镍基高温合金高温环境下裂纹扩展速率研究
Study on Crack Growth Rate of Ni-base Superalloy at High Temperature
袁珂 1王甲贺 2黄子琳 1方向 1杨文鑫 2王艳芳2
作者信息
- 1. 中国航发湖南动力机械研究所,湖南 株洲 412002
- 2. 青岛苏试海测检测技术有限公司,山东 青岛 266000
- 折叠
摘要
GH4720Li镍基高温合金作为航空发动机涡轮盘的主要材料,其损伤容限性能对航空发动机起主要作用.本文完成了高温环境下的定K、降K两组裂纹扩展速率试验.试验得到的Pairs公式参数n和C与文献相比吻合度很好,并给出了材料的门槛值;对试样断口分析发现定K试样扩展区和瞬断区均出现剪切断裂特征.
Abstract
GH4720Li Ni-base superalloy is the main material of aero-engine turbine disk,and its damage tolerance plays an important role in aero-engine.In this paper,two sets of fatigue crack growth rate tests of constant k and decreasing K at high temperature have been completed.The Pairs formula parameters n and C are in good agreement with the references,and the material threshold is given.The analysis of fracture surface shows that the shear fracture appears in both the extension zone and the instantaneous fracture zone of the fixed-k specimen.
关键词
镍基高温合金/裂纹扩展速率/降K/断口分析Key words
Nickel base superalloy/crack growth rate/k-drop/fracture analysis引用本文复制引用
基金项目
国家科技重大专项(J2019-Ⅷ-0002-0163)
出版年
2024
NETL
NSTL
万方数据