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所属单位：能源与动力学院

发表刊物：Hangkong Dongli Xuebao

摘要：Composite cooling performance of a rotating turbine blade cooling structure was investigated through heat transfer simulation with three-dimensional fluid-solid coupling, and the effects of radiation heat transfer and rotational speed on overall cooling effectiveness were discussed. Results showed that a local high-temperature area around the blade hub and hence a large scope of low cooling effectiveness occurred, leading to a nonuniform distribution of overall temperature for blade structure 1. The cooling effectiveness adjacent to the leading edge was improved, lessening the low effectiveness area as a result of more reasonable film flow distribution of blade structure 2. The cooling effectiveness on blade suction side was markedly enhanced through internal serpentine passages and a uniform distribution of integral cooling effectiveness was obtained for blade structure 3. The blade temperature increased with a regional temperature increment over 50K for the surface emissivity of 1, while the effect of radiation heat transfer can't be ignored. The overall cooling effectiveness on pressure side improved with the augmentation of rotational speed, resulting in a highest regional increase percentage of 15.6%, 13.4% and 16.4% for the three structures, respectively. Nevertheless, the cooling effectiveness on suction side produced little change except a reduction at mid-chord region with the increase of rotational speed. © 2017, Editorial Department of Journal of Aerospace Power. All right reserved.

ISSN号：1000-8055

是否译文：否

发表时间：2017-03-01

合写作者：Zhu, Xing-Dan,谭晓茗

通讯作者：张靖周