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中文摘要: 涡轮盘用GH4698合金材料断裂性能数据不足,难以支撑该材料用于燃气轮机涡轮盘损伤容限工程 设计。通过裂纹扩展试验研究,建立该材料在500 ℃下裂纹扩展模型,并进行数值模拟,验证模型的有效性, 为该材料用于燃气轮机涡轮盘损伤容限设计打下基础。
Abstract:Engineering design for damage tolerance of turbine disk is not satisfied for the lack of fracture data of GH4698 alloy. Based on the experimental study of crack growth, a crack growth model of GH4698 alloy at 500 ℃ is established, that is verified by numerical simulation, which lays a foundation on design for damage tolerance of gas turbine disk using the material.
keywords: gas turbine crack damage tolerance
文章编号: 中图分类号:TK474.7;TK475 文献标志码:
基金项目:国家科技重大专项(2017-IV-0008-0045)
引用文本:
作者.题名[J].刊名,出版年份,卷号(期号):起止页码.
[2]KIM K M, PARK J S, DONG H L, et al. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages[J]. Engineering Failure Analysis, 2011, 18(4):1212-1222.
作者.题名[J].刊名,出版年份,卷号(期号):起止页码.
[2]KIM K M, PARK J S, DONG H L, et al. Analysis of conjugated heat transfer, stress and failure in a gas turbine blade with circular cooling passages[J]. Engineering Failure Analysis, 2011, 18(4):1212-1222.