燃气轮机旋转状态下的动叶气膜冷却效果数值模拟研究
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摘要
采用数值模拟的方法研究了旋转对叶片气膜冷却效果的影响,详细对比了不同吹风比下叶片在旋转和静止状态下的气膜冷却特性,并用平均气膜冷却效率和不均匀系数评估了气膜冷却效果。结果表明:在叶片压力面,叶片的旋转使得射流气体从气膜孔流出后法向动量增大,与主流掺混作用加强,从而使得叶片压力面气膜冷却效率值低于静止状态;在叶片吸力面,叶片旋转使得冷却气体流出后法向动量减小,能够更好地贴附在叶片表面向下游流动,使得旋转时叶片吸力面气膜冷却效率要优于静止状态,并且叶片后沿的平均气膜冷却效率较静止状态有显著提高;旋转状态下叶片表面的不均匀度系数要略大于静止时叶片表面不均匀度系数。
In this paper, the film cooling effectiveness of rotating gas turbine blade is investigated through numerical simulations.The cooling characteristics under different blowing ratios in rotating state as well as static state are compared in details. The average film cooling efficiency and cooling non-uniformity coefficient are used to evaluate the film cooling effect. The results show that on the pressure surface of the blade, due to the blade rotation the momentum of the jet cooling air in the normal direction will increase after the airflow passes through the film hole and then intensify with the mix of mainstream, such that the film cooling efficiency on pressure surface is lower than that of the static state. While on suction surface the rotation will result in the decrease of the normal momentum of jet air through the film hole, which will make it remain well attached to the surface and move downstream. Therefore the film cooling efficiency on suction surface is higher than that of the static state, and the average film cooling efficiency on the trailing edge is significantly boosted in comparison with the static state. The cooling non-uniformity coefficient on rotating blade is slightly greater than that of the static blade.
In this paper, the film cooling effectiveness of rotating gas turbine blade is investigated through numerical simulations.The cooling characteristics under different blowing ratios in rotating state as well as static state are compared in details. The average film cooling efficiency and cooling non-uniformity coefficient are used to evaluate the film cooling effect. The results show that on the pressure surface of the blade, due to the blade rotation the momentum of the jet cooling air in the normal direction will increase after the airflow passes through the film hole and then intensify with the mix of mainstream, such that the film cooling efficiency on pressure surface is lower than that of the static state. While on suction surface the rotation will result in the decrease of the normal momentum of jet air through the film hole, which will make it remain well attached to the surface and move downstream. Therefore the film cooling efficiency on suction surface is higher than that of the static state, and the average film cooling efficiency on the trailing edge is significantly boosted in comparison with the static state. The cooling non-uniformity coefficient on rotating blade is slightly greater than that of the static blade.
引文
[1]刘钊,杨星,丰镇平.燃气轮机透平叶片传热和冷却研究:气膜冷却[J].热力透平,2014, 43(1):1-9.LIU Zhao, YANG Xing, FENG Zhenping. Study on heat transfer and cooling in gas turbine blade:Film cooling[J]. Thermal Turbine, 2014,43(1):1-9.
[2] ITO S, GOLDSTEIN R J, ECKERT E R G. Film cooling of a gas turbine blade[J]. ASME Journal of Engineering for Power, 1978, 100:476-481.
[3] SMITH S H, MUNGAL M G. Mixing, structure and scaling of the jet in crossflow[J]. Journal of Fluid Mechanics, 1998, 357(1):83-122.
[4]高媛,葛利顺,王宏光,等.振动平板单孔气膜冷却实验研究[J].动力工程学报,2016, 36(9):704-710.GAO Yuan, GE Lishun, WANG Hongguang, et al. Experimental study on single-hole film cooling effectiveness over vibrating plates[J]. Journal of Chinese Society of Power Engineering, 2016,36(9):704-710.
[5] AL-ZURFI N, TURAN A, NASSER A. Numerical investigation of rotation effects on anti-vortex film-cooling holes[J]. Flow,Turbulence and Combustion,2016, 96(1):133-162.
[6]常艳,杨卫华,张靖周.突片形状对气膜冷却效率的影响[J].南京航空航天大学学报,2016, 48(3):317-325.CHANG Yan, YANG Weihua, ZHANG Jingzhou. Effects of tab shapes on film cooling effectiveness[J]. Journal of Nanjing University of Aeronautics&Astronautics, 2016, 48(3):317-325.
[7]唐学智,李录平,黄章俊,等.重型燃气轮机透平第一级动叶气膜冷却特性数值模拟研究[J].燃气轮机技术,2016, 29(4):37-43.TANG Xuezhi, LI Luping, HUANG Zhangjun, et al. Numerical simulation study on gas film cooling features on the first stage moving blades in a heavy-duty gas turbine[J]. Gas Turbine Technology, 2016, 29(4):37-43.
[8]李少华,宋东辉,刘建红,等.不同孔型平板气膜冷却的数值模拟[J].中国电机工程学报,2006, 26(17):112-116.LI Shaohua, SONG Donghui, LIU Jianhong, et al. Numerical simulations of flat plate film cooling using respectively different shaped jet holes[J]. Proceedings of the CSEE, 2006, 26(17):112-116.
[9]郭婷婷,金建国,李少华,等.不同出射角度对气膜冷却流场的影响[J].中国电机工程学报,2006, 26(16):117-121.GUO Tingting, JING Jianguo, LI Shaohua, et al. A numerical simulation in film cooling flows with different injection angles[J].Proceedings of the CSEE, 2006, 26(16):117-121.
