TC4合金组织演变对力学性能的影响研究
Research on the Influence of TC4 Alloy Structure Evolution on Mechanical Properties
张瑜1
作者信息
- 1. 大连职业技术学院,辽宁 大连 116000
- 折叠
摘要
航空发动机风扇机匣、转子叶片和钛合金整体叶盘等部件在焊接制造过程中,焊缝部位组织易发生转变,降低了焊缝疲劳性能,导致焊缝部位的开裂故障时有发生.鉴于此,主要针对TC4型钛合金在5种热处理状态下的高周疲劳性能进行研究,结果表明:在室温、700 ℃、800 ℃、900 ℃、1 000 ℃、1 100 ℃六种热处理状态下,TC4合金的疲劳强度分别为782.7 MPa、780 MPa、725.6 MPa、660 MPa、553.3 MPa、590 MPa,均满足95％置信度;随着热处理温度的升高,TC4合金的高周疲劳强度逐渐降低,1 100 ℃热处理状态下的疲劳强度略高于1 000 ℃热处理状态下的疲劳强度;热处理过程中产生的元素再分配过程是导致合金高周疲劳极限随着热处理温度的升高而降低的主要原因.
Abstract
In the welding process of aero-engine fan casing,rotor blade,titanium alloy integral blade disk and other components,the microstructure of weld parts is changed,which reduces the fatigue performance and leads to the cracking failure of weld parts.This paper mainly studies the high-cycle fatigue performance of TC4 titanium alloy under five heat treatment states,and the results show that at room temperature,700 ℃,800℃.900 ℃,1 000 ℃ and 1 100 ℃,the fatigue strength of TC4 alloy is 782.7 MPa,780 MPa,725.6 MPa,660 MPa,553.3 MPa and 590 MPa,which meet 95％confidence.With the increase of heat treatment temperature,the high cycle fatigue strength of TC4 alloy decreases gradually,and the fatigue strength at 1 100 ℃ is slightly higher than that at 1 000 ℃.The element redistribution process during heat treatment is the main reason that the high cycle fatigue limit of the alloy decreases with the increase of heat treatment temperature.
关键词
航空发动机/钛合金组织/高周疲劳性能/组织演化Key words
aeroengine/titanium alloy structure/high cycle fatigue performance/organizational evolution引用本文复制引用
基金项目
大连职业技术学院(大连开放大学)校级科研课题(ZK2023QN12)
出版年
2024
NETL
NSTL
万方数据