NACA翼型叶顶对低展弦比向心涡轮影响特性

doi:10.3901/JME.2020.18.172

机械工程学报 ›› 2020, Vol. 56 ›› Issue (18): 172-179.doi: 10.3901/JME.2020.18.172

• 可再生能源与工程热物理 • 上一篇下一篇

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NACA翼型叶顶对低展弦比向心涡轮影响特性

王星¹, 朱阳历¹, 李文^1,2, 左志涛¹, 陈海生^1,2,3

1. 中国科学院工程热物理研究所北京 100190;
2. 中国科学院大学北京 100049;
3. 国家能源大规模物理储能技术(毕节)研发中心毕节 551712

收稿日期:2019-11-05 修回日期:2020-05-27 出版日期:2020-09-20 发布日期:2020-11-17
通讯作者: 陈海生(通信作者),男,1977年出生,博士,研究员。主要研究方向为压缩空气储能系统、叶轮机械内部气动特性的试验与数值。E-mail:chen_hs@mail.etp.ac.cn
作者简介:王星,男,1986年出生,博士。主要研究方向为透平膨胀机的设计优化。E-mail:wangxing@iet.cn
基金资助:
国家重点研发计（2017YFB0903605）、国家自然科学基金（51806211）、中国科学院国际合作局国际伙伴计划（182211KYSB20170029）和贵州省发改委2017年第一批高新技术产业发展专项资金（黔发改高技[2017]951号）资助项目。

Effects of Blade Tip Profile Based on NACAAirfoil on Aerodynamic Performance of Low Aspect Ratio Radial-inflow Turbine

WANG Xing¹, ZHU Yangli¹, LI Wen^1,2, ZUO Zhitao¹, CHEN Haisheng^1,2,3

1. Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190;
2. University of Chinese Academy of Sciences, Beijing 100049;
3. National Energy Large Scale Physical Energy Storage Technologies R&D Center(Bijie), Bijie 551712

Received:2019-11-05 Revised:2020-05-27 Online:2020-09-20 Published:2020-11-17

摘要/Abstract

摘要： 针对压缩空气储能向心涡轮叶片展弦比低、叶顶间隙泄漏损失大的问题，将NACA0004翼型引入叶片顶部厚度分布以改善气动性能。采用ANSYS CFX软件对向心涡轮三维流场进行数值求解，分析0.5%~8%叶顶间隙范围内NACA0004翼型叶顶对间隙泄漏流结构和损失特征的影响。结果表明，NACA0004翼型叶顶对向心涡轮等熵效率的影响随叶顶间隙而变化。当叶顶间隙为0.5%时，NACA0004翼型叶顶使向心涡轮等熵效率降低0.3%；当叶顶间隙由1%增加至8%时，NACA0004翼型叶顶对等熵效率提升值由0.4%增加到1.9%。不同叶顶间隙下NACA0004翼型叶顶对间隙泄漏流损失特影响机理存在差异，当叶顶间隙为0.5%时，NACA0004翼型叶顶使泄漏流集中在叶片吸力面附近，并在叶轮出口区域产生更多泄漏流，增加叶片吸力面附近流动损失；当叶顶间隙为1%~8%时，NACA0004翼型叶顶能够降低叶片前缘和尾缘附近叶片压力面和吸力面压差，减小叶顶间隙泄漏流速度，降低与主流掺混强度，抑制流动损失。与此同时，叶轮强度也满足要求。研究成果可为同类向心涡轮叶顶间隙泄漏损失的控制提供参考。

