论文:2024,Vol:42,Issue(2):278-285
引用本文:
吴芳芳, 许卫疆, 刘存良, 史经垠, 余泽宇. 凹槽叶顶的气膜冷却特性[J]. 西北工业大学学报
WU Fangfang, XU Weijiang, LIU Cunliang, SHI Jingyin, YU Zeyu. Film cooling characteristics of squealer tip of a turbine blade[J]. Journal of Northwestern Polytechnical University

凹槽叶顶的气膜冷却特性
吴芳芳, 许卫疆, 刘存良, 史经垠, 余泽宇
西北工业大学 动力与能源学院, 陕西 西安 710072
摘要:
涡轮工作时,叶顶间隙内高速高温的间隙泄露流会直接冲刷动叶顶部,产生局部高温区域,因此控制间隙泄露流至关重要。基于压敏漆涂料(PSP)实验,研究了密度比、吹风比和间隙高度对凹槽叶顶气膜冷却特性的影响。研究结果表明:密度比增大,凹槽叶顶气膜冷却效果逐渐提高,尤其是大间隙下冷效提高较为明显,叶顶面平均冷效增加了35%;间隙高度和吹风比对叶顶表面冷效的作用不是单一的,小间隙条件下,叶顶表面气膜冷效随着吹风比增大而增大,大间隙条件下,吹风比的增加使得叶顶表面气膜冷效先减小后增加,同时小吹风比时,间隙高度增加提高了叶顶尾缘区域和孔周围的气膜冷效,叶顶面平均冷效提高了6.85%。
关键词:    凹槽叶顶    间隙高度    吹风比    密度比    气膜冷效   
Film cooling characteristics of squealer tip of a turbine blade
WU Fangfang, XU Weijiang, LIU Cunliang, SHI Jingyin, YU Zeyu
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
The high-speed and high-temperature gap leakage flow in the turbine blade tip clearance directly scours the tip of the rotor blade and generates a local high-temperature region, so the active and passive control of the gap leakage flow is very important. Based on the pressure sensitive paint (PSP) experiment, the effects of density ratio, blowing ratio, and clearance height on the film cooling characteristics of the squealer blade tip were studied. The results show that with the increase of the density ratio, the film-cooling effectiveness of the squealer blade tip gradually increases, especially in the large clearance height, and the average cooling effect of the blade tip is increased by 35%. The effect of tip clearance height and blowing ratio on the tip surface cooling effect is not single. Under the condition of small tip clearance, the tip surface film-cooling effectiveness increases with the increase of the blowing ratio. Under the condition of large tip clearance, the tip surface film-cooling effectiveness decreases first and then increases with the increase of blowing ratio. At the same time, when the blowing ratio is small, the increase in tip clearance height improves the tip trailing edge area and the film-cooling effectiveness around the holes, and the average cooling effect of the blade tip surface increases by 6.85 %.
Key words:    squealer tip of a turbine blade    clearance height    blowing ratio    density ratio    film-cooling effectiveness   
收稿日期: 2023-04-23     修回日期:
DOI: 10.1051/jnwpu/20244220278
基金项目: 国家自然科学基金(U2241268)与陕西省创新能力支撑计划(2023-CX-TD-19)资助
通讯作者: 许卫疆(1974—),副教授 e-mail:xuweijiang@nwpu.edu.cn     Email:xuweijiang@nwpu.edu.cn
作者简介: 吴芳芳(1999—),硕士研究生
相关功能
PDF(2977KB) Free
打印本文
把本文推荐给朋友
作者相关文章
吴芳芳  在本刊中的所有文章
许卫疆  在本刊中的所有文章
刘存良  在本刊中的所有文章
史经垠  在本刊中的所有文章
余泽宇  在本刊中的所有文章

参考文献:
[1] NEWTON P J, LOCK G D, KRISHNABABU S K, et al. Aero-thermal investigation of tip leakage flow in axial flow turbines: part Ⅲ-tip cooling[J]. Journal of Turbomachinery, 2009, 131(1): 011008
[2] YANG H, ACHARYA S, EKKAD S V, et al. Flow and heat transfer predictions for a flattip turbine blade[C]//Turbo Expo: Power for Land, Sea, and Air, 2002: 271-283
[3] AZAD G M, HAN J C, TENG S. Heat transfer and pressure distribution on a gas turbine blade tip[R]. ASME Paper 2000-GT-0194, 2000
[4] 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 Liming, LI Jun. Numerical investigation of turbine blade with grooved tip on the heat transfer performance[J]. Journal of Propulsion Technology, 2014, 35(5): 618-623 (in Chinese)
[5] CHYU M K, MOON H K, METZGER D E. Heat transfer in the tip region of grooved turbine blades[J]. Journal of Turbomachinery, 1989, 111: 131-138
[6] NAIK S, GEORGAKIS C, HOFER T, et al. Heat transfer and film cooling of blade tips and endwalls[J]. Journal of Turbomachinery, 2011, 134(4): 041004
