变几何涡轮叶栅叶端小翼的气动性能

doi:10.7527/S1000-6893.2016.0139

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

变几何涡轮叶栅叶端小翼的气动性能

高杰, 郑群, 刘鹏飞, 魏明

哈尔滨工程大学动力与能源工程学院, 哈尔滨 150001

收稿日期:2015-12-17 修回日期:2016-04-29 出版日期:2016-12-15 发布日期:2016-05-04
通讯作者: 高杰,Tel.:0451-82518116,E-mail:gaojie_d@hrbeu.edu.cn E-mail:gaojie_d@hrbeu.edu.cn
作者简介:高杰,男,博士,副教授,硕士生导师。主要研究方向:叶轮机械气动热力学。Tel.:0451-82518116,E-mail:gaojie_d@hrbeu.edu.cn
基金资助:
国家自然科学基金（51406039）；黑龙江省自然科学基金（QC2016059）

Aerodynamic performance of a variable geometry turbine cascade using a vane-end winglet

GAO Jie, ZHENG Qun, LIU Pengfei, WEI Ming

College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China

Received:2015-12-17 Revised:2016-04-29 Online:2016-12-15 Published:2016-05-04
Supported by:
National Natural Science Foundation of China (51406039); Natural Science Foundation of Heilongjiang Province of China (QC2016059)

摘要/Abstract

摘要：

针对大子午扩张变几何涡轮在可调静叶转动时旋转轴端严重恶化端区流场的问题，提出在可调静叶的机匣端部应用小翼结构的方法以克服这一问题并减少叶端间隙泄漏流动。应用数值方法和标准k-ω两方程湍流模型，并结合低速风洞试验，首先研究了可调静叶栅小翼端部流场及损失分布，并考虑了可调静叶转动的影响，随后给出了叶端凹槽状小翼结构，并评估了其气动性能以及对间隙变化的敏感性。研究结果表明：在可调静叶栅中应用叶端小翼不但可以避免可调静叶转动时旋转轴端恶化端区流场，还降低了叶端间隙泄漏驱动力，从而使得可调静叶在所有转角下都具有较好的端区流动性能，并且叶端小翼结合凹槽结构可以进一步减少间隙泄漏，总体上可调静叶栅总压损失系数降低了8.9%。

关键词: 变几何涡轮, 小翼, 凹槽, 气动损失, 叶栅

Abstract:

In a high endwall-angle variable-geometry turbine, the rotating shaft end can lead to a serious deterioration of endwall flow fields when the variable vane rotates. A winglet is proposed to be applied to the variable vane casing-end to overcome this problem and then reduce the vane-end leakage flow. Combined with the low-speed wind tunnel test, numerical investigation is performed by solving Reynolds-averaged Navier-Stokes equations in conjunction with a standard k-ω two-equation turbulence model. The endwall flow fields and loss distribution of the variable vane with winglets are analyzed. The effects of vane turning are discussed. The vane-end cavity-winglet structure is then proposed, and the aerodynamic performance and its sensitivity to vane-end clearance height are evaluated. The results show that the variable vane with winglets can not only avoid the deterioration of endwall flow fields caused by vane turning, but also reduce the vane-end clearance leakage driving force, thus leading to improved endwall flow performance of variable vanes at all turning angles. Besides, the variable vane with cavity-winglets can further reduce the leakage flow, and the total pressure loss coefficient is reduced overall by 8.9% as compared to the baseline.

Key words: variable geometry turbine, winglet tip, cavity tip, aerodynamic loss, cascade

中图分类号:

V231.3

高杰, 郑群, 刘鹏飞, 魏明. 变几何涡轮叶栅叶端小翼的气动性能[J]. 航空学报, 2016, 37(12): 3615-3624.

GAO Jie, ZHENG Qun, LIU Pengfei, WEI Ming. Aerodynamic performance of a variable geometry turbine cascade using a vane-end winglet[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(12): 3615-3624.

