凹槽状叶顶气膜孔优化设计与知识挖掘

推进技术 ›› 2019, Vol. 40 ›› Issue (2): 276-284.

凹槽状叶顶气膜孔优化设计与知识挖掘

李琛玺,郭振东,宋立明,李军,丰镇平

西安交通大学能源与动力工程学院，陕西西安 710049,西安交通大学能源与动力工程学院，陕西西安 710049,西安交通大学能源与动力工程学院，陕西西安 710049,西安交通大学能源与动力工程学院，陕西西安 710049,西安交通大学能源与动力工程学院，陕西西安 710049

发布日期:2021-08-15
作者简介:李琛玺，博士生，研究领域为叶轮机械气动热力学与优化设计。E-mail: lichenxi@stu.xjtu.edu.cn 通讯作者:宋立明，博士，教授，研究领域为叶轮机械气动优化设计。

Film-Cooling Holes Design Optimization and Knowledge Mining of a Squealer Tip

School of Energy and Power Engineering，Xi’an Jiaotong Universtiy，Xi’an 710049，China,School of Energy and Power Engineering，Xi’an Jiaotong Universtiy，Xi’an 710049，China,School of Energy and Power Engineering，Xi’an Jiaotong Universtiy，Xi’an 710049，China,School of Energy and Power Engineering，Xi’an Jiaotong Universtiy，Xi’an 710049，China and School of Energy and Power Engineering，Xi’an Jiaotong Universtiy，Xi’an 710049，China

Published:2021-08-15

摘要/Abstract

摘要： 为改善叶顶气膜冷却效果，基于全局优化算法，引入数据挖掘技术，建立了凹槽状叶顶气膜孔优化设计与数据挖掘框架。以叶顶的平均气膜有效度为优化目标和以冷气流量为约束条件，对GE_E3动叶叶顶的气膜孔进行优化设计。优化后叶顶的平均气膜有效度提高了3.7倍。流动结构与冷却分析表明，优化后气膜孔的分布得到了改善，孔径的改变使得冷气流量分布更为合理，从而增加了叶顶前缘的气膜覆盖面积，增强了主流对冷气的压制效应，喷射冷气更加贴近壁面，叶顶的平均气膜有效度显著提高。同时通过对设计空间进行知识挖掘，探究设计空间信息，结果表明叶顶前缘气膜孔对叶顶气膜冷却影响显著，增大叶顶前缘气膜孔孔径，将前缘气膜孔向前缘移动，减小中部气膜孔间距，可有效改善叶顶气膜冷却效果。

关键词: 凹槽状叶顶；气膜冷却；全局优化算法；知识挖掘

Abstract: In order to improve the film-cooling effectiveness of squealer tip，by integrating data mining techniques and effective global optimization (EGO) algorithm，an optimization method for film-cooling holes on squealer tip is proposed. Using this method，the design optimization is carried out for maximizing average film-cooling effectiveness of the squealer tip of GE_E3 rotor tip，while the constraint is coolant mass flow rate. After optimization，the film-cooling effectiveness of tip increased by 3.7 times. According to flow structure and cooling flow analysis，for optimal design，the distribution of film cooling holes is improved. And the optimal design changes the dimeter of film-cooling holes to adjust the mass flow of holes of coolant air and increase flow area of coolant air in the squealer cavity. In addition，the mainstream suppression effect enhances，so that the coolant air from film cooling holes is closer to squealer tip. Therefore，the cooling effectiveness of squealer tip increases significantly. Meanwhile，the knowledge discovery of design space is carried out，the effects of design variables near leading edge on film-cooling effectiveness of squealer tip are important. Increasing the dimeter of film cooling holes and reducing the distance between film cooling holes near leading edge should improve film cooling in squealer tip.

Key words: Squealer tip；Film cooling；Effective global optimization；Knowledge mining

李琛玺,郭振东,宋立明,李军,丰镇平. 凹槽状叶顶气膜孔优化设计与知识挖掘[J]. 推进技术, 2019, 40(2): 276-284.

LI Chen-xi,GUO Zhen-dong,SONG Li-ming,LI Jun,FENG Zhen-ping. Film-Cooling Holes Design Optimization and Knowledge Mining of a Squealer Tip[J]. Journal of Propulsion Technology, 2019, 40(2): 276-284.

