Effect of blade bowing and local modification on high-turning angle compressor stator performance

LI Shao-bin; SU Jie-xian; FENG Guo-tai; WANG Zhong-qi

Chinese

您当前的位置：

首页 >

文章列表页 >

Effect of blade bowing and local modification on high-turning angle compressor stator performance

更新时间：2026-07-07

- Effect of blade bowing and local modification on high-turning angle compressor stator performance
- Vol. 22, Issue 3, (2007)
- 作者机构：
  
  哈尔滨工业大学能源科学与工程学院,哈尔滨,150001
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2007
- 稿件说明：
移动端阅览
LI Shao-bin, SU Jie-xian, FENG Guo-tai, et al. Effect of blade bowing and local modification on high-turning angle compressor stator performance[J]. 2007, 22(3).
DOI：

LI Shao-bin, SU Jie-xian, FENG Guo-tai, et al. Effect of blade bowing and local modification on high-turning angle compressor stator performance[J]. 2007, 22(3). DOI：

摘要

通过数值模拟对具有51°叶型折转角的环形扩压叶栅进行了研究.将外流飞行器上控制附面层流动的基本思想和修型措施应用于弯叶片的局部修型

结合近壁面附面层流动和总压损失对比分析了大折转角扩压叶栅采用直叶片、弯叶片和局部修型弯叶片的气动性能.结果表明:在大折转角、高亚声速气流进口条件下

局部修型弯叶片能更有效的控制大逆压梯度下叶栅内附面层的发展

提高叶栅气动性能.

Abstract

This paper presents a numerical study of a high-turning angle compressor stator with 51°.The main ideas and local modification to achieve better control of boundary layer flow in aircraft are applied to the contouring of bowed stator.The skin friction line of suction side and total pressure loss are discussed in the straight blade

bowed blade and local modified bowed blade.The results show that the local modified bowed blade can effectively control the boundary layer flow and it is applicable to the boundary conditions of high adverse pressure gradient

high-turning and high subsonic inlet velocity.

关键词

Keywords

references

Views

468

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Prediction method on equivalent thermal conductivity coefficient of plain braided C/SiC composites material based on finite element method

Aerodynamic characteristics of design Mach number of 5 two-dimensional inlet with mixed-compression under typical condition

Computation of effect of different nozzle parameters on internal performance of convergent-divergent axisymmetric nozzle

Study of novel flow control concept for fix-geometry two-dimensional mix-compression supersonic inlet

Numerical investigation on the effect of bowed blade to aerodynamic performance of low pressure turbine under stage condition

Related Author

LU Si-da

GAO Xi-guang

SONG Ying-dong

WENG Xiao-chai

GUO Rong-wei

ZHU Dan-dan

SHAO Wan-ren

WENG Xiao-chai

Related Institution

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

Department of Power and Propulsion, School of Engineering, Cranfield University, Bedfordshire MK4

State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics

Unit 94710, the Chinese People's Liberation Army

Innovation Center for Advanced Aero-Engine

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