算[M].北京:国防工业出版社,1988. [11] 申秀丽,齐晓东,王荣桥,等.航空发动机涡轮榫接结构齿形基本参数研究[J].航空动力学报,2011,26(4):735-744. SHEN Xiuli,QI Xiaodong,WANG Rongqiao,et al.Research on the dentiform basic parameters of aero-engine turbine joint structure[J].Journal of Aerospace Power,2011,26(4):735-744.(in Chinese) [12] 俞茂铮.用有限元方法确定涡轮机枞树型叶根的合理结构[M].北京:国防工业出版社,1978. [13] 陆山,陶冶,鲁冯杰.轮盘结构方案设计及重量预估 .第十五届发动机结构强度与振动学术交流会论文集.杭州:中国航空学会,2010:372-379. [14] 刘长福,邓明.航空发动机结构分析[M].西安:西北工业大学出版社,2006. [15] 北京航空材料研究所.航空发动机设计用材料数据手册[M].北京:中国航空发动机总公司,1990.
点击查看大图
计量
- 文章访问数: 1978
- HTML浏览量: 2
- PDF量: 782
- 被引次数: 0