Experiment of Reynolds number effects on subsonic compressor plane cascade

Wei WEI; Siyuan REN; Husheng MA; Xuechen LI; Youhai ZONG

doi:10.13224/j.cnki.jasp.20210252

Chinese

您当前的位置：

首页 >

文章列表页 >

Experiment of Reynolds number effects on subsonic compressor plane cascade

Turbomachinery | 更新时间：2025-04-07

- Experiment of Reynolds number effects on subsonic compressor plane cascade
- Journal of Aerospace Power Vol. 37, Issue 5, Pages: 1020-1029(2022)
- 作者机构：
  
  中国空气动力研究与发展中心空天技术研究所，四川绵阳 621000
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210252
  CLC：
- 稿件说明：
移动端阅览
Wei WEI, Siyuan REN, Husheng MA, et al. Experiment of Reynolds number effects on subsonic compressor plane cascade[J]. Journal of Aerospace Power, 2022, 37(5): 1020-1029.
DOI：

Wei WEI, Siyuan REN, Husheng MA, et al. Experiment of Reynolds number effects on subsonic compressor plane cascade[J]. Journal of Aerospace Power, 2022, 37(5): 1020-1029. DOI： 10.13224/j.cnki.jasp.20210252.

摘要

采用降低试验压力减小试验叶栅弦长雷诺数的方法，研究了UKG030.3压气机叶型叶片表面和尾迹区域气流随雷诺数、马赫数及攻角变化的流动特性，获得了表面等熵马赫数、总压损失系数等参数随雷诺数的变化规律。试验结果表明：弦长雷诺数减小到一定程度时，叶片吸力面峰值马赫数位置之后会逐渐呈现流动分离气泡产生、分离气泡扩大至分离气泡破碎的过程；长分离气泡出现以后尾迹宽度和叶型总压损失突然急剧增大，但损失突增所对应的临界雷诺数并不一致；叶型总压损失和弦长雷诺数经地面状态参数比值处理以后可以发现，总压损失比突增位置处于0.4倍弦长雷诺数比附近。

Abstract

The flow characteristics of the UKG030.3 compressor airfoil surface and the wake area were investigated in details with the varying Reynolds number，Mach number and the angle of incidences by means of decreasing the pressure of the test chamber.The surface isentropic Mach number and the total pressure loss coefficient of the airfoil with the changing Reynolds number were concluded.The experimental results showed that the whole developing process of the separation bubbles，which exhibited appearing，extending and bursting processes，came into sight behind the maximum Mach number location of the airfoil suction side with the test chamber pressure and Reynolds number decreasing.When the separation bubbles became long，the width of the wake area and the total pressure loss coefficient increased radically.However，the critical Reynolds number associated with the loss bursting was inconsistent under different conditions.When the total pressure loss coefficient and Reynolds number were divided by the corresponding coefficients of the atmosphere condition，it revealed that the location of the total pressure loss ratio bursting was near 0.4 times the ratio of the chord Reynolds number.

关键词

Keywords

references

肖洪 , 吴虎 , 廉筱纯 . 雷诺数对涡扇发动机性能及稳定性影响 [J]. 航空动力学报 , 2005 , 20 （ 3 ）: 394 ⁃ 398 .

XIAO Hong , WU Hu , LIAN Xiaochun . Reynolds number effects on performance and aerodynamic stabilities of the turbofan engines [J]. Journal of Aerospace Power , 2005 , 20 （ 3 ）: 394 ⁃ 398 . （in Chinese）

王进 , 骆广琦 , 陶增元 . 雷诺数对压气机特性及发动机稳定性影响的计算和分析 [J]. 航空动力学报 , 2002 , 18 （ 1 ）: 20 ⁃ 23 .

WANG Jin , LUO Guangqi , TAO Zengyuan . Effects of Reynolds number on compressor performance and engine stability [J]. Journal of Aerospace Power , 2002 , 18 （ 1 ）: 20 ⁃ 23 . （in Chinese）

WASSELL A B . Reynolds number effects in axial compressors [J]. Journal of Engineering for Power ， 1968 , 4 : 149 ⁃ 156 .

SCHÄFFLER A . Experimental and analytical investigation of the effects of Reynolds number and blade surface roughness on multistage axial flow compressors [J]. Journal of Engineering for Power , 1980 , 102 （ 1 ）: 5 ⁃ 12 .

JAMES P L . Flow separation prevention on a turbine blade in cascade at low Reynolds number [D]. Air Force Institute of Technology , 1999 .

CASTNER R , CHIAPPETTA S , WYZYKOWSKI J , et al . An engine research program focused on low pressure turbine aerodynamic performance [R]. ASME Paper GT⁃2002⁃30004 , 2002 .

HEINZ⁃ADOLF S , WOLFGANG S , BERNHARD K . Effects of Reynolds number and free⁃stream turbulence on boundary layer transition in a compressor cascade [J]. Journal of Turbomachinery , 2002 , 124 （ 1 ）: 1 ⁃ 9 .

TOYOTAKA S , HEINZ⁃ADOLF S . Aerodynamic characteristics of supersonic outlet guide vanes at low Reynolds number conditions [J]. Journal of Turbomachinery , 2007 , 129 （ 11 ）: 694 ⁃ 704 .

JOHN D C , HOWARD P H . Unsteady boundary⁃layer transition in low⁃pressure turbines [J]. Journal of Fluid Mechanics , 2011 , 681 : 370 ⁃ 410 .

MAYLE R E . The role of laminar⁃turbulent transition in gas turbine engines [J]. Journal of Turbomachinery , 1991 , 113 （ 11 ）: 509 ⁃ 536 .

雷志军 , 王明杰 , 朱俊强 . 低速压气机叶栅附面层分离的实验研究 [J]. 工程热物理学报 . 2008 , 29 （ 11 ）: 1839 ⁃ 1843 .

LEI Zhijun , WANG Mingjie , ZHU Junqiang . Experimental investigation on the suction surface boundary layer separation of a low⁃speed compressor cascade [J]. Journal of Engineering Thermophysics , 2008 , 29 （ 11 ）: 1839 ⁃ 1843 . （in Chinese）

王文涛 , 王子楠 , 张宏武 , 等 . 压气机静叶栅层流分离泡转捩与角区分离数值模拟与实验 [J]. 航空动力学报 , 2017 , 32 （ 9 ）: 2273 ⁃ 2282 .

WANG Wentao , WANG Zinan , ZHANG Hongwu , NIE Chaoque . Numerical simulation and experimental of laminar separation bubble transition and corner separation of compressor stator cascade [J]. Journal of Aerospace Power , 2017 , 32 （ 9 ）: 2273 ⁃ 2282 . （in Chinese）

凌代军 , 王晖 , 马昌友 . 低雷诺数亚声速扩压平面叶栅试验 [J]. 航空动力学报 , 2013 , 28 （ 1 ）: 171 ⁃ 179 .

LING Daijun , WANG Hui , MA Changyou . Subsonic compressor plane cascade experimental at low Reynolds number [J]. Journal of Aerospace Power , 2013 , 28 （ 1 ）: 171 ⁃ 179 . （in Chinese）

刘太秋 , 黄洪波 , 杜辉 . 压气机低雷诺数叶型设计技术研究 [J]. 航空发动机 , 2006 , 32 （ 2 ）: 26 ⁃ 32 .

LIU Taiqiu , HUANG Hongbo , DU Hui . Compressor airfoil design for low Reynolds number [J]. Aeroengine , 2006 , 32 （ 2 ）: 26 ⁃ 32 . （in Chinese）

刘波 , 侯为民 , 项效镕 . 高空低雷诺数二维抗分离叶型研究 [J]. 西北工业大学学报 , 2008 , 26 （ 6 ）: 703 ⁃ 706 .

LIU Bo , HOU Weimin , XIANG Xiaorong . Cascade profile optimization design for low Reynolds number and high altitude [J]. Journal of Northwestern Polytechnical University , 2008 , 26 （ 6 ）: 703 ⁃ 706 . （in Chinese）

李俊 , 刘波 , 杨小东 , 等 . 高空低雷诺数吸附式压气机叶型耦合优化设计 [J]. 航空动力学报 . 2016 , 31 （ 2 ）: 503 ⁃ 512 .

LI Jun , LIU Bo , YANG Xiaodong , et al . Coupling optimization design for aspirated compressor airfoil with low Reynolds number in high altitude [J]. Journal of Aerospace Power , 2016 , 31 （ 2 ）: 503 ⁃ 512 . （in Chinese）

范洁川 . 风洞试验手册 [M]. 北京：航空工业出版社 , 2002 .

国防科学技术工业委员会 . 高速风洞和低速风洞流场品质规范 : GJB 1179A-91 [S]. 北京：国防科工委军标出版发行部， 1992 . 1⁃15 .

刘永泉 , 刘太秋 , 季路成 . 航空发动机风扇/压气机技术发展的若干问题和思考 [J]. 航空学报 , 2015 , 36 （ 8 ）: 2563 ⁃ 2576 .

LIU Yongquan , LIU Taiqiu , JI Lucheng . Some problems and throughts in the development of aero⁃engine fan/compressor [J]. Acta Aeronautica et Astronutica Sinica , 2015 , 36 （ 8 ）: 2563 ⁃ 2576 . （in Chinese）

DUNKER R , RECHTER H , STARKEN H . Compressor stator and equivalent plane cascades with subsonic controlled diffusion blades [J]. Journal of Engineering for Gas Turbines and Power , 1984 , 106 （ 4 ）: 461 ⁃ 472 .

BRUNA D , CRAVERO C . Modeling the aerodynamic performance of modern axial flow compressor profiles:a correlative approach using current CFD technology [R]. AIAA⁃ 2007⁃0021 , 2007 .

STEINERT W , FUCHS R , STARKEN H . Inlet flow angle determination of transonic compressor cascades [J]. Journal of Turbomachinery , 1992 , 114 （ 7 ）: 487 ⁃ 493 .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

The Effects of Reynolds Number on the Stability of Axial compressors

Effects of Reynolds Number on Compressor Performance and Engine Stability

Application of neural network model in compressor through⁃flow analysis

Position rule of turboshaft engine surge based on bench test

Heat transfer and flow resistance characteristics of multi⁃row jet impingement cooling in double⁃wall cooling structure

Related Author

WANG Ying-feng

HU Jun

WANG Jin

LUO Guang-qi

TAO Zeng-yuan

Teng FEI

Lucheng JI

Ling ZHOU

Related Institution

Nanjing University of Aeronautics and Astronautics

Air Force Engineering University

School of Aerospace Engineering，Beijing Institute of Technology

Institute for Aero Engine，Tsinghua University

Aeronautical Foundation Institute，Naval Aviation University

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