叶顶压力侧小翼对跨声速涡轮级气动性能影响的数值研究

doi:10.13675/j.cnki.tjjs.200334

推进技术 ›› 2021, Vol. 42 ›› Issue (1): 94-102.DOI: 10.13675/j.cnki.tjjs.200334

叶顶压力侧小翼对跨声速涡轮级气动性能影响的数值研究

陈绍文，李伟航，王松涛

哈尔滨工业大学能源科学与工程学院，黑龙江哈尔滨 150000

出版日期:2021-01-15 发布日期:2021-01-15
基金资助:
国家自然科学基金（51776048；51436002）。

Numerical Study of Effects of Blade Tip Pressure-Side Winglet Cavity on Aerodynamic Performance of a Transonic Turbine Stage

School of Energy Science and Engineering，Harbin Institute of Technology，Harbin 150001，China

Online:2021-01-15 Published:2021-01-15

摘要/Abstract

摘要： 为了研究涡轮叶顶间隙泄漏流动有效控制的方式，本文将肋条小翼结构这种被动流动控制技术应用于涡轮级动叶叶顶中，以控制跨声速涡轮级叶顶间隙泄漏流动并改善其气动性能。通过数值模拟方法，分析了采用平顶方案、肋条方案和小翼肋条方案的涡轮级气动性能和叶顶间隙流动特性，研究了变间隙条件下小翼肋条方案对间隙泄漏流的控制效果，深入探讨小翼最大偏置距离和外倾角对小翼控制效果的影响。结果表明：所采用的肋条小翼结构能够有效地控制叶顶间隙泄漏流动并提高涡轮级的效率；在间隙高度为1mm时，涡轮级效率的提升达到0.51%，叶顶间隙泄漏流率下降48.6%；此外，随着小翼外倾角的增加，涡轮级效率逐渐增加并存在一个最佳的向外偏置距离为1.2mm。

关键词: 涡轮级;叶顶间隙;肋条小翼;涡轮效率;间隙泄漏流

Abstract: In order to study the effective control method of turbine tip clearance leakage flow， the present study applies the passive flow control technology of the rim winglet structure to the turbine stage rotor blade tip to control the transonic turbine stage tip clearance leakage flow and improve its aerodynamic performance. The aerodynamic performance and flow field around the blade tip were evaluated by numerical simulations under a flat-tip case， a groove tip case and a rim winglet case. The effects of different tip clearance heights of rim winglet cases on the tip leakage flow were investigated in this study. In addition， the influence of both the maximum off-set position and the inclination angle of the winglet were discussed in detail. The results supported that the tip leakage flow was well regulated and consequently the efficiency was enhanced with the application of the rim winglet. More concretely， the efficiency of the turbine stage was improved by 0.51% and the mass flow rate of the tip leakage flow was decreased by 48.6% under 1mm tip clearance. Moreover， the efficiency of the turbine stage increased with an enlarged winglet inclination angle. The optimal winglet off-set position turned out to be 1.2mm.

Key words: Gas turbine stage;Tip gap;Rim winglet;Turbine efficiency;Tip Leakage flow

陈绍文，李伟航，王松涛. 叶顶压力侧小翼对跨声速涡轮级气动性能影响的数值研究[J]. 推进技术, 2021, 42(1): 94-102.

CHEN Shao-wen, LI Wei-hang, WANG Song-tao. Numerical Study of Effects of Blade Tip Pressure-Side Winglet Cavity on Aerodynamic Performance of a Transonic Turbine Stage[J]. Journal of Propulsion Technology, 2021, 42(1): 94-102.

