Research on turbofan engine HP-compressor rotor-12 blade tip clearance control

LUO Fei-teng; SONG Wen-yan; LI Jian-ping; LI Qiang

Chinese

您当前的位置：

首页 >

文章列表页 >

Research on turbofan engine HP-compressor rotor-12 blade tip clearance control

更新时间：2026-07-07

- Research on turbofan engine HP-compressor rotor-12 blade tip clearance control
- Vol. 24, Issue 4, (2009)
- 作者机构：
  
  西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
移动端阅览
LUO Fei-teng, SONG Wen-yan, LI Jian-ping, et al. Research on turbofan engine HP-compressor rotor-12 blade tip clearance control[J]. 2009, 24(4).
DOI：

LUO Fei-teng, SONG Wen-yan, LI Jian-ping, et al. Research on turbofan engine HP-compressor rotor-12 blade tip clearance control[J]. 2009, 24(4). DOI：

摘要

以某型发动机为对象

采用CFD数值模拟

研究了高压压气机12级孤立转子在不同叶尖间隙值下的单通道流动细节

分析和比较了不同叶尖间隙值下该级转子的压比和效率

获得了最佳性能前提的叶尖间隙值

并讨论了最佳间隙下的流场结构.结合ANSYS有限元软件评估了转子叶片和轮盘在热-结构耦合作用下的径向应变.研究结果对改进转子叶尖间隙装配和控制具有较好的参考价值.

Abstract

Using CFD numerical simulation method

the single-passage flowfield of high pressure compressor rotor-12 with different tip clearances were investigated

and the corresponding total pressure ratio and efficiency were analyzed and compared

then a tip clearance value of optimal performance was obtained.The flowfield structure under optimal performance was discussed next.Finally

based on the finite element analysis software——ANSYS

the radial strain of rotor blade and disc

which are under coupled effect of thermal-structure

were estimated.The research results provide good reference for rotor blade tip clearance assembling and control.

关键词

Keywords

references

Views

463

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Analysis of matching characteristic of transonic tandem stator airfoil and its optimization

Intensity analysis of blades in axial compressor with inlet distortion

Numerical simulation of the effect of total pressure inlet distortion on a compressor rotor

Investigation of off design performance of a transonic compressor with circumferential grooves

Unsteady numerical simulation on transonic compressor with screwed slots casing treatment

Related Author

TAO Yuan

YU Xian-jun

LIU Bao-jie

ZHANG Ming-ming

HOU An-ping

HE Xiao-fan

LI Shao-bin

LIANG Chao

Related Institution

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

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

School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics

School of Aerospace, Tsinghua University

The Second Artillery Engineering College

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