Study on the Turbine Blade Tip Leakage Flow Control Using Ring-Type Plasma Actuation

ZHOU Zuohong; HUANG Ming; YAN Xin; LI Zhigang; LI Jun

doi:10.7652/xjtuxb202406012

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Study on the Turbine Blade Tip Leakage Flow Control Using Ring-Type Plasma Actuation

更新时间：2025-07-28

- Study on the Turbine Blade Tip Leakage Flow Control Using Ring-Type Plasma Actuation
- Vol. 58, Issue 6, Pages: 128-138(2024)
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202406012
  CLC： TK474.7
- Published：2024
- 稿件说明：
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ZHOU Zuohong, HUANG Ming, YAN Xin, et al. Study on the Turbine Blade Tip Leakage Flow Control Using Ring-Type Plasma Actuation[J]. 2024, 58(6): 128-138.
DOI：

ZHOU Zuohong, HUANG Ming, YAN Xin, et al. Study on the Turbine Blade Tip Leakage Flow Control Using Ring-Type Plasma Actuation[J]. 2024, 58(6): 128-138. DOI： 10.7652/xjtuxb202406012.

摘要

为探究等离子体激励对叶顶泄漏流动的影响

基于非对称阻挡介质放电等离子体激励的数值模型

提出了环形电极的阻挡介质放电等离子体激励模型。将等离子体激励产生的体积力耦合至雷诺平均Navier-Stokes(RANS)方程组的动量方程中

数值研究了3种等离子体激励电压(9、13、17 kV)和3种激励频率(8、10、12 kHz)的透平叶顶泄漏流动特征。结果表明:环形电极等离子体激励显著改变了叶顶间隙的压力分布

在叶顶间隙内部和叶顶的两侧诱导形成大尺寸涡系结构

阻碍压力侧的主流进入叶顶间隙

有效抑制了动叶叶顶泄漏流动; 在激励频率一定时

随着激励电压的增加

叶顶泄漏流动引起的总压损失减弱

但过高的激励电压会造成额外的诱导涡损失; 激励电压保持不变

激励频率的增大对叶顶间隙的高压区域无明显影响

而叶顶两侧的诱导涡得到增强并挤压相邻的通道涡

叶栅通道120%轴向弦长处截面的总压损失进一步降低

13 kV激励电压、12 kHz激励频率工况具有最低的总压损失系数

相比无等离子体激励降低了16.12%。研究阐明了等离子体激励电压与激励频率对透平叶顶区域流场以及叶栅气动性能的影响规律。

Abstract

To explore the effect of plasma actuation on tip leakage flow

ring-type dielectric barrier discharge plasma model is proposed based on unsymmetrical electrodes dielectric barrier discharge plasma model in this paper. Blade tip leakage flow characteristics on a gas turbine is numerically studied with three plasma actuation voltage(9

17 kV)and three actuation frequency(8

12 kHz)by implementing plasma actuation forces into the momentum equations of Reynolds-averaged Navier-Stokes equations. The results show that the pressure distribution has been changed in the tip clearance by ring-type plasma actuation. The mainstream of pressure side is obstructed by strong vortex structure which is generated by plasma actuation in tip clearance and both sides of the tip. The tip leakage flow is suppressed effectively. When the actuation frequency is constant

the total pressure loss caused by the tip leakage flow decreases with the increase of the actuation voltage

but excessively high actuation voltage will cause additional induced vortex loss. When the actuation voltage remains unchanged

the increase of the actuation frequency has little effect on the high pressure region of the tip clearance and the induced vortices on both sides of the tip are enhanced and the adjacent passage vortices are squeezed. The area-average total pressure loss on 120% axial chord passage section is further reduced. The actuation voltage of 13 kV and actuation frequency of 12 kHz has the lowest total pressure loss coefficient on 120% axial chord passage section

which is 16.12% lower than no plasma actuation. The influence law of plasma actuation voltage and actuation frequency on the tip flow characteristics and aerodynamic performance is clarified in this paper.

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references

KEY N L, ARTS T. Comparison of turbine tip leakage flow for flat tip and squealer tip geometries at high-speed conditions [J]. Journal of Turbomachinery, 2006, 128(2): 213-220.

SAXENA V, EKKAD S V. Effect of squealer geometry on tip flow and heat transfer for a turbine blade in a low speed cascade [J]. Journal of Heat Transfer, 2004, 126(4): 546-553.

JUNG J S, KIM I, JOO J S, et al. Experimental study on aerodynamic loss and heat transfer for various squealer tips [J]. Journal of Turbomachinery, 2021, 143(5): 051002.

JUNG J S, KWON O, SON C. An investigation on aerodynamics loss mechanism of squealer tips of a high pressure turbine blade using URANS [C]//ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2016: V02DT44A027.

LOMAKIN N, GRANOVSKIY A, SHCHAULOV V, et al. Effect of various tip clearance squealer design on turbine stage efficiency [C]//ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. New York, NY, USA: ASME, 2015: V02AT38A017.

GARG A, VADLAMANI N R, SRINIVASAN B. Aerothermal performance of axially varying winglet-squealer blade tips [C]//ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2022: V10BT30A030.

LI Li, JIANG Dengyu, ZHOU Chao, et al. Near tip loss control with a winglet baffle cavity tip in a turbine cascade [J]. Journal of Engineering for Gas Turbines and Power, 2021, 143(10): 101007.

