Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing

Jianming LIU; Shengchun HAO; Hui WU; Zhan ZHAO; Lei ZHANG; Hao LI

doi:10.13224/j.cnki.jasp.20210271

Chinese

您当前的位置：

首页 >

文章列表页 >

Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing

Turbomachinery | 更新时间：2025-04-07

- Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing
- Journal of Aerospace Power Vol. 37, Issue 7, Pages: 1560-1568(2022)
- 作者机构：
  
  中国航空发动机集团有限公司沈阳发动机研究所，沈阳 110015
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210271
  CLC：
- 稿件说明：
移动端阅览
Jianming LIU, Shengchun HAO, Hui WU, et al. Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing[J]. Journal of Aerospace Power, 2022, 37(7): 1560-1568.
DOI：

Jianming LIU, Shengchun HAO, Hui WU, et al. Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing[J]. Journal of Aerospace Power, 2022, 37(7): 1560-1568. DOI： 10.13224/j.cnki.jasp.20210271.

摘要

为了考察中介机匣气动性能水平并验证设计方法，对中介机匣进行了气动性能试验，同时采用NUMECA Fine软件进行了相应的数值模拟。为了准确测量流过中介机匣内涵的气流流量，设计了一种流量测量装置并进行了精度校核，结果表明：测量精度的相对偏差小于1.5%。针对高进口马赫数时在进口平直段上两侧的壁面静压比中间区域小，以及某些涵道比未能调节到目标进口马赫数的情况，进行了相应的数值模拟并提出了解决方案。用单点总压管对内、外涵出口进行了扇面测量，得到了内涵的总性能曲线、总压恢复系数径向变化曲线及内、外涵总压恢复系数云图，并与计算结果进行对比，结果表明：内涵总性能曲线及内、外涵总压恢复系数云图的计算结果与试验结果吻合较好，在设计状态下，内、外涵出口测量截面的总压恢复系数分别为0.992 1、0.986，两数值均高于设计指标，中介机匣具有较好的气动性能。

Abstract

In order to investigate the aerodynamic performance of the intermediate casing and verify the design method，the aerodynamic performance of the intermediate casing was experimented.At the same time，corresponding numerical simulations were carried out by using NUMECA Fine software.To accurately measure the flow through the core of the intermediate casing，a flow measurement device was designed and the accuracy was checked.Results showed the relative deviation of the measurement accuracy was less than 1.5%.Considering the wall static pressure on both sides of the inlet straight section was smaller than in the center area at high inlet Mach number，and some bypass ratios failed to be adjusted to the target inlet Mach numbers，corresponding numerical simulations were carried out and the solutions were proposed.A single hole total pressure probe was used to measure the sector of the core and bypass outlet.The total performance curves and total pressure recovery coefficient radial change curves of the core，the total pressure recovery coefficient cloud images of the core and bypass were gained and compared with the calculated results.Results showed the core total performance curves，the core and bypass total pressure recovery coefficient cloud images of the calculated results were in good agreement with the experimental results.In the design state，the total pressure recovery coefficients of the core and bypass outlet measurement section were 0.9921 and 0.986，respectively，both were higher than the design indices，indicating the intermediate casing had good aerodynamic performance.

关键词

Keywords

references

DUEÑAS C O ， MILLER R J ， HODSON H P ， et al . Effect of length on compressor inter‑stage duct performance [R]. ASME Paper GT2007⁃27752 ， 2007 .

BAILEY D W ， BRITCHFORD K M ， CARROTTE J F ， et al . Performance assessment of an annular S‑shaped duct [R]. ASME Paper 95⁃GT⁃242 ， 1995 .

WALKER A D ， BARKER A G ， CARROTTE J F ， et al . Integrated OGV design for an aggressive S⁃shaped compressor transition duct [R]. ASME Paper GT2011⁃45627 ， 2011 .

NAYLOR E M J ， DUEÑAS C O ， MILLER R J ， et al . Optimisation of non‑axisymmetric endwalls in compressor S⁃shaped ducts [R]. ASME Paper GT2008⁃50448 ， 2008 .

KARAKASIS M K ， NAYLOR E M J ， MILLER R J ， et al . The effect of an upstream compressor on a non⁃axisymmetric S⁃duct [R]. ASME Paper GT2010⁃23404 ， 2010 .

