| 典型层板冷却结构热疲劳破坏特性研究 |
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| 引用本文： | 吴向宇,黎旭,时艳,张翠华,杜治能.典型层板冷却结构热疲劳破坏特性研究[J].航空动力学报,2014,29(5):1177-1183. |
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| 作者姓名： | 吴向宇 黎旭 时艳 张翠华 杜治能 |
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| 作者单位： | 北京航空航天大学 能源与动力工程学院, 北京 100191;中国航空工业集团公司 沈阳发动机设计研究所, 沈阳 110015;中国航空工业集团公司 沈阳发动机设计研究所, 沈阳 110015;中国航空工业集团公司 沈阳发动机设计研究所, 沈阳 110015;中国航空工业集团公司 沈阳发动机设计研究所, 沈阳 110015;中国航空工业集团公司 沈阳发动机设计研究所, 沈阳 110015 |
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| 摘 要： | 针对三种不同形式的典型层板冷却结构,设计加工了高温合金材料试验件.模拟涡轮冷却叶片在实际发动机中的高温工作环境,通过冷热循环加载方式试验研究每种层板冷却结构的热疲劳寿命,分析其破坏部位及破坏原因,并与数值计算结果进行了对比.结果表明:层板冷却结构热疲劳裂纹出现在排气板气膜孔附近,并沿气膜孔纵向扩展,内表面扩展程度大于外表面.在三种层板冷却结构中,211型层板冷却结构热疲劳寿命最低,161型和141型层板冷却结构热疲劳寿命相当.
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| 关 键 词： | 高效冷却 层板冷却结构 涡轮冷却叶片 热疲劳 气膜孔裂纹 |
| 收稿时间： | 2014/2/28 0:00:00 |
Investigation of thermal fatigue failure characteristics on typical cooling laminated configurations |
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| WU Xiang-yu,LI Xu,SHI Yan,ZHANG Cui-hua and DU Zhi-neng.Investigation of thermal fatigue failure characteristics on typical cooling laminated configurations[J].Journal of Aerospace Power,2014,29(5):1177-1183. |
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| Authors: | WU Xiang-yu LI Xu SHI Yan ZHANG Cui-hua and DU Zhi-neng |
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| Institution: | School of Power and Energy Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China;Shenyang Engine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China |
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| Abstract: | Superalloy test pieces for three different typical forms of cooling laminated configurations were designed and processed. High working temperature of cooled turbine blades in real engine was simulated; the thermal fatigue life of each type of cooling laminated configuration by thermal cycling loading was studied experimently; the reasons for its destruction and damage locations were analyzed, and the data were compared with the numerical results. The results show that thermal fatigue cracks in each configuration occur near the film holes of exhaust plate and extend along longitudinal direction of film hole. The cracks extention at inner surface is greater than that at outer surface. 211-type has the shortest thermal fatigue life among three cooling laminated configurations, and the thermal fatigue lifes of 161-and 141-type cooling laminated configurations are on the same level. |
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| Keywords: | high efficiency cooling cooling laminated configuration cooled turbine blade thermal fatigue film hole cracks |
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