考虑椭圆孔偏转角组合的凹槽叶顶气热性能优化研究  

Optimization of Aero-Thermal Performance on a Squealer Blade Tip Considering the Combination of Oval Hole Inclination Angles

作　　者：郭嘉杰 梁崇治[2] 郭振东[1] 宋立明[1] 李军[1] GUO Jiajie;LIANG Chongzhi;GUO Zhendong;SONG Liming;LI Jun(School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China;Power Station Service Division,Dongfang Turbine Limited Company,Deyang,Sichuan 618000,China)

机构地区：[1]西安交通大学能源与动力工程学院,西安710049 [2]东方汽轮机有限公司电站服务事业部,四川德阳618000

出　　处：《西安交通大学学报》2023年第10期99-110,共12页Journal of Xi'an Jiaotong University

基　　金：国家科技重大专项资助项目(2019-Ⅱ-0008-0028);国家自然科学基金资助项目(51936008)。

摘　　要：为进一步提高凹槽叶顶的冷却与气动性能,基于Kriging代理模型优化算法,耦合商业CFD分析软件,引入椭圆冷却孔型,设计了凹槽叶顶冷却孔组合偏转角参数化方法,并建立了组合偏转角自动优化框架。以实验条件下的GE-E3首级动叶的叶顶冷却孔布局为研究对象,兼顾冷却与气动两方面性能,开展了凹槽叶顶的冷却孔优化设计与气热分析。研究结果显示,在凹槽叶顶布置吸力面朝向与凹槽尾缘朝向的组合偏角气膜孔能有效增强气膜的贴壁性能,扩大气膜的覆盖范围,同时引导了射流向凹槽尾缘堆积,提升了刮削涡对泄漏流的阻塞作用,有效降低了泄漏流量。椭圆孔依靠低曲率的长轴边出流,相较于圆形孔进一步扩大了气膜覆盖范围并提升了贴壁性能,使凹槽尾缘的流线堆积效应相应增强,进一步地减少了泄漏流量。圆形孔优化结构相比参考结构的气膜冷却效率提高了331.7%,泄漏流量相对减少了1.641%;椭圆孔优化结构的气膜冷却效率提升了565.1%,泄漏流量相对减少率为2.063%。For the purpose of enhancing cooling and aerodynamic performance of the squealer tip,based on the Kriging surrogate model and commercial CFD analysis software,a parameterization method combining inclination angles and cooling holes for the squealer tip was established and an automatic optimization framework was constructed.As the tip cooling hole layout on the GE-E 3 first stage rotor under the experimental conditions was taken as the research object,the optimization and thermal-aerodynamics analysis for the squealer tip were carried out,when both the cooling and the aerodynamic performance were taken into account.The results show that the combination of the negative radial inclination and the positive axial inclination can effectively improve the wall attachment performance and the coverage of the film.It also can divert the jet flow to accumulate at the cavity trailing edge,enhancing the blocking effect between the scraping vortex and the leakage flow and effectively reducing the leakage flow rate.Compared with the round hole,the oval hole can further improve the wall attachment performance and coverage of the film,relying on the outflow from the long axis edge which has a low curvature.so the streamline accumulation effect at the cavity trailing edge is enhanced,and the leakage flow is further reduced.For the round hole,its film cooling effectiveness of the optimization structure is 358.3%higher than that of the reference structure,and the relative reduction rate of leakage flow is 1.641%.For the optimization structure of the oval hole,the values are 565.1%and 2.063%,respectively.

关 键 词：气膜冷却 凹槽叶顶 全局优化算法 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]