付云峰, 孟睿, 俞建阳, 等. 球底蜂窝组合叶顶对涡轮叶尖泄漏流动的控制 [J]. 工程热物理学报, 2018, 39(11): 2382-2388.

FU Yunfeng, MENG Rui, YU Jianyang, et al. Control of tip clearance flow of turbine cascade with spherical-bottom honeycomb tip [J]. Journal of Engineering Thermophysics, 2018, 39(11): 2382-2388.

杜昆, 李华容, 王力泉, 等. 多腔室凹槽对涡轮叶顶流动传热特性影响的数值研究 [J]. 推进技术, 2022, 43(10): 313-321.

DU Kun, LI Huarong, WANG Liquan, et al. Numerical investigations of multi-cavity tip effects on turbine blade tip flow and heat transfer characteristics [J]. Journal of Propulsion Technology, 2022, 43(10): 313-321.

许承天, 白波, 李志刚, 等. 涡轮动叶倾斜肩壁凹槽状叶顶气动性能研究 [J]. 西安交通大学学报, 2023, 57(5): 46-57.

XU Chengtian, BAI Bo, LI Zhigang, et al. Research on aerodynamic performance of gas turbine blade squealer tip with inclined rim [J]. Journal of Xi'an Jiaotong University, 2023, 57(5): 46-57.

ROTH J R, SHERMAN D M, WILKINSON S P.Boundary layer flow control with a one atmosphere uniform glow discharge surface plasma [C]//36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA, USA: AIAA, 1998: AIAA 1998-328.

ROTH J R, DAI Xin. Optimization of the aerodynamic plasma actuator as an electrohydrodynamic(EHD)electrical device [C]//44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA, USA: AIAA, 2006: AIAA 2006-1203.

ENLOE C L, FONT G I, MCLAUGHLIN T E, et al.Surface potential and longitudinal electric field measurements in the aerodynamic plasma actuator [J]. AIAA Journal, 2008, 46(11): 2730-2740.

TAKIZAWA Y, MATSUDA A, KIKUCHI K, et al.Optical observation of discharge plasma structure in DBD plasma actuator [C]//38th Plasmadynamics and Lasers Conference. Reston, VA, USA: AIAA, 2007: AIAA 2007-4376.

PORTER C O, MCLAUGHLIN T E, ENLOE C L, et al. Boundary layer control using a DBD plasma actuator [C]//45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA, USA: AIAA, 2007: AIAA 2007-786.

王斌, 李华星, 郝江南. 新型等离子体激励器对流动分离点控制 [J]. 实验流体力学, 2013, 27(2): 31-34.

WANG Bin, LI Huaxing, HAO Jiangnan. Flow separation point control by new plasma actuator [J]. Journal of Experiments in Fluid Mechanics, 2013, 27(2): 31-34.

ZHAO Jintao, ZHANG Hexiang, MENG Xuanshi, et al. Aerodynamic effects of a tube-type AC-DBD plasma actuator [C]//AIAA AVIATION 2023 Forum. Reston, VA, USA: AIAA, 2023: AIAA 2023-3747.

VAN NESS D K Ⅱ, CORKE T C, MORRIS S C. Stereo PIV of a turbine tip clearance flow with plasma actuation [C]//45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, VA, USA: AIAA, 2007: AIAA 2007-647.

MATSUNUMA T, SEGAWA T. Tip leakage flow reduction of a linear turbine cascade using string-type DBD plasma actuators [C]//ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. New York, NY, USA: ASME, 2018: V02BT41A026.

SHYY W, JAYARAMAN B, ANDERSSON A.Modeling of glow discharge-induced fluid dynamics [J]. Journal of Applied Physics, 2002, 92(11): 6434-6443.

SUZEN Y N, HUANG P G, JACOB J D, et al. Numerical simulations of plasma based flow control applications [C]//35th AIAA Fluid Dynamics Conference and Exhibit. Reston, VA, USA: AIAA, 2005: AIAA 2005-4633.

ARAM S, LEE Y T, SHAN Hua. Numerical analysis of SDBD-plasma based separation control on the blades of a rotating impeller [C]//ASME 2016 Fluids Engineering Division Summer Meeting collocated with the ASME 2016 Heat Transfer Summer Conference and the ASME 2016 14th International Conference on Nanochannels, Microchannels, and Minichannels. New York, NY, USA: ASME, 2016: V01AT02A002.

YU Jianyang, YU Jianing, CHEN Fu, et al. Numerical study of tip leakage flow control in turbine cascades using the DBD plasma model improved by the parameter identification method [J]. Aerospace Science and Technology, 2019, 84: 856-864.

WANG Zhao, YU Jianyang, CHEN Fu, et al. Effect of multiple DBD plasma actuators on the tip leakage flow structure and loss of a turbine cascade [J]. International Journal of Heat and Fluid Flow, 2019, 77: 377-387.

MATSUNUMA T, SEGAWA T. Vortex structure for reducing tip leakage flow of linear turbine cascade using dielectric barrier discharge plasma actuator [J]. Aerospace Science and Technology, 2023, 136: 108215.

张芝涛. 大气压窄间隙DBD等离子体源与应用基础研究 [D]. 大连: 大连海事大学, 2003: 50-54.

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