[7] JEONG J, KIM W, KWAK J, et al. Heat transfer coefficient and film cooling effectiveness on the partial cavity tip of a gas turbine blade[J]. Journal of Turbomachinery, 2019, 141:071007
[8] 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 Turbomachinery, 2003, 125: 648-657
[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 HAN Chang, REN Jing, JIANG Hongde. Multi-parameter influence on film cooling at blade tip[J]. Journal of Engineering Thermophysics, 2012, 33(9): 1501-1504 (in Chinese)
[10] AHN J Y, MHETRAS S, HAN J C. Film cooling effectiveness on a gas turbine blade tip using pressure-sensitive paint[J]. ASME Journal of Heat Transfer, 2005, 127: 521-530
[11] 黄琰, 晏鑫, 何坤, 等. 气膜孔分布对凹槽叶顶传热和冷却性能的影响[J]. 西安交通大学学报, 2016, 50(5): 101-107 HUANG Yan, YAN Xin, HE Kun, et al. Effect of cooling-hole distributions on heat transfer and cooling effectiveness on turbine blade tip[J]. Journal of Xi'an Jiaotong University, 2016, 50(5): 101-107 (in Chinese)
[12] 王维杰, 卢少鹏, 马海腾, 等. 高压涡轮尾切凹槽叶尖冷却换热特性[J]. 航空动力学报, 2019, 34(10): 2131-2139 WANG Weijie, LU Shaopeng, MA Haiteng, et al. Cooling and heat transfer characteristics of high-pressure turbine blade with cutback squealer tip[J]. Journaln of Aerospace Power, 2019, 34(10): 2131-2139 (in Chinese)
[13] 杨蓓洁, 谭晓茗, 单勇, 等. 肋条结构对气膜冷却凹槽叶尖流动换热的影响[J]. 航空动力学报,2021, 36(7): 1462-1471 YANG Beijie, TAN Xiaoming, SHAN Yong, et al. Effects of rib structure on flow and heat transfer characteristics of film cooling rotor blade with squealer tip[J]. Journal of Aerospace Power, 2021, 36(7): 1462-1471 (in Chinese)
[14] 于金杏, 叶明亮, 晏鑫. 发动机工况下透平级凹槽叶顶冷却传热性能研究[J]. 西安交通大学学报, 2021, 55(7): 106-116 YU Jinxing, YE Mingliang, YAN Xin. Investigations on the heat transfer and film cooling effect at squealer tip of a turbine stage under engine conditions[J]. Journal of Xi'an Jiaotong University, 2021, 55(7):106-116 (in Chinese)
[15] 叶明亮,晏鑫,何坤.隔板位置对透平级凹槽叶顶传热和冷却性能的影响[J].西安交通大学学报,2018,52(5):116-124 YE Mingliang, YAN Xin, HE Kun. Effect of rib location on heat transfer and cooling effect of a squealer tip in turbine stage[J]. Journal of Xi'an Jiaotong University, 2018, 52(5): 116-124 (in Chinese)
[16] 郭嘉杰, 王新军, 鲍宇航. 椭圆孔及偏转角对凹槽叶顶气膜冷却流动换热特性的影响[J]. 西安交通大学学报, 2021, 55(1): 153-161 GUO Jiajie, WANG Xinjun, BAO Yuhang. Effects of oval-hole and inclination angle on the flow and heat transfer performance of the turbine blade with squealer tip[J]. Journal of Xi'an Jiaotong University, 2021, 55(1): 153-161 (in Chinese)
[17] 陈大为. 尾迹影响下的涡轮叶片表面气膜冷却有效度[D]. 西安:西北工业大学, 2020 Chen Dawei. Film cooling effectiveness of turbine blade surface under the influence of wake[D]. Xi'an: Northwestern Polytechnical University, 2020 (in Chinese)
[18] CHEN D W, ZHU H R, LIU C L, et al. Combined effects of unsteady wake and free-stream turbulence on turbine blade film cooling with laid-back fan-shaped holes using psp technique[J]. International Journal of Heat and Mass Transfer, 2019, 133: 382-392
[19] MCCLINTOCK F A. Describing uncertainties in single-sample experiments[J]. Mechanical Engineering, 1953, 75(1): 3-8
[20] 李佳. 燃气轮机透平气膜冷却机理的实验与理论研究[D]. 北京:清华大学, 2011 LI Jia. Experimental and theoretical research on gas turbine film cooling[D]. Beijing: Tsinghua University, 2011 (in Chinese)
[21] JOHNSON B E, HU H. Measurement uncertainties analysis in the determination of adiabatic film cooling effectiveness by using pressure sensitive paint(PSP) technique[C]//Fluids Engineering Division Summer Meeting, 2014
[22] NATSUI G, LITTLE Z, KAPAT J S, et al. A detailed uncertainty analysis of adiabatic film cooling effectiveness measurements using pressure-sensitive paint[J]. Journal of Turbomachinery, 2016, 138(8): 081007