Research on application of micro channel in the blade cooling structure

MA Shi-yan; XU Guo-qiang; DENG Hong-wu; TAO Zhi; DING Shui-ting

Chinese

您当前的位置：

首页 >

文章列表页 >

Research on application of micro channel in the blade cooling structure

更新时间：2026-07-07

- Research on application of micro channel in the blade cooling structure
- Vol. 24, Issue 9, (2009)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院, 航空发动机气动热力重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
移动端阅览
MA Shi-yan, XU Guo-qiang, DENG Hong-wu, et al. Research on application of micro channel in the blade cooling structure[J]. 2009, 24(9).
DOI：

MA Shi-yan, XU Guo-qiang, DENG Hong-wu, et al. Research on application of micro channel in the blade cooling structure[J]. 2009, 24(9). DOI：

摘要

采用数值计算的方法

针对涡轮叶片中部的微小通道冷却结构进行了换热以及流阻特性的分析

得到了微小通道宽高比和肋厚高比对其特性的影响.在进口雷诺数Re=11000时

若肋厚高比一定

则该冷却结构的综合换热效果随微小通道宽高比的增加先增加后减小;若微小通道宽高比一定

则该冷却结构的综合换热效果随肋厚高比的增加呈现先增加后减小的趋势.

Abstract

Numerical method was used to analyze the characteristics of heat transfer and flow resistance in micro channels in the middle of turbine blades;and the effect of aspect ratio and the rib aspect ratio in the micro channels was also studied.The result shows: in the case of the inlet Re=11000

if the rib aspect ratio is invariable

and the aspect ratio of micro channel increases

the integrated effect of heat transfer will increase firstly and then decrease;if the aspect ratio is invariable

and the rib aspect ratio increases

the integrated effect of heat transfer also will increase firstly and then decrease.

关键词

Keywords

references

Views

452

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Experiment on the effects of side load and pipe diameter on the characteristics of boiling two-phase pipe flow

ICT assisted detection for remainders in the internal cooling channel of the turbine blade

Effects of hot-gas wall nickelage and cooling channel inflow on regenerative cooling

Creep of Ni-based single crystal superalloy: finite element analysis of blade creep

The Interior Heat Transfer Characteristics of Gas Turbine Blade Due to Sparse Film Cooling Holes

Related Author

SHAN Shao-rong

SONG Bao-yin

MA Qi-cheng

YANG Min

SUN Jing-jing

LI Xing-dong

WEI Dong-bo

KANG Yu-dong

Related Institution

School of Astronautics, Beijing University of Aeronautics and Astronautics

Beijing Institute of Aeronautical Materials, China Aviation Industry Corporation

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

Nanjing University of Aeronautics and Astronautics

th Dept.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