WALKER A D ， BARKER A G ， CARROTTE J F . Numerical design and experimental evaluation of an aggressive S⁃shaped compressor transition duct with bleed [R]. ASME Paper GT2011⁃45628 ， 2011 .

WALLIN F ， JOHANSSON P ， ROBERTSSON T . Design of integrated turning vanes for a compressor transition duct [R]. International Symposium on Air Breathing Engines，ISABE⁃2011⁃1213 ， 2011 .

WALLIN F ， BERGSTEDT R ， WALKER A D ， et al . Aero⁃design and validation of turning struts for an intermediate compressor duct [R]. International Symposium on Air Breathing Engines，ISABE⁃2015⁃20089 ， 2015 .

WALKER A D ， BARKER A G ， MARIAH I ， et al . An aggressive S‑shaped compressor transition duct with swirling flow and aerodynamic lifting struts [R]. ASME Paper GT2014⁃25844 ， 2014 .

邓小明，高丽敏，冯旭栋，等 . 压气机中介机匣三点NURBS曲线参数化方法 [J]. 工程热物理学报， 2014 , 35 （ 7 ）: 1330 ⁃ 1333 .

DENG Xiaoming ， GAO Limin ， FENG Xudong ， et al . Three⁃points NURBS parameterized method for compressor intermediate duct [J]. Journal of Engineering Thermophysics ， 2014 ， 35 （ 7 ）: 1330 ⁃ 1333 . （in Chinese）

高丽敏，冯旭栋，陈璇，等 . 关于压气机过渡段设计方法的探讨 [J]. 航空学报， 2013 ， 34 （ 5 ）: 1057 ⁃ 1063 .

GAO Limin ， FENG Xudong ， CHEN Xuan ， et al . Exploration about compressor intermediate duct design [J]. Acta Aeronautica et Astronautica Sinica ， 2013 ， 34 （ 5 ）: 1057 ⁃ 1063 . （in Chinese）

阙晓斌，侯安平，周盛 . 基于壁面压力梯度控制的压气机S形过渡段设计 [J]. 航空学报， 2010 ， 31 （ 3 ）: 459 ⁃ 465 .

QUE Xiaobin ， HOU Anping ， ZHOU Sheng . S⁃shaped compressor transition duct design based on wall pressure gradient control [J]. Acta Aeronautica et Astronautica Sinica , 2010 ， 31 （ 3 ）: 459 ⁃ 465 . （in Chinese）

阙晓斌，侯安平，周盛 . 轴流压缩系统带支板过渡段的轴对称等效方法 [J]. 航空学报， 2010 ， 31 （ 9 ）: 1715 ⁃ 1722 .

QUE Xiaobin ， HOU Anping ， ZHOU Sheng . Axisymmetric equivalent of S⁃shaped transition duct with struts in axial compression systems [J]. Acta Aeronautica et Astronautica Sinica ， 2010 ， 31 （ 9 ）: 1715 ⁃ 1722 . （in Chinese）

JIN Donghai ， LIU Xiwu ， ZHAO Weiguang ， et al . Optimization of endwall contouring in axial compressor S⁃shaped ducts [J]. Chinese Journal of Aeronautics ， 2015 ， 28 （ 4 ）: 1076 ⁃ 1086 .

向宏辉，张良，陆庆飞，等 . 进气条件对压气机中介机匣流场影响的试验研究 [J]. 燃气涡轮试验与研究 , 2011 ， 24 （ 4 ）: 15 ⁃ 19 .

XIANG Honghui ， ZHANG Liang ， LU Qingfei ， et al . Experimental investigation of inlet conditions' effect on compressor intermediate casing flow field [J]. Gas Turbine Experiment and Research ， 2011 ， 24 （ 4 ）: 15 ⁃ 19 . （in Chinese）

庄皓琬，李斌，滕金芳，等 . 进气畸变对大涵道比发动机压气机中介机匣性能的影响 [J]. 科学技术与工程 , 2020 ， 20 （ 22 ）: 9229 ⁃ 9233 .