关键词: 压缩空气储能, 向心涡轮, 间隙流动, 叶片型线, NACA0004翼型

Abstract: In order to reduce the serious tip leakage loss caused by low aspect ratio blade in radial turbine for compressed air energy storage (CAES) system, NACA0004 airfoil is adopted to form the thickness distribution near blade tip to improve the aerodynamic performance. Three-dimensional flow structure for the blade with NACA0004 airfoil tip is investigated numerically by using ANSYS CFX software. The effects of NACA0004 airfoil tip on the structure and loss characteristics of tip leakage flow are analyzed when tip clearance increased from 0.5% to 8%. The results show that the effect of blade with NACA0004 airfoil tip on isentropic efficiency of radial turbine varies with tip clearance. The isentropic efficiency of radial turbine is reduced by 0.3% when tip clearance is 0.5%, while the isentropic efficiency can be increased from 0.4% to 1.9% when tip clearance is varied from 1% to 8%. The tip leakage loss mechanism of the blade with NACA0004 airfoil tip is varied with the increase of tip clearance. When tip clearance is 0.5%, the leakage flow is concentrated near blade suction surface, and more leakage flow, which also increases the flow loss, is found near outlet region of rotor. However, when tip clearance is increased from 1% to 8%, the pressure difference between the blade pressure surface and suction surface near the leading edge and trailing edge of the blade is reduced, the leakage velocity and the mixing strength with the mainstream is decreased, and the flow loss is thus suppressed. When NACA0004 airfoil tip is adopted, the power output of the radial turbine has not been reduced, and the maximum deformation and equivalent stress of blade meet the requirements of structural size and material strength. The above research can provide a reference for reducing tip leakage loss of radial turbines with similar structure.

Key words: compressed air energy storage, radial inflow turbine, tip clearance flow, blade profile, NACA0004 airfoil

中图分类号:

TK05

王星, 朱阳历, 李文, 左志涛, 陈海生. NACA翼型叶顶对低展弦比向心涡轮影响特性[J]. 机械工程学报, 2020, 56(18): 172-179.

WANG Xing, ZHU Yangli, LI Wen, ZUO Zhitao, CHEN Haisheng. Effects of Blade Tip Profile Based on NACAAirfoil on Aerodynamic Performance of Low Aspect Ratio Radial-inflow Turbine[J]. Journal of Mechanical Engineering, 2020, 56(18): 172-179.

参考文献

[1] CHEN Haisheng,CONG T N,YANG Wei,et al. Progress in electrical energy storage system:A critical review[J]. Progress in Natural Sciences,2009,19(3):291-321.
[2] RODGERS C. Review of mixed flow and radial turbine options[C]//American Institute of Aeronautics and Astronautics. 26th Joint Propulsion Conference,July 16-18,1990,Orlando,Florida,Washington,D.C:AIAA,1990:AIAA 90-2414.
[3] GUO Qiang,ZHU Xiaocheng,DU Zhaohui. Experi-mental investigation of tip clearance flow for an axial flow fan rotor[J]. Chinese Journal of Mechanical Engine-ering,2006,19(3):376-382.
[4] SYED N D,MA Chaochen,YANG Ce,et al. Comparison of two methods to increase tip clearance and its effect on performance of turbocharger centrifugal compressor stage[J]. Chinese Journal of Mechanical Engineering,2007,19(3):60-65.
[5] LI Wei,QIAO Weiyang,SUN Dawei. Tip clearance flows in turbine cascade[J]. Chinese Journal of Aeron-autics,2008,3(21):193-199.
[6] 汪永阳,杜礼明,李成,等. 轴流式涡轮机动叶片的叶顶间隙对其气动性能影响[J]. 大连交通大学学报,2015,36(4):37-40. WANG Yongyang,DU Liming,LI Cheng,et al. Influence of tip clearance variation on aerodynamic performance of axial turbine[J]. Journal of Dalian Jiaotong University,2015,36(4):37-40.
[7] MOORE J,TILTON J S. Tip leakage flow in a linear turbine cascade[J]. ASME Journal of Turbomachinery,1988,110(1):18-26.
[8] HEYES F J G,HODSON H P. Measurement and prediction of the tip clearance flow in linear turbine cascade[J]. ASME Journal of Turbomachinery,1993,115(1):396-382.
[9] YAMAMOTO A. Endwall flow/loss mechanisms in a linear turbine cascade[J]. ASME Journal of Turbo-machinery,1988,110(1):18-26.
[10] ZHANG Q,HE L,RAWLINSON A. Effects of inlet turbulence and end-wall boundary layer on aerothermal performance of a transonic turbine blade tip[J]. ASME Journal of Engineering for Gas Turbines and Power,2014,136:052603-1-052603-7.
[11] MATSUNUMA T. Effects of reynolds number and freestream turbulence on turbine tip clearance flow[J]. ASME Journal of Turbomachinery,2006,128:166-177.
[12] HUANG A C,GREITZER E M,TAN C S,et al. Blade loading effects on axial turbine tip leakage vortex dynamics and loss[J]. ASME Journal of Turboma-chinery,2013,135:051012-1-051012-11.
[13] PALMER T R,TAN C,ZUNIGA H,et al. Quantifying loss mechanisms in turbine tip shroud cavity flows[J]. ASME Journal of Turbomachinery,2016,138:091006-1-091006-10.
[14] EI-GABRY L A. Numerical modeling of heat transfer and pressure losses for an uncooled gas turbine blade tip:Effect of tip clearance and tip geometry[J]. Journal of Thermal Science and Engineering Applications,2009,1:022005-1-022005-10.
[15] LAVAGNOLI S,MAESSCHALCK C D,PANIAGUA G. Analysis of the heat transfer driving parameters in tight rotor blade tip clearance[J]. ASME Journal of Heat Transfer,2016,138:011705-1-011705-10.
[16] PAPA M,GOLDSTEIN R J,GORI F. Effects of tip geometry and tip clearance on the mass/heat transfer from a large-scale gas turbine blade[J]. ASME Journal of Turbomachinery,2003,125:90-96.
[17] 曹丽华,张冬雪,胡鹏飞,等. 汽轮机动叶栅顶部泄漏流的数值分析[J]. 机械工程学报,2014,50(4):172-177. CAO Lihua,ZHANG Dongxue,HU Pengfei,et al. Numerical analysis of tip leakage flow in steam turbine rotor cascades[J]. Journal of Mechanical Engineering,2014,50(4):172-177.
[18] FUTAL S M,HOLESKI D E. Experimental results of varying the blade-shroud clearance in a 6.02 inch radial inflow turbine[R]. Washington,DC:NASA,1970.
[19] DAMBACH R,HODSON H P,HUMTSMAN I. An experimental study of tip clearance flow in a radial inflow turbine[J]. ASME Journal of Turbinemachinery,1999,121(4):644-650.
[20] 邓清华,牛久芳,丰镇平. 向心涡轮叶轮顶部间隙泄漏流动特性研究[J]. 中国科学E辑:技术科学,2009,39(4):618-625. DENG Qinghua,NIU Jiufang,FENG Zhenping. Study on tip leakage flow characteristics in a radial turbine[J]. Science in China(Series E),2009,39(4):618-625.
[21] ANSYS Inc. ANSYS academic research,release 14.5,theory manual[M/OL]. Canonsburg,PA:ANSYS,Inc.,2013.
[22] MENTER F R. Two equation eddy viscosity turbulence models for engineering applications[J]. AIAA Journal,1994,32(8):1598-1605.
[23] MENTER F R. Zonal two equation turbulence models for aerodynamic flows[R]. AIAA Paper 1993-2906.
[24] SIMONYI P S,ROELKE R J,STABE R G,et al. Aerodynamic evaluation of two compact radial inflow turbine rotors[R]. New York:National Aeronautics and Space Administration,NASA-TP-3514.
[25] 高杰,郑群,姜玉廷. 涡轮间隙流动结构及其损失产生机理研究[J]. 工程热物理学报,2013,34(10):1833-1837. GAO Jie,ZHENG Qun,JIANG Yuting. Investigation on tip clearance flow structure and its loss generation mechanism in turbine rotors[J]. Journal of Engineering Thermophysics,2013,34(10):1833-1837.

NACA翼型叶顶对低展弦比向心涡轮影响特性

Effects of Blade Tip Profile Based on NACAAirfoil on Aerodynamic Performance of Low Aspect Ratio Radial-inflow Turbine

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