摘要
对国产粉末冶金FGH96镍基高温合金在650℃总应变控制下进行了无保载疲劳试验以及最大拉/压应变保载蠕变-疲劳试验,研究了其失效寿命及失效模式,并与铸造GH4169镍基高温合金的失效寿命进行了对比。结果表明:保载的引入降低了FGH96高温合金的失效寿命,与最大拉应变保载相比,最大压应变保载时产生的蠕变损伤更大,失效寿命更短;FGH96高温合金的疲劳失效寿命基本上高于GH4169高温合金的,但是较高应变幅下(大于1.4%)的蠕变-疲劳失效寿命低于GH4169高温合金的,在较低应变幅下(小于1.4%)则相反;FGH96高温合金的疲劳断口和蠕变-疲劳断口均呈现出表面或近表面多裂纹源失效特征。
Fatigue test without load-holding and creep-fatigue tests with load-holding at maximum tension/compression strains were conducted on domestic powder metallurgy nickel-based superalloy FGH96 under total strain control at 650℃.The failure life and failure mode of the alloy were studied,and the failure life was compared with that of as-cast nickel-based superalloy GH4169.The results show that the introduced load-holding process reduced the failure life of the FGH96 superalloy.Compared with load-holding at maximum tension strain,the creep damage produced during load-holding at the maximum compression strain was larger,resulting in a shorter failure life.The fatigue failure lives of FGH96 superalloy were higher than those of GH4169 superalloy,and the creepfatigue failure lives were lower than those of GH4169 superalloy at relatively high strain amplitude(larger than1.4%),while the opposite was true at relatively low strain amplitude(lower than 1.4%).The fatigue fracture and creep-fatigue fracture of FGH96 superalloy both showed mutiple crack initiation failure characteristics on surface or near surface.
作者
聂潇乾
张成成
王润梓
张显程
涂善东
NIE Xiaoqian;ZHANG Chengcheng;WANG Runzi;ZHANG Xiancheng;TU Shantong(Key Laboratory of Pressurized System and Safety,East China University of Science and Technology,Shanghai 200237,China;Shanghai Engineering Research Center for Commercial Aircraft Engine,AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 201108,China)
出处
《机械工程材料》
CAS
CSCD
北大核心
2019年第6期8-11,17,共5页
Materials For Mechanical Engineering
基金
国家自然科学基金资助项目(51322510)
上海市科委基础重大项目(13DJ1400202)
关键词
蠕变-疲劳
加载波形
粉末冶金合金
断口特征
creep-fatigue
loading waveform
powder metallurgy alloy
fracture characteristic
