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

Shao Bin Li; Jie Xian Su; Guo Tai Feng; Zhong Qi Wang

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

Shao Bin Li^*
, Jie Xian Su
, Guo Tai Feng
, Zhong Qi Wang

^*此作品的通讯作者

Harbin Institute of Technology

科研成果: 期刊稿件 › 文章 › 同行评审

摘要

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.

源语言	英语
页（从-至）	465-470
页数	6
期刊	Hangkong Dongli Xuebao/Journal of Aerospace Power
卷	22
期	3
出版状态	已出版 - 3月 2007
已对外发布	是

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title = "Effect of blade bowing and local modification on high-turning angle compressor stator performance",

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.",

keywords = "Aerospace propulsion system, Bowed blade, Compressor stator, High-turning angle, Local modification",

author = "Li, \{Shao Bin\} and Su, \{Jie Xian\} and Feng, \{Guo Tai\} and Wang, \{Zhong Qi\}",

year = "2007",

month = mar,

language = "英语",

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TY - JOUR

T1 - Effect of blade bowing and local modification on high-turning angle compressor stator performance

AU - Li, Shao Bin

AU - Su, Jie Xian

AU - Feng, Guo Tai

AU - Wang, Zhong Qi

PY - 2007/3

Y1 - 2007/3

N2 - 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.

AB - 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.

KW - Aerospace propulsion system

KW - Bowed blade

KW - Compressor stator

KW - High-turning angle

KW - Local modification

UR - https://www.scopus.com/pages/publications/34247330631

M3 - 文章

AN - SCOPUS:34247330631

SN - 1000-8055

VL - 22

SP - 465

EP - 470

JO - Hangkong Dongli Xuebao/Journal of Aerospace Power

JF - Hangkong Dongli Xuebao/Journal of Aerospace Power

IS - 3

ER -

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

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