Turbine blade displacement transfer based on mesh regeneration method

LI Li-zhou; WANG Jing-chao; LU Zhen-zhou; YUE Zhu-feng

Chinese

您当前的位置：

首页 >

文章列表页 >

Turbine blade displacement transfer based on mesh regeneration method

更新时间：2026-07-07

- Turbine blade displacement transfer based on mesh regeneration method
- Vol. 23, Issue 3, (2008)
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 西北工业大学力学与土木建筑学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2008
- 稿件说明：
移动端阅览
LI Li-zhou, WANG Jing-chao, LU Zhen-zhou, et al. Turbine blade displacement transfer based on mesh regeneration method[J]. 2008, 23(3).
DOI：

LI Li-zhou, WANG Jing-chao, LU Zhen-zhou, et al. Turbine blade displacement transfer based on mesh regeneration method[J]. 2008, 23(3). DOI：

摘要

在涡轮叶片多学科优化中需要在气动模型和结构模型之间进行耦合信息(气压、温度和变形等数据)传递

来考虑学科耦合的性质.采用修正几何外形和网格重生成的方法实现了叶片结构变形向气动模型传递.传递时在叶片几何模型上增加若干外形控制线

叶片的外形由这些控制线的形状来决定.根据叶片结构变形

调整控制线节点位置坐标

以修改叶片外形控制线的形状

可以实现变形向叶片几何模型的传递.进一步

重新生成气动网格

可以得到结构变形后叶片的气动网格模型.

Abstract

In multi-disciplinary design optimization(MDO) of turbine blades

the coupling data between aerodynamics and structural mechanics models must be transferred to consider the multi-disciplinary coupling property.Amesh-regeneration method was proposed to transfer displacement in this paper.Agroup of lines were added on blade surface

and the shape of blades was determined by the shape of these control lines.According to the displacement of blade structure

the position coordinate of the nodes of the lines was adjusted to modify the shape of the blade's control lines

thus achieving the displacement transfer towards geometric model of blade.By re-meshing

the CFDmesh of the deformed blade was generated.

关键词

Keywords

references

Views

461

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Displacement transfer with the mesh deformation method in multidisciplinary optimization of turbine blades

Experimental research on heat transfer of "impingement/effusion" double-plate configuration in rotating state

Influence of aerodynamic parameters on film cooling effectiveness on the vane leading edge

Influence of pin fin on the convective heat transfer characteristics of turbine blade trailing edge

New characteristics of fatigue-creep tests on serration of turbine blades

Related Author

HAN Yong-zhi

XU Lei

CHANG Hai-ping

PAN Jin-dong

LI Guang-chao

ZHU Hui-ren

LIAO Nai-bing

XU Du-chun

Related Institution

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

School of Power and Energy,Northwestern Polytechnical University

China Aviation Powerplant Research Institute

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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