Effects of rib structure on flow and heat transfer characteristics of film cooling rotor blade with squealer tip

被引：0
|
作者：
Yang B. [1 ]
Tan X. [1 ]
Shan Y. [1 ]
Zhang J. [1 ]
机构：
[1] Key Laboratory of Thermal Management and Energy Utilization of Aircraft, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Shan, Yong (nuaasy@nuaa.edu.cn) | 1600年 / Beijing University of Aeronautics and Astronautics (BUAA)卷 / 36期
关键词：
Blade tip rib; Film cooling; Heat transfer characteristics; Squealer tip; Tip leakage flow; Turbine blade;
D O I：
10.13224/j.cnki.jasp.20200434
中图分类号：
学科分类号：
摘要：
In order to inhibit the tip leakage flow and reduce the tip thermal load of turbine rotor blade, numerical simulation method was used to calculate the flow field of high pressure turbine rotor blade with film cooling of five structures of tip rib, and the aerothermal performance was evaluated.The results showed that the location and path of the cavity vortex, the scraping vortex, vortex induced by rib and the kidney eddies can be effectively controlled by adding rib structure, which can reduce the high surface heat transfer coefficient region and improve the average film cooling efficiency of the blade tip. At the same time, the tip leakage flowing into the leading edge of pressure side was reduced, and the total pressure loss coefficient caused by tip leakage flow was decreased. The aerothermal performance and the effect on adding leakage flow resistance of squealer tip with the half rib structure in the rear squealer cavity were the best. Compared with the case without ribs, the average surface heat transfer coefficient of blade tip was reduced by 20.1%, and the average film cooling efficiency was increased by 24.3%. © 2021, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1462 / 1471
页数：9
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