PSP experiment of global surface pressure distribution on suction surface of compressor cascade with large curved angle

GAO Li-min; GAO Jie; WANG Huan; ZHOU Qiang; LIU Bo

Chinese

您当前的位置：

首页 >

文章列表页 >

PSP experiment of global surface pressure distribution on suction surface of compressor cascade with large curved angle

更新时间：2026-07-07

- PSP experiment of global surface pressure distribution on suction surface of compressor cascade with large curved angle
- Vol. 26, Issue 9, (2011)
- 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：2011
- 稿件说明：
移动端阅览
GAO Li-min, GAO Jie, WANG Huan, et al. PSP experiment of global surface pressure distribution on suction surface of compressor cascade with large curved angle[J]. 2011, 26(9).
DOI：

GAO Li-min, GAO Jie, WANG Huan, et al. PSP experiment of global surface pressure distribution on suction surface of compressor cascade with large curved angle[J]. 2011, 26(9). DOI：

摘要

基于自行组建的PSP(pressure sensitive paint)测量系统

采用中国科学院化学研究所PSP

实验测量了来流马赫数分别为0.4和0.5时大弯角扩压叶栅叶片吸力面全域压力分布

并与传统测压技术所得结果进行了比较.研究结果表明:①采用PSP技术测量可以获得叶片表面全域的连续压力分布

具有空间分布率高、定量测量的特点;②叶片中部PSP测量压力值与压力扫描阀结果吻合得非常好

但受到叶片吸力面曲率的影响

叶片前缘与尾缘附近的误差较大

最大误差为4.48%;③随着来流速度的提高

PSP与压力扫描阀之间的误差逐渐减小.

Abstract

Based on the home-made PSP (pressure sensitive paint)system and ICCAS's (Institute of Chemistry

Chinese Academy of Sciences) PSP

the pressure distribution on the compressor cascade surface was performed on a subsonic cascade wind-tunnel while the conventional pressure scanner was employed to validate the PSP measurement.Comparison between the PSP and the pressure scanner indicates: (1) Pressure distribution on the suction surface of with use of PSP is quantitative

continuous and global

and that with use of pressure scanner is discrete and limited.(2) Compared with the results of pressure scanner

there is a good agreement on the pressure valley and the maximum measuring error near the leading edge and trailing edge

which does not exceed to 4.48%.(3) The maximum measuring error is decreasing when Mach number of the inflow is increasing.

关键词

Keywords

references

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Effect of unilateral blade tip fillet structure on blade tip clearance flow of compressor cascade

Inverse design method of airfoil based on deep learning

Numerical simulation on cavitation flow field characteristics of squeeze film damper based on two-phase flow model

Prediction of hybrid airfoil leading edge pressure distribution based on deep learning

Experiment on seal characteristics of high ratational speed of stepped labyrinth seals

Related Author

ZHAO Lei

WANG Haoha

GAO Limin

LIU Tao

QIAN Weiqi

HE Lei

崔颖

李婷

Related Institution

中国航空发动机集团有限公司四川燃气涡轮研究院

大连海事大学船舶与海洋工程学院

西北工业大学航空学院

西北工业大学无人机特种技术重点实验室

南京航空航天大学能源与动力学院

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