旋转状态下涡轮叶片复合冷却结构

朱兴丹; 张靖周; 谭晓茗

doi:10.13224/j.cnki.jasp.2017.03.009

旋转状态下涡轮叶片复合冷却结构

doi: 10.13224/j.cnki.jasp.2017.03.009

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室,南京 210016

基金项目: 中央高校基本科研业务费专项资金；江苏省研究生培养创新工程（KYLX_0307）; 航空科学基金（2015ZB52019）

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出版历程
- 收稿日期: 2015-07-24
- 刊出日期: 2017-03-28

Composite cooling structure on rotating turbine blade

摘要

摘要: 采用三维流固耦合换热计算研究了旋转状态下涡轮叶片冷却结构的复合冷却性能,讨论了辐射换热和转速对综合冷却效果的影响.结果表明：结构1叶根处出现局部高温区,低冷却效率范围大,叶片整体温度分布不均匀,结构2通过更合理的气膜流量分配提高了前缘附近冷却效率,降低了叶片表面最高温度,结构3采用内部蛇形通道使吸力面冷却效率显著提高,叶片整体冷却效率分布较为均匀；考虑壁面辐射换热时叶片表面温度升高,当表面发射率为1时局部温升超过50K,壁面辐射换热的影响不能被忽略；压力面综合冷却效率随转速增大而升高,3种结构的局部冷却效率最高分别能提升15.6%，13.4%和16.4%,吸力面上除弦中区冷却效率随转速升高有所降低外,其余位置冷却效率变化不大.
- 涡轮叶片 /
- 复合冷却 /
- 辐射换热 /
- 旋转 /
- 流固耦合
Abstract: 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.
- turbine blade /
- composite cooling /
- radiation heat transfer /
- rotation /
- fluid-solid coupling

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