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

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

Chinese

您当前的位置：

首页 >

文章列表页 >

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

更新时间：2026-07-07

- Displacement transfer with the mesh deformation method in multidisciplinary optimization of turbine blades
- Vol. 22, Issue 12, (2007)
- 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：2007
- 稿件说明：
移动端阅览
LI Li-zhou, WANG Jing-chao, HAN Yong-zhi, et al. Displacement transfer with the mesh deformation method in multidisciplinary optimization of turbine blades[J]. 2007, 22(12).
DOI：

LI Li-zhou, WANG Jing-chao, HAN Yong-zhi, et al. Displacement transfer with the mesh deformation method in multidisciplinary optimization of turbine blades[J]. 2007, 22(12). DOI：

摘要

为实现学科耦合

需要在涡轮叶片多学科设计优化的气动模型和结构模型之间传递温度、气压和变形等载荷.研究结构变形向气动网格传递的实现方法.参数空间插值方法解决耦合面网格不一致时的变形插值问题;网格变形技术用来调整气动网格内部节点的位置

保证变形传递后的网格质量.某涡轮叶片变形传递实例的表明:该方法能够用于多学科设计优化问题中的变形传递.

Abstract

A mesh-deformation-based method was provided in transferring structural displacements to aerodynamics meshes for multidisciplinary optimization of turbine blades.The method focuses on disturbing interior nodes of aerodynamics meshes to keep mesh-quality for the deflected blades.The nodes was disturbed as if they are in a deformed solid under displacement loads.This solid represented the interrelationship of nodes of the aerodynamics meshes.Adisplacement transfer of a turbine blade was provided.The results indicate that the mesh-deformation-based method work well for the displacement transfer.

关键词

Keywords

references

Views

470

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Turbine blade displacement transfer based on mesh regeneration method

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

XU Lei

CHANG Hai-ping

PAN Jin-dong

LI Guang-chao

ZHU Hui-ren

LIAO Nai-bing

XU Du-chun

SONG Shuang-wen

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