摘要
在涡轮叶片服役过程中,疲劳是其失效的重要原因之一,而已有研究主要针对不同应变速率下IC10合金1 100℃低周疲劳性能展开,本文研究定向凝固IC10单晶高温合金静态空气介质环境下室温和750℃高周疲劳性能。在应力比R=-1、f≈83.3Hz条件下,进行高周疲劳试验,并利用扫描电镜对疲劳断口进行观察;基于试验观测结果,讨论室温和750℃下IC10单晶高温合金高周疲劳性能差异的内在机制。结果表明:IC10单晶室温疲劳强度为288 MPa,750℃疲劳强度为416 MPa;裂纹萌生于试样表面或近表面缺陷处,断口主要由裂纹萌生区、稳态扩展区和组成。
Fatigue is one of the important reason for losing efficacy during the process of turbine blade service,but current study aims at IC10alloy and low cycle fatigue behavior at different strain rate.The high cycle fatigue properties of single crystal IC10super alloy are investigated at room temperature and750℃in ambient atmosphere in this paper.The high cycle fatigue experiments are tested with ratio of stress R=-1and f≈83.3Hz.The fatigue fracture surface morphology is observed by SEM(scanning electron microscope).The internal mechanism of the high cycle fatigue properties of IC10single crystal super alloy at room temperature and750℃is discussed based on the observation.The result shows that the fatigue strength of single crystal IC10is288MPa at room temperature and416MPa at750℃.The fatigue cracks mainly originate from defects on surface or subsurface of specimen.The fatigue fractures are composed of fatigue source,steady state extension region and transient fracture zone.
作者
张帅奇
王帅
宗毳
陈升平
张强
谭永宁
Zhang Shuaiqi;Wang Shuai;Zong Cui;Chen Shengping;Zhang Qiang;Tan Yongning(The Key Laboratory of Advanced High Temperature Structural Materials, Beijing Institute of Aeronautical Materials, Beijing 100095, China)
出处
《航空工程进展》
CSCD
2017年第4期486-490,共5页
Advances in Aeronautical Science and Engineering
关键词
IC10单晶合金
高周疲劳性能
疲劳裂纹
疲劳强度
IC10 single crystal super alloy
high cycle fatigue property
fatigue crack
fatigue strength
