Experimental Study of Full Coverage Film Cooling Effectiveness for a Turbine Blade With Compound Shaped Holes

Shuai-qi Zhang, Cun-liang Liu, Qi-ling Guo, Dapeng Liang, Fan Zhang
{"title":"Experimental Study of Full Coverage Film Cooling Effectiveness for a Turbine Blade With Compound Shaped Holes","authors":"Shuai-qi Zhang, Cun-liang Liu, Qi-ling Guo, Dapeng Liang, Fan Zhang","doi":"10.1115/GT2020-15110","DOIUrl":null,"url":null,"abstract":"\n The film coverage of a turbine blade surface is determined by all the film cooling structures. The direct study of full coverage film cooling is relatively rare, especially for related research on turbine blades. In this paper, the pressure-sensitive paint (PSP) measurement technique is used to carry out experiments under different turbulence intensities and mass flux ratios, and the distribution of the film cooling effectiveness on the entire surface is studied in detail. In this study, a basic turbine blade and an improved turbine blade are investigated. The film cooling hole position distribution on the improved blade is the same as that on the basic blade, but the film cooling hole shape on the suction surface and the pressure surface is changed from cylindrical holes to laid-back fan-shaped holes. Both blades have 5 rows of cylindrical holes at the leading edge and 4 rows of film cooling holes on the suction surface and the pressure surface. The leading edge, suction surface, and pressure surface have their own coolant inlet cavities. This kind of design is not only close to the actual working conditions in a flow distribution but also conveniently eliminates the mutual interference caused by the uneven flow distribution between the pressure surface and the suction surface to facilitate the independent analysis of the pressure surface and the suction surface.\n In this paper, the film cooling effectiveness of two kinds of turbine blades under different turbulence intensities and mass flux ratios is studied. The results show that the average cooling effectiveness of the improved blade is much better than that of the basic blade. The laid-back fan-shaped hole rows improve the cooling effectiveness of the suction surface by 60% to 100% and 50% to 120% on the pressure surface. The increase in turbulence intensity will reduce the cooling effectiveness of the blade surface; however, the effect of the turbulence intensity becomes weaker with an increase in the mass flux ratio. Compared with the multiple rows of cylindrical holes, the cooling effectiveness of the laid-back fan-shaped holes is more affected by the turbulence intensity under the small mass flux ratio.","PeriodicalId":147616,"journal":{"name":"Volume 7B: Heat Transfer","volume":"11 1","pages":"0"},"PeriodicalIF":0.0000,"publicationDate":"2020-09-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Volume 7B: Heat Transfer","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.1115/GT2020-15110","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
引用次数: 0

Abstract

The film coverage of a turbine blade surface is determined by all the film cooling structures. The direct study of full coverage film cooling is relatively rare, especially for related research on turbine blades. In this paper, the pressure-sensitive paint (PSP) measurement technique is used to carry out experiments under different turbulence intensities and mass flux ratios, and the distribution of the film cooling effectiveness on the entire surface is studied in detail. In this study, a basic turbine blade and an improved turbine blade are investigated. The film cooling hole position distribution on the improved blade is the same as that on the basic blade, but the film cooling hole shape on the suction surface and the pressure surface is changed from cylindrical holes to laid-back fan-shaped holes. Both blades have 5 rows of cylindrical holes at the leading edge and 4 rows of film cooling holes on the suction surface and the pressure surface. The leading edge, suction surface, and pressure surface have their own coolant inlet cavities. This kind of design is not only close to the actual working conditions in a flow distribution but also conveniently eliminates the mutual interference caused by the uneven flow distribution between the pressure surface and the suction surface to facilitate the independent analysis of the pressure surface and the suction surface. In this paper, the film cooling effectiveness of two kinds of turbine blades under different turbulence intensities and mass flux ratios is studied. The results show that the average cooling effectiveness of the improved blade is much better than that of the basic blade. The laid-back fan-shaped hole rows improve the cooling effectiveness of the suction surface by 60% to 100% and 50% to 120% on the pressure surface. The increase in turbulence intensity will reduce the cooling effectiveness of the blade surface; however, the effect of the turbulence intensity becomes weaker with an increase in the mass flux ratio. Compared with the multiple rows of cylindrical holes, the cooling effectiveness of the laid-back fan-shaped holes is more affected by the turbulence intensity under the small mass flux ratio.
查看原文
分享 分享
微信好友 朋友圈 QQ好友 复制链接
本刊更多论文
复合形孔涡轮叶片全覆盖气膜冷却效果试验研究
涡轮叶片表面的气膜覆盖是由所有气膜冷却结构决定的。对全覆盖气膜冷却的直接研究相对较少,特别是对涡轮叶片的相关研究。本文采用压敏涂料(PSP)测量技术进行了不同湍流强度和质量通量比下的实验,详细研究了膜层冷却效率在整个表面的分布。本文研究了一种基本涡轮叶片和一种改进型涡轮叶片。改进叶片上的气膜冷却孔位置分布与基本叶片相同,但吸力面和压力面上的气膜冷却孔形状由圆柱孔变为斜扇形孔。两叶片前缘均有5排圆柱孔,吸力面和压力面均有4排气膜冷却孔。前缘、吸力面和压力面都有各自的冷却液入口腔。这种设计不仅在流量分布上接近实际工况,而且方便地消除了压力面和吸力面之间由于流量分布不均匀而产生的相互干扰,便于对压力面和吸力面进行独立分析。本文研究了两种涡轮叶片在不同湍流强度和质量通量比下的气膜冷却效果。结果表明,改进叶片的平均冷却效果明显优于基本叶片。扇形孔排将吸力面的冷却效率提高了60% ~ 100%,压力面的冷却效率提高了50% ~ 120%。湍流强度的增加会降低叶片表面的冷却效果;随着质量通量比的增大,湍流强度的影响逐渐减弱。与多排圆柱孔相比,在小质量通量比条件下,扇形孔的冷却效果更受湍流强度的影响。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
求助全文
约1分钟内获得全文 去求助
来源期刊
自引率
0.00%
发文量
0
期刊最新文献
Film Cooling Performance on Turbine Blade Suction Side With Various Film Cooling Hole Arrangements Evaluation of a Machine Learning Turbulence Model in a Square Transverse Jet in Crossflow LES Study of the Effects of Oscillations in the Main Flow on Film Cooling Effects of Film Hole Shape and Turbulence Intensity on the Thermal Field Downstream of Single Row Film Holes Experimental Study of Full Coverage Film Cooling Effectiveness for a Turbine Blade With Compound Shaped Holes
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
现在去查看 取消
×
提示
确定
0
微信
客服QQ
Book学术公众号 扫码关注我们
反馈
×
意见反馈
请填写您的意见或建议
请填写您的手机或邮箱
已复制链接
已复制链接
快去分享给好友吧!
我知道了
×
扫码分享
扫码分享
Book学术官方微信
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术
文献互助 智能选刊 最新文献 互助须知 联系我们:info@booksci.cn
Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。
Copyright © 2023 Book学术 All rights reserved.
ghs 京公网安备 11010802042870号 京ICP备2023020795号-1