铸造2018，Vol.67Issue(4)：308-311,4.
某型航空发动机单晶涡轮叶片热冲击疲劳行为研究
Study of Thermal Shock Fatigue Behavior on the Single Crystal Turbine Blades of a Certain Type Aero-Engine
王小蒙 1王洪斌 1卢玉章 2李青1
作者信息
- 1. 中国航发沈阳发动机研究所,辽宁沈阳110015
- 2. 中国科学院金属研究所,辽宁沈阳110016
- 折叠
摘要
Abstract
The effect of thermal shock fatigue for 1 000 cycles on the damage behavior of turbine blade manufactured by single crystal superalloy was investigated.The results show that the thermal fatigue cracks are formed at the intersection between the separated walls of the trailing edge cutback and the transition rolling angle position of the pressure side of blade,which is quite short with the crack deflection.The γ'precipitates at different positions of blades were micro-observed and characterized quantitatively.The results indicate that the morphology of partial γ'precipitates at the trailing edge of blade is obviously degraded,while the γ'degradation cannot be observed at the other positions of blade,which still retains the regular cubes,revealing that the thermal shock fatigue for 1 000 cycles affects the anti-cooling and thermal fatigue performance of blade,slightly.关键词
涡轮叶片/热冲击疲劳/裂纹/γ'相Key words
turbine blades/thermal shock fatigue/cracks/γ'phase分类
矿业与冶金引用本文复制引用
王小蒙,王洪斌,卢玉章,李青..某型航空发动机单晶涡轮叶片热冲击疲劳行为研究[J].铸造,2018,67(4):308-311,4.
