摘要
实验研究了三种不同状态下ＴＣ１１钛合金锻件中的疲劳裂纹扩展。发现锻造工艺不同的ＴＣ１１钛合金疲劳裂纹扩展机制和裂纹扩展速率无明显差异；疲劳裂纹扩展速率曲线可用公式ｄａ／ｄＮ＝Ｂ（ΔＫ－ΔＫｔｈ）２拟合。结合对文献中许多不同钛合金疲劳裂纹扩展数据的分析结果，给出了一种通用性较强的钛合金疲劳裂纹扩展速率估算方法，即ｄａ／ｄＮ＝１５．９／Ｅ２［ΔＫ－（α－βσ０．２）（１－Ｒ）γ］２对于钛合金板材，γ＝０．８５，α＝１６．５ＭＰａ·ｍ１／２，β＝０．１１ｍ１／２。
The fatigue crack propagation (FCP) behavior of a wrought TC11 titanium alloy under three different conditions was investigated, little influence of the high temperature deformation processes was observed on the FCP mechanisms and the FCP rates. The FCP formula d a/ d N=B( Δ K- Δ K th ) 2 gives good fits to the FCP test data of titanium alloys available from the present investigation, as well as to those from literature. On the basis of this formula, a simple method for predicting the FCP rates was offered. That is, d a d N=15.9/E 2[ Δ K-(α-β σ 0.2 )(1-R) γ] 2 for titanium alloy sheets, γ=0.85, α=16.5 MPa·m 1/2 , β=0.11 m 1/2 .
出处
《中国有色金属学报》
EI
CAS
CSCD
北大核