摘要
针对涡轮动叶凹槽状叶顶近压力侧气膜冷却设计的结构,设计了2条全肋条、1条全肋条和1条压力侧尾缘半肋条与1条吸力侧尾缘半肋条的3种凹槽状叶顶肋条布局设计。采用数值求解三维Reynolds-Averaged Navier-Stokes(RANS)方程和标准k-ω湍流模型研究了肋条布局的凹槽状叶顶气膜冷却效率和气热性能,研究了4种吹风比下2条全肋条布局的凹槽状叶顶的传热冷却性能。在吹风比为1.0时,对比分析了典型凹槽状叶顶和3种肋条布局凹槽状叶顶的气动传热特性和气膜冷却效率。结果表明:数值预测的叶顶传热系数分布与实验测量结果吻合良好,验证了数值方法的可靠性;吹风比1.0时,全肋条凹槽状叶顶具有最高的平均气膜冷却效率;全肋条布局凹槽状叶顶具有最高的平均气膜冷却效率;相比于典型凹槽状叶顶,全肋条布局凹槽状叶顶能够使气膜冷却效率提高2.2%;压力侧半肋条布局的凹槽状叶顶具有最低的平均传热系数和总压损失系数;肋条布局通过调控叶顶涡系与冷气的迁移路径而显著改变了凹槽状叶顶的流场结构,进而影响气热性能和气膜冷却效率;全肋条布局的动叶凹槽状叶顶具有最佳的综合气热性能和气膜冷却效率。
This study focuses on the squealer tip film cooling design of turbine blades,presenting three layouts:two with full ribs,one with a full rib and a half-rib on the pressure side,and one with a half-rib on the suction side.Using numerical simulations through three-dimensional Reynolds-Averaged Navier-Stokes(RANS)equations and a standard k-ωturbulence model,the heat transfer and cooling performance of grooved blade tips with two full rib layouts were studied under four different blowing ratios.The aerodynamic and heat transfer performance,as well as film cooling effectiveness of blade squealer tip with different rib layouts and typical squealer tip without rib layout were compared and analyzed at blow ratio 1.0 condition.Results show that the distribution of heat transfer coefficient at the blade tip predicted by numerical methods is in good agreement with the experimental measurement results,which verifies the reliability of the numerical method;at a blowing ratio of 1.0,the squealer tip with full ribs exhibits the highest average film cooling effectiveness,surpassing the typical groove design by 2.2%in effectiveness.The layout with half ribs on the pressure side shows the lowest average heat transfer coefficient and total pressure loss.Rib configurations markedly alters the flow structure over the leaf top,thereby affecting its aerothermal performance and film cooling effectiveness,with the full rib layout displaying optimal overall aerothermal performance and cooling effectiveness.
作者
周祚弘
程国强
许承天
孔祥林
李志刚
李军
ZHOU Zuohong;CHENG Guoqiang;XU Chengtian;KONG Xianglin;LI Zhigang;LI Jun(Institute of Turbomachinery,Xi'an Jiaotong University,Xi'an 710049,China;Dongfang Electric Corporation Dongfang Turbine Co.,LTD,Deyang 618000,Sichuan Province,China;State Key Laboratory of Clean and Efficient Turbomachinery Power Equipment,Deyang 618000,Sichuan Province,China)
出处
《动力工程学报》
CAS
CSCD
北大核心
2024年第9期1446-1458,共13页
Journal of Chinese Society of Power Engineering
关键词
涡轮动叶
凹槽状叶顶
肋条布局
气热性能
气膜冷却效率
turbine blade
squealer tip
rib layout
aerothermal performance
film cooling effectiveness
作者简介
周祚弘(1999-),男,重庆涪陵人,博士研究生,研究方向为气动热力学与传热冷却。电话(Tel.):17323457129,E-mail:fly0805@stu.xjtu.edu.cn。