参考文献

[1] Denton J D. Loss Mechanisms in Turbomachines［J］. Journal of Turbomachinery， 1993， 115（4）： 621-656.
[2] Lee S W， Moon H S， Lee S E. Tip Gap Height Effects on Flow Structure and Heat Mass Transfer over Plane Tip of a High-Turning Turbine Rotor Blade［J］. International Journal of Heat and Fluid Flow， 2009， 30（2）： 198-210.
[3] Yamamoto A， Kaba K， Matsunuma T. Measurement and Visualization of Three Dimensional Flows in a Linear Turbine Cascade［R］. ASME 95-GT-341.
[4] Bindon J P. The Measurement and Formation of Tip Clearance Loss［J］. Journal of Turbomachinery， 1989， 111（3）： 257-263.
[5] 魏明，高杰，付维亮，等. 涡轮叶顶间隙自适应控制的研究［J］. 推进技术， 2017， 38（9）： 1921-1929.
[6] 周治华，陈绍文，兰云鹤，等. 叶顶不同位置喷气对涡轮间隙泄漏流动的影响［J］. 推进技术， 2016， 37（5）： 879-885.
[7] 牛茂升，臧述升. 机匣喷气位置对涡轮间隙流动控制的影响［J］. 推进技术， 2009， 30（5）： 594-598.
[8] Mischo B， Burdet A， Behr T， et al. Control of Rotor Tip Leakage Through Cooling Injection from Casing in a High-Work Turbine： Computational Investigation Using a Feature Based Jet Model［R］. ASME GT 2007-27669.
[9] Zhang Haideng， Wu Yun， Li Yinghong， et al. Control of Compressor Tip Leakage Flow Using Plasma Actuation［J］. Aerospace Science and Technology， 2019， 86： 244-255.
[10] Yu J， Yu J， Chen F， 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.
[11] 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.
[12] Lee S E， Lee S W， Kwak H S. Tip Leakage Aerodynamics over Stepped Squealer Tips in a Turbine Cascade［J］. Experimental Thermal and Fluid Science， 2011， 35（1）： 135 -145.
[13] 魏曼，钟兢军. 具有叶尖小翼的涡轮叶栅间隙流动的实验研究［J］. 推进技术， 2015， 36（12）： 1825-1832.
[14] Zhou Zhi-hua， Chen Shao-wen， Li Wei-hang， et al. Experiment Study of Aerodynamic Performance for the Suction Side and Pressure-Side Winglet-Cavity Tips in a Turbine Blade Cascade［J］. Experimental Thermal and Fluid Science， 2018， 90： 220-230.
[15] 高杰，郑群，李义进. 动叶顶部蜂窝面迷宫密封对涡轮级气动性能的影响［J］. 航空动力学报， 2012， 27（1）： 160-168.
[16] 付云峰，宋彦萍，陈聪，等. 机匣与叶顶蜂窝密封对涡轮叶栅顶部泄漏流动的影响［J］. 工程热物理学报， 2016， 37（5）： 963-968.
[17] Jiang S， Chen F， Yu J Y， et al. Treatment and Optimization of Casing and Blade Tip for Aerodynamic Control of Tip Leakage Flow in a Turbine Cascade［J］. Aerospace Science and Technology， 2019， 86： 704-713.
[18] 崔涛，汪帅，张伟，等. 开口双肋凹槽式涡轮叶顶间隙流动数值研究［J］. 推进技术， 2017， 38（4）： 815-827.
[19] Booth T C， Dodge P R， Hepworth H K. Rotor-Tip Leakage： Part I-Basic Methodology［J］. Journal of Engineering for Power， 1982， 104（1）： 154-161.
[20] Yaras M I， Sjolander S A. Measurements of the Effects of Winglets on Tip-Leakage Losses in a Linear Turbine Cascade［R］. ISABE 91-7011.
[21] Zhou C， Hodson H， Tibbott I， et al. Effects of Endwall Motion on the Aero-Thermal Performance of a Winglet Tip in a HP Turbine［J］. Journal of Turbomachinery， 2012， 134（6）.
[22] 周治华. 涡轮叶尖泄漏流动控制及传热特性研究［D］. 哈尔滨：哈尔滨工业大学， 2019.
[23] 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）.
[24] Erhard J. Design， Construction and Commissioning of a Transonic Test-Turbine Facility［D］. Steiermark： Graz University of Technology， 2000.

叶顶压力侧小翼对跨声速涡轮级气动性能影响的数值研究

Numerical Study of Effects of Blade Tip Pressure-Side Winglet Cavity on Aerodynamic Performance of a Transonic Turbine Stage

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