摘要
本文对某型号航空发动机GH4033第三级涡轮叶片榫头裂纹及断裂失效进行了分析,确定了失效模式为两类,第一类为蠕变疲劳裂纹,第二类为起始应力较大的高低周复合疲劳断裂。研究发现GH4033合金屈服强度偏低、晶界强化能力不足是叶片发生蠕变疲劳开裂的主要原因。而叶片的高低周复合疲劳断裂则主要与个别相邻叶片的叶冠间隙偏大引发的高振动弯曲应力及R处加工刀痕引发的应力集中有关。最后提出了预防叶片发生该类失效的措施。
This paper analyzed the rabbet cracks and fracture failures of the 3rd turbine blades of GH4033 in some aero-engmes. The failure mode could be classified as the creep fatigue and the complex high cycle and low cycle fatigue fracture resulted from initially high stress. The main causes for the creep fatigue cracking were the low yield strength and the poor reinforcement effect of GH4033. And the main causes for the high stress fatigue fracture were the high bending-vibration stress from the large interval between some tip shrouds and the stress concentration from the machining remarks at the R. Measurements were given to such failures.
出处
《失效分析与预防》
2007年第1期24-28,共5页
Failure Analysis and Prevention