[10]李少华,张玲,朱励,等.涡轮叶片前缘气膜冷却的流线分析[J].中国电机工程学报,2010, 30(14):96-101.LI Shaohua, ZHANG Ling, ZHU Li, et al. Streamline analysis on film cooling at leading edges of turbine blade[J]. Proceedings of the CSEE,2010, 30(14):96-101.
[11]程代京,谢永慧.燃气轮机传热和冷却技术[M].西安:西安交通大学出版社,2005:1-4.
[12]李少华,李知骏,王梅丽,等.旋转对复合角度气膜冷却叶片的数值模拟[J].汽轮机技术,2011,53(3):164-166.LI Shaohua, LI Zhijun, WANG Meili, et al. Numerical simulation study on the effect of rotation on film cooling of blades with compound angle holes[J]. Turbine Technology, 2011,53(3):164-166.
[13]沈菁菁.燃气轮机叶片气膜冷却数值模拟[D].上海:上海发电设备成套设计研究院,2014.
[14]郭婷婷,张玲,邹晓辉,等.旋转叶片气膜冷却效果的数值研究[J].中国电机工程学报,2008(29):83-87.GUO Tingting, ZHANG Ling, ZHOU Xiaohui, et al.Numerical study on the film cooling effect of rotating blades[J]. Proceedings of the CSEE, 2008(29):83-87.
[15]骆剑霞.涡轮叶片内冷结构对外部气膜冷却特性的影响研究[D].西安:西北工业大学,2015.
[2] ITO S, GOLDSTEIN R J, ECKERT E R G. Film cooling of a gas turbine blade[J]. ASME Journal of Engineering for Power, 1978, 100:476-481.
[3] SMITH S H, MUNGAL M G. Mixing, structure and scaling of the jet in crossflow[J]. Journal of Fluid Mechanics, 1998, 357(1):83-122.
[4]高媛,葛利顺,王宏光,等.振动平板单孔气膜冷却实验研究[J].动力工程学报,2016, 36(9):704-710.GAO Yuan, GE Lishun, WANG Hongguang, et al. Experimental study on single-hole film cooling effectiveness over vibrating plates[J]. Journal of Chinese Society of Power Engineering, 2016,36(9):704-710.
[5] AL-ZURFI N, TURAN A, NASSER A. Numerical investigation of rotation effects on anti-vortex film-cooling holes[J]. Flow,Turbulence and Combustion,2016, 96(1):133-162.
[6]常艳,杨卫华,张靖周.突片形状对气膜冷却效率的影响[J].南京航空航天大学学报,2016, 48(3):317-325.CHANG Yan, YANG Weihua, ZHANG Jingzhou. Effects of tab shapes on film cooling effectiveness[J]. Journal of Nanjing University of Aeronautics&Astronautics, 2016, 48(3):317-325.
[7]唐学智,李录平,黄章俊,等.重型燃气轮机透平第一级动叶气膜冷却特性数值模拟研究[J].燃气轮机技术,2016, 29(4):37-43.TANG Xuezhi, LI Luping, HUANG Zhangjun, et al. Numerical simulation study on gas film cooling features on the first stage moving blades in a heavy-duty gas turbine[J]. Gas Turbine Technology, 2016, 29(4):37-43.
[8]李少华,宋东辉,刘建红,等.不同孔型平板气膜冷却的数值模拟[J].中国电机工程学报,2006, 26(17):112-116.LI Shaohua, SONG Donghui, LIU Jianhong, et al. Numerical simulations of flat plate film cooling using respectively different shaped jet holes[J]. Proceedings of the CSEE, 2006, 26(17):112-116.
[9]郭婷婷,金建国,李少华,等.不同出射角度对气膜冷却流场的影响[J].中国电机工程学报,2006, 26(16):117-121.GUO Tingting, JING Jianguo, LI Shaohua, et al. A numerical simulation in film cooling flows with different injection angles[J].Proceedings of the CSEE, 2006, 26(16):117-121.
[10]李少华,张玲,朱励,等.涡轮叶片前缘气膜冷却的流线分析[J].中国电机工程学报,2010, 30(14):96-101.LI Shaohua, ZHANG Ling, ZHU Li, et al. Streamline analysis on film cooling at leading edges of turbine blade[J]. Proceedings of the CSEE,2010, 30(14):96-101.
[11]程代京,谢永慧.燃气轮机传热和冷却技术[M].西安:西安交通大学出版社,2005:1-4.
[12]李少华,李知骏,王梅丽,等.旋转对复合角度气膜冷却叶片的数值模拟[J].汽轮机技术,2011,53(3):164-166.LI Shaohua, LI Zhijun, WANG Meili, et al. Numerical simulation study on the effect of rotation on film cooling of blades with compound angle holes[J]. Turbine Technology, 2011,53(3):164-166.
[13]沈菁菁.燃气轮机叶片气膜冷却数值模拟[D].上海:上海发电设备成套设计研究院,2014.
[14]郭婷婷,张玲,邹晓辉,等.旋转叶片气膜冷却效果的数值研究[J].中国电机工程学报,2008(29):83-87.GUO Tingting, ZHANG Ling, ZHOU Xiaohui, et al.Numerical study on the film cooling effect of rotating blades[J]. Proceedings of the CSEE, 2008(29):83-87.
[15]骆剑霞.涡轮叶片内冷结构对外部气膜冷却特性的影响研究[D].西安:西北工业大学,2015.