参考文献

[1] KARSTENSEN K W, WIGGINS J O. A variable-geometry power turbine for marine gas turbines[J]. Journal of Turbomachinery, 1990, 112(2):165-174.
[2] MOFFITT T P, WHITNEY W J, SCHUM H J. Performance of a single-stage turbine as affected by variable stator area:AIAA-1969-0525[R]. Reston:AIAA, 1969.
[3] 宋力强, 王永泓. 变几何燃气涡轮损失模型的分析[J]. 燃气轮机技术, 2004, 17(2):35-40. SONG L Q, WANG Y H. Analysis on the loss model of variable geometry turbines[J]. Gas Turbine Technology, 2004, 17(2):35-40(in Chinese).
[4] QIU C, SONG H F, WANG Y H, et al. Performance estimation of variable geometry turbines[J]. Proceedings of the Institution of Mechanical Engineers, Part A:Journal of Power and Energy, 2009, 223(4):441-449.
[5] RAZINSKY E H, KUZIAK W R. Aerothermodynamic performance of a variable nozzle power turbine stage for an automotive gas turbine[J]. Journal of Engineering for Gas Turbines and Power, 1977, 99(4):587-592.
[6] 刘顺隆, 冯永明, 刘敏, 等. 船用燃气轮机动力涡轮可调导叶级的流场结构[J]. 热能动力工程, 2005, 20(2):120-124. LIU S L, FENG Y M, LIU M, et al. The flow field structure of the power-turbine variable-area nozzle stage of a marine gas turbine[J]. Journal of Engineering for Thermal Energy and Power, 2005, 20(2):120-124(in Chinese).
[7] 冯永明, 刘顺隆, 刘敏, 等. 船用燃气轮机变几何动力涡轮大攻角流动特性的三维数值模拟[J]. 热能动力工程, 2005, 20(5):459-463. FENG Y M, LIU S L, LIU M, et al. Three-dimensional numerical simulation of the flow characteristics at a large incidence of the variable-geometry power turbine of a marine gas turbine[J]. Journal of Engineering for Thermal Energy and Power, 2005, 20(5):459-463(in Chinese).
[8] YUE G Q, YIN S Q, ZHENG Q. Numerical simulation of flow fields of variable geometry turbine with spherical endwalls or nonuniform clearance:GT2009-59737[R]. New York:ASME, 2009.
[9] 陈升, 邱超, 宋华芬. 涡轮平面叶栅变几何试验研究[J]. 热能动力工程, 2011, 26(1):7-12. CHEN S, QIU C, SONG H F. Variable geometry experimental study of a turbine plane cascade[J]. Journal of Engineering for Thermal Energy and Power, 2011, 26(1):7-12(in Chinese).
[10] 马超, 臧述升, 黄名海. 变几何涡轮动叶栅流场的PIV实验研究[J]. 动力工程学报, 2014, 34(6):458-462. MA C, ZANG S S, HUANG M H. PIV flow field measurement for rotor blade cascade of a variable geometry turbine[J]. Journal of Chinese Society of Power Engineering, 2014, 34(6):458-462(in Chinese).
[11] 潘波, 陶海亮, 赵洪雷, 等. 可调导叶端壁间隙泄漏损失控制方法研究[J]. 工程热物理学报, 2013, 34(4):618-623. PAN B, TAO H L, ZHAO H L, et al. Investigation on the control strategy of variable guide vane endwall gap leakage loss[J]. Journal of Engineering Thermophysics, 2013, 34(4):618-623(in Chinese).
[12] GAO J, ZHENG Q, YUE G Q, et al. Variable geometry design of a high endwall angle power turbine for marine gas turbines:GT2015-43173[R]. New York:ASME, 2015.
[13] MISCHO B, BURDET A, ABHARI, et al. Influence of stator-rotor interaction on the aerothermal performance of recess blade tips:GT2008-50496[R]. New York:ASME, 2008.
[14] EL-GHANDOUR M, MORI K, NAKAMURA Y. Desensitization of tip clearance effects in axial flow turbines[J]. Journal of Fluid Science and Technology, 2010, 5(2):317-330.
[15] 高杰, 郑群. 叶顶凹槽形态对动叶气动性能的影响[J]. 航空学报, 2013, 34(2):218-226. GAO J, ZHENG Q. Effect of squealer tip geometry on rotor blade aerodynamic performance[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(2):218-226(in Chinese).
[16] COULL J D, ATKINS N R, HODSON H P. Winglets for improved aerothermal performance of high pressure turbines[J]. Journal of Turbomachinery, 2014, 136(9):091007-1-091007-11.
[17] LEE S W, KIM S U, KIM K H. Aerodynamic performance of winglets covering the tip gap inlet in a turbine cascade[J]. International Journal of Heat and Fluid Flow, 2012, 34:36-46.
[18] GAO J, ZHENG Q, ZHANG Z Y, et al. Aero-thermal performance improvements of unshrouded turbines through management of tip leakage and injection flows[J]. Energy, 2014, 69:648-660.
[19] NIU M S, ZANG S S. Experimental and numerical investigations of tip injection on tip clearance flow in an axial turbine cascade[J]. Experimental Thermal and Fluid Science, 2011, 35(6):1214-1222.
[20] 刘宇, 闫锦生, 卫嘉, 等. 燃气轮机动力涡轮可转导叶系统:ZL202348444U[P]. 2012-07-25. LIU Y, YAN J S, WEI J, et al. Variable-geometry vane system for gas turbine power turbines:China:ZL202348444U[P]. 2012-07-25(in Chinese).

