摘要
在高温长期服役条件下高温合金涡轮叶片的组织存在老化和性能退化问题。通过对DZ406合金试样进行预先加载处理,模拟涡轮叶片的高温服役环境,热力耦合模拟条件分别为980℃/70 MPa,980℃/110 MPa,980℃/140 MPa与980℃/180 MPa,再对试样进行980℃/275 MPa持久实验。观察分析不同服役载荷条件下试样的显微组织和980℃/275 MPa持久寿命。结果表明:DZ406合金标准热处理组织由碳化物、残余(γ+γ′)共晶和规则立方状的γ′相组成;在模拟服役条件热力耦合作用下,随着服役载荷应力的增加,合金的共晶和碳化物形貌及尺寸无明显变化,平行于[001]方向试样的γ′相呈现不同程度的筏排化,垂直于[001]方向截面的γ′相尺寸明显增大;随着服役载荷应力的增加,不同热力耦合作用试样的剩余持久寿命迅速降低。
There is a problem about microstructure evolution and properties degradation for the superalloy turbine blades in long term service conditions. DZ406 alloy samples were pre-loaded to simulate the high temperature service environment of turbine blades. The thermodynamic coupling simulation conditions were 980 ℃/70 MPa, 980 ℃/110 MPa, 980 ℃/140 MPa and 980 ℃/180MPa respectively. And then the samples were subjected to stress rupture property test at 980 ℃/275 MPa. The microstructure and980 ℃/275 MPa rupture life of the samples under different service loading conditions were observed and analyzed. The results show that the heat treatment microstructure of DZ406 alloy is composed of carbides, residual γ +γ′ eutectic and regular γ′ phase. The morphology and size of carbides and eutectic have no obvious change with the increase of loading stress under simulated service conditions. The γ′ phase of the sample parallel to [001] direction presents different degrees of rafting, and the size of γ′ phase perpendicular to [001] direction obviously increases. The residual stress rupture life of the sample declines rapidly with the increase of service stress.
作者
贾新云
宗毳
郭婧
陈升平
郑真
赵文侠
黄朝晖
JIA Xinyun;ZONG Cui;GUO Jing;CHEN Shengping;ZHENG Zhen;ZHAO Wenxia;HUANG Zhaohui(AECC Science and Technology on Advanced High Temperature Structural Materials Laboratory,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China;AECC Hunan Powerplant Research Institute,Zhuzhou 412002,Hunan,China;Beijing Key Laboratory of Aeronautical Materials Testing and Evaluation,AECC Beijing Institute of Aeronautical Materials,Beijing 100095,China)
出处
《航空材料学报》
CAS
CSCD
北大核心
2022年第2期83-90,共8页
Journal of Aeronautical Materials
关键词
定向高温合金DZ406
热力耦合模拟
持久寿命
筏排化
directional DZ406 superalloy
thermodynamic coupled simulation
stress rupture life
rafting
