Experimental study on film cooling effectiveness of blade with chevron shaped holes under wake influence

Ji Chen Li, Hui Ren Zhu, Da Wei Chen, Dao En Zhou

科研成果: 书/报告/会议事项章节会议稿件同行评审

摘要

Gas turbines have been widely used. With the continuous improvement of the performance of gas turbines, the turbine inlet temperature has greatly exceeded the heat resistance limit of the turbine blade material, so advanced cooling technology is required. The film cooling effectiveness distribution over the blade under the effect of wake was obtained by Pressure Sensitive Paint (PSP) technique. The test blade has 5 rows of chevron film holes on the pressure side, 3 rows of cylindrical film holes on the leading edge and 3 rows of chevron film holes on the suction side. The mainstream Reynolds number is 130,000 based on the blade chord length, and the mainstream turbulence intensity is 2.7%. The upstream wake was simulated by the spoken-wheel type wake generator. The film cooling effectiveness was measured at three wake Strouhal numbers (0, 0.12 and 0.36) and three mass flux ratios (MFR1, MFR2 and MFR3). The results show that the increase of mass flux ratio leads a decrease of the film cooling effectiveness on the suction surface. In the wake condition, the effect of mass flux ratio is weakened. Wake leads a marked decrease of the film cooling effectiveness over most blade surface except for the surface near leading edge on the pressure surface. In the high mass flux ratio condition, the effect of wake on the film cooling effectiveness is weakened on the suction surface and strengthened on the pressure surface.

源语言英语
主期刊名Heat Transfer
出版商American Society of Mechanical Engineers (ASME)
ISBN(电子版)9780791884171
DOI
出版状态已出版 - 2020
活动ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, GT 2020 - Virtual, Online
期限: 21 9月 202025 9月 2020

出版系列

姓名Proceedings of the ASME Turbo Expo
7B-2020

会议

会议ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition, GT 2020
Virtual, Online
时期21/09/2025/09/20

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