参考文献

[1] Metzger D E, Bunker R S, Chyu M K. Cavity Heat Transfer on a Transverse Grooved Wall in a Narrow Flow Channel[J]. Journal of Heat Transfer, 1989, 111(1):73-79.
[2] Bunker R S. A Review of Turbine Blade Tip Heat Transfer[J]. Annals of the New York Academy of Sciences, 2001, 934(1).
[3] Azad G S, Han J C, Teng S, et al. Heat Transfer and Pressure Distributions on a Gas Turbine Blade Tip[J]. Journal of Turbomachinery, 2000, 122(4): 717-724.
[4] Kwak J S, Han J C. Heat Transfer Coefficients and Film Cooling Effectiveness on the Squealer Tip of a Gas Turbine Blade[J]. Journal of Heat Transfer, 2002, 125(3):494.
[5] Yang H, Acharya S, Ekkad S V, et al. Numerical Simulation of Flow and Heat Transfer Past a Turbine Blade with a Squealer-Tip[R]. ASME GT 2002-30193.
[6] Ahn J, Mhetras S, Han J C, et al. Film-Cooling Effectiveness on a Gas Turbine Blade Tip Using Pressure-Sensitive Paint[J]. Journal of Heat Transfer, 2005, 127(5):521-530.
[7] Yang H, Chen H C, Han J C. Film-Cooling Prediction on Turbine Blade Tip with Various Film Hole Configurations[J]. Journal of Thermophysics & Heat Transfer, 2015, 20(3): 558-568.
[8] 李广超, 朱慧人, 白江涛, 等. 气膜孔布局对前缘气膜冷却效率影响的实验[J]. 推进技术, 2008, 29(2):153-157. (LI Guang-chao, ZHU Hui-ren, BAI Jiang-tao, et al. Experimental Investigation of Film Cooling Effectiveness on Leading Edge with Various Geometries[J]. Journal of Propulsion Technology, 2008, 29(2):153-157.)
[9] 韩昌, 任静, 蒋洪德. 多参数对叶顶气膜冷却的影响[J]. 工程热物理学报, 2012, 33(9): 1501-1504.
[10] 王文三, 唐菲, 赵庆军, 等. 涡轮叶顶冷却布置对叶顶传热冷却性能的影响[J]. 工程热物理学报, 2012, 33(3): 393-396.
[11] 杜昆, 宋立明, 李军. 凹槽状叶顶涡轮叶片传热特性的数值研究[J]. 推进技术, 2014, 35(5): 618-623. (DU Kun, SONG Li-ming, LI Jun. Numerical Investigations on Heat Transfer Characteristics of Turbine Blade with Squealer Tip[J]. Journal of Propulsion Technology, 2014, 35(5): 618-623.)
[12] Dennis B H, Yegorovegorov I, Sobieczky H, et al. Parallel Thermoelasticity Optimization of 3-D Serpentine Cooling Passages in Turbine Blades[J]. International Journal of Turbo & Jet Engines, 2004, 21(1): 57-68.
[13] Talya S, Chattopadhyay A, Rajadas J. Multidisciplinary Analysis and Design Optimization Procedure for Cooled Gas Turbine Blades[R]. AIAA 2000-4877.
[14] Kang Y S, Rhee D H, Kim C T, et al. Aerodynamic Optimization of Axial Turbine Tip Cavity with Approximation Model[R]. ASME TBTS 2013-2079.
[15] 岂兴明, 朴英. 涡轮叶顶间隙形态的优化[J]. 西安通大学学报吉林大学学报(工学版), 2009, 39(4):874-879.
[16] 卢少鹏, 迟重然, 温风波, 等. 考虑气膜冷却的涡轮静叶多目标优化[J]. 工程热物理学报, 2013, 34(6):1036-1041.
[17] Chiba K, Oyama A, Obayashi S, et al. Multidisciplinary Design Optimization and Data Mining for Transonic Regional-Jet Wing[J]. Journal of Aircraft, 2007, 44(4): 1100–1112.
[18] Oyama A, Nonomura T, Fujii K. Data Mining of Pareto-Optimal Transonic Airfoil Shapes Using Proper Orthogonal Decomposition[R]. AIAA 2009-4000.
[19] Kipouros T, Mleczko M, Savill A M. Use of Parallel Coordinates for Post-Analyses of Multi-Objective Aerodynamic Design Optimisation in Turbomachinery[R]. AIAA 2008-2138.
[20] Koziel S, Tesfahunegn Y A, Amrit A, et al. Rapid Multi-Objective Aerodynamic Design Using Co-Kriging and Space Mapping[R]. AIAA 2016-0418.
[21] Donald R. Jones M S, William J Welch. Efficient Global Optimization of Expensive Black-Box Functions[J]. Journal of Global Optimization, 1998, 13: 455–492.
[22] Chenxi LI, Zhengdong GUO, Liming SONG, et al. Design Optimization of a 3D Parameterized Vane Cascade with Non-Axisymmetric Endwall Based on a Modified EGO Algorithm and Data Mining Techniques[R]. ASME GT 2017-63738.
[23] Guo Z, Song L, Zhou Z, et al. Multi-Objective Aerodynamic Optimization Design and Data Mining of a High Pressure Ratio Centrifugal Impeller [J]. Journal of Engineering for Gas Turbines & Power, 2015, 137(9).
[24] Li E, Wang H. Bi-Direction Multi-Surrogate Assisted Global Optimization[J]. Engineering Computations, 2016, 33(3): 646-666.(编辑:田佳莹)　　　　　　　　　　　　　　收稿日期:2017-12-18；修订日期:2018-02-23。作者简介:李琛玺,博士生,研究领域为叶轮机械气动热力学与优化设计。E-mail: lichenxi@stu.xjtu.edu.cn通讯作者:宋立明,博士,教授,研究领域为叶轮机械气动优化设计。E-mail: songlm@mail.xjtu.edu.cn