铸造技术2017，Vol.38Issue(8)：1816-1818,1821,4.DOI:10.16410/j.issn1000-8365.2017.08.010
航空发动机涡轮盘GH4133B合金的疲劳断裂与组织研究
Study on Fatigue Fracture and Microstructure of GH413B Alloy for Aeroengine Turbine Disk
高新红 1朱金波 1徐如涛 1王秋林1
作者信息
- 1. 成都航空职业技术学院工程实训中心,四川成都610021
- 折叠
摘要
Abstract
The fatigue performance of GH4133B alloy for aeroengine turbine disk under different stress amplitudes was investigated,and the fatigue fractures morphology were observed.The results show that the average of GH4133B alloy fatigue theory limit is 239.5 MPa,there is no obviously plastic deformation fatigue fracture when the stress amplitude value is 432 MPa,as a whole,the fracture is relatively smooth.Fatigue source is located at inclusions on the sample surface,it expands to the heart under stress effect,the last fractures zone is located in the outer edge,and there ere the small area shear lips.The second phase particles in the alloy can restrain the expansion of the fatigue crack in a certain extent,and it also slow down the propagation rate of crack.关键词
涡轮盘/GH4133B合金/疲劳寿命/断口/形貌Key words
aeroengine turbine disk/GH4133B alloy/fatigue life/fracture/morphology分类
矿业与冶金引用本文复制引用
高新红,朱金波,徐如涛,王秋林..航空发动机涡轮盘GH4133B合金的疲劳断裂与组织研究[J].铸造技术,2017,38(8):1816-1818,1821,4.