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

变几何涡轮叶栅叶端小翼的气动性能

Aerodynamic performance of a variable geometry turbine cascade using a vane-end winglet

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	李国强, 宋奎辉, 覃晨, 赵光银, 吴霖鑫, 杨永东. 基于后缘小翼的翼型动态失速主动控制试验[J]. 航空学报, 2024, 45(3): 128699-128699.
[2]	王博, 吴艳辉, 黄令举, 王子胥. 基于端壁L形凹槽的扩压叶栅角区分离控制[J]. 航空学报, 2024, 45(10): 129206-129206.
[3]	孟博威, 马虎, 夏镇娟, 周长省. 旋转爆轰燃烧室与涡轮导向器集成特性数值研究[J]. 航空学报, 2024, 45(10): 129223-129223.
[4]	刘锬韬, 李瑞宇, 高丽敏, 赵磊. 基于数据同化的试验数据驱动的叶栅流场预测[J]. 航空学报, 2023, 44(14): 628201-628201.
[5]	朱寅鑫, 彭文强, 罗振兵, 康赢, 赵志杰, 程盼, 刘杰夫. 全叶高合成双射流对大折转角扩压叶栅的影响[J]. 航空学报, 2023, 44(12): 127734-127734.
[6]	王博, 吴艳辉. 扩压叶栅叶尖非定常流动的涡动力学机理[J]. 航空学报, 2020, 41(11): 123881-123881.
[7]	罗佳奇, 陈泽帅, 曾先. 考虑几何设计参数不确定性影响的涡轮叶栅稳健性气动设计优化[J]. 航空学报, 2020, 41(10): 123826-123826.
[8]	苟磊, 马玉娥, 杜永, 刘磊, 郭超, 李钢. 7050凹槽铝板激光冲击强化残余应力分布与疲劳寿命[J]. 航空学报, 2019, 40(12): 423096-423096.
[9]	唐海敏, 杜厦, 傅建明, 李欣益. 超声速细长飞行器前置小翼展开过程的非定常特性[J]. 航空学报, 2018, 39(5): 121701-121701.
[10]	马奕扬, 招启军. 后缘小翼对旋翼气动特性的控制机理及参数分析[J]. 航空学报, 2018, 39(5): 121671-121671.
[11]	高丽敏, 李永增, 张帅, 蔡明. 扩压叶栅剪敏液晶试验与图像处理[J]. 航空学报, 2017, 38(9): 520981-520981.
[12]	江雄, 邱名, 范召林. 喉道对压气机超声叶栅流态及性能的影响[J]. 航空学报, 2017, 38(3): 120308-120308.
[13]	马奕扬, 招启军, 赵国庆. 基于后缘小翼的旋翼翼型动态失速控制分析[J]. 航空学报, 2017, 38(3): 120312-120312.
[14]	王子楠, 耿少娟, 张宏武. 间隙变化对压气机静叶叶栅气动性能的影响[J]. 航空学报, 2016, 37(11): 3304-3316.
[15]	周迪, 王晓宇, 陈俊, 洪志亮, 孙晓峰. 转子叶栅非同步振荡发声特性研究[J]. 航空学报, 2015, 36(3): 737-748.