ZHUANG Haowan ， LI Bin ， TENG Jinfang ， et al . Effect of inlet distortion on performance of the compressor inter⁃mediate casing of a high bypass ratio aero engine [J]. Science Technology and Engineering ， 2020 ， 20 （ 22 ）: 9229 ⁃ 9233 . （in Chinese）

王迎国，吴晓东，向宏辉，等 . 外涵调节对中介机匣性能影响的试验研究 [J]. 燃气涡轮试验与研究， 2019 , 32 （ 1 ）: 38 ⁃ 42 .

WANG Yingguo ， WU Xiaodong ， XIANG Honghui ， et al . Experimental study on performance impact of bypass regulation on intermediate casing [J]. Gas Turbine Experiment and Research ， 2019 ， 32 （ 1 ）: 38 ⁃ 42 . （in Chinese）

魏崇，向宏辉，刘志刚，等 . 探针测量布局对中介机匣流场影响的试验研究 [J]. 燃气涡轮试验与研究， 2020 , 33 （ 5 ）： 44 ⁃ 47，62 .

WEI Chong ， XIANG Honghui ， LIU Zhigang ， et al . Experimental investigation for effect of probe measurement position on flowfield of intermediate duct [J]. Gas Turbine Experiment and Research ， 2020 ， 33 （ 5 ）: 44 ⁃ 47，62 . （in Chinese）

李斌，吴亚东，滕金芳，等 . 压气机中介机匣几何结构的试验验证 [J]. 航空动力学报， 2013 ， 28 （ 10 ）: 2326 ⁃ 2331 .

LI Bin ， WU Yadong ， TENG Jinfang ， et al . Experimental validation of geometry of compressor intermediate casing [J]. Journal of Aerospace Power ， 2013 ， 28 （ 10 ）: 2326 ⁃ 2331 . （in Chinese）

韦禹，羌晓青，董威，等 . 中介机匣可调放气活门数值研究 [J]. 科学技术与工程， 2020 ， 20 （ 31 ）: 13061 ⁃ 13066 .

WEI Yu ， QIANG Xiaoqing ， DONG Wei ， et al . Numerical study of variable bleed valve of intermediate casing duct [J]. Science Technology and Engineering ， 2020 ， 20 （ 31 ）: 13061 ⁃ 13066 . （in Chinese）

辛亚楠，李家军，韩阳，等 . 大径向落差长度比中介机匣气动特性研究 [J]. 推进技术， 2017 ， 38 （ 4 ）: 808 ⁃ 814 .

XIN Yanan ， LI Jiajun ， HAN Yang ， et al . Numerical study on aerodynamic characteristics of a large radius change to length ratio intermediate Duct [J]. Journal of Propulsion Technology ， 2017 ， 38 （ 4 ）: 808 ⁃ 814 . （in Chinese）

张耀光，杨琳 . 压气机紧凑S形过渡段内周向弯静子性能数值计算 [J]. 航空发动机， 2020 ， 46 （ 3 ）: 7 ⁃ 13 .

ZHANG Yaoguang ， YANG Lin . Numerical calculation of circumferential curved stator performance in aggressive S⁃shaped transition duct of compressor [J]. Aeroengine ， 2020 ， 46 （ 3 ）: 7 ⁃ 13 . （in Chinese）

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Effects of porous media on rod⁃airfoil interaction noise

Effect of tip injection on aerodynamic performance of squealer tip

Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions

Numerical investigation on adaptive flow⁃control of supersonic inlet based on air⁃bleeding multi⁃slots

Impacts of non⁃axisymmetric stagger angle on performance of compressor rotor blade

Related Author

Chenghao YANG

Heying FENG

Yehui PENG

Nüzi BAO

Liming XUAN

Zhengping ZOU

Qiang ZHAO

Lin HUANG

Related Institution

Hunan Provincial Key Laboratory of Health Maintenance for Mechanical Equipment， Hunan University of Science and Technology

School of Mathematics and Computational Science，Hunan University of Science and Technology

National Key Laboratory of Science and Technology on Aero⁃Engine Aero⁃thermodynamics，School of Energy and Power Engineering，Beihang University

Research Institute of Aero⁃Engine，Beihang University

Laboratory of Light⁃Duty Gas⁃Turbine，Institute of Engineering Thermophysics，Chinese Academy of Sciences

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