Design of key part on turbine disk using multiarcs method and multivariable optimization

于洪飞; 赵巍; 付强; 王佰智

doi:10.13224/j.cnki.jasp.2017.12.005

Chinese

您当前的位置：

首页 >

文章列表页 >

Design of key part on turbine disk using multiarcs method and multivariable optimization

更新时间：2026-07-07

- Design of key part on turbine disk using multiarcs method and multivariable optimization
- Vol. 32, Issue 12, Pages: 2848-2854(2017)
- 作者机构：
  
  1. 中国航空发动机集团有限公司中国航空发动机研究院,北京,101304
  2. 中国航空发动机集团有限公司沈阳发动机研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.12.005
  CLC：
- Published：2017
- 稿件说明：
移动端阅览
于洪飞, 赵巍, 付强, 王佰智. 涡轮盘关键部位多圆弧设计及多变量优化[J]. 航空动力学报, 2017, 32(12): 2848-2854.

doi: 10.13224/j.cnki.jasp.2017.12.005
于洪飞, 赵巍, 付强, 王佰智. 涡轮盘关键部位多圆弧设计及多变量优化[J]. 航空动力学报, 2017, 32(12): 2848-2854. DOI： 10.13224/j.cnki.jasp.2017.12.005.

doi: 10.13224/j.cnki.jasp.2017.12.005 DOI：

摘要

为得到质量最低且满足设计准则要求的涡轮盘结构形式，研究了多圆弧过渡对涡轮盘关键部位应力的影响。提出了双圆弧和三圆弧结构设计方案并推导了几何关系，为过渡圆弧的改进与优化提供了理论上的支持。通过有限元计算，获得了多圆弧结构参数对涡轮盘应力的影响规律。基于ANSYS Workbench优化平台及参数化建模技术，筛选了优化设计变量，以涡轮盘总质量最小为优化目标，以等效应力为约束对涡轮盘关键部位进行了多变量优化。结果表明：经过优化设计，两个关键部位的最大应力分别降低662%和11.40%，涡轮盘的质量减小0.16%。本文的研究结果为涡轮盘的多圆弧设计和工程应用提供了有益参考。

Abstract

In order to obtain the structure type of turbine disk satisfying minimum masses and stress standards

the influence of multiarcs transition on stress distribution at key parts was studied. Doublearcs and threearcs structure design schemes were proposed

and geometric theory on arcs transition was derived to support the design modifications and optimization. Based on finite element calculation

the stress varying with structure parameters was obtained. Based on ANSYS Workbench platform and parametric modeling technique

optimization design variables were chosen to get minimum masses with constrained equivalent stress. Result showed that

the maximum equivalent stress on two parts decreased by 662% and 1140%

the mass of turbine disk decreased by 016%. The results provide useful references for multiarcs design and engineering applications of the gas turbine disk.

关键词

Keywords

references

Views

571

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

General transition arcs redesign and multivariable optimization of tenon-mortise joints

Simulation method of short crack propagation in turbine disks based on crystal plasticity

Flow channel scheme of U⁃shaped cooling channel in scramjet

Fatigue life prediction method based on the features of surface defects

Fatigue life evaluation procedure and its application for turbine disk

Related Author

LEI Chi

WEN Wei-dong

CUI Hai-tao

Zhongbing LUO

Rongxin ZHOU

Mao YANG

Xin JING

Shan LU

Related Institution

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

School of Power and Energy，Northwestern Polytechnical University

Nondestructive Testing and Evaluation Laboratory， Dalian University of Technology

College of Civil Engineering， Hefei University of Technology

College of Aerospace Science and Engineering，National University of Defense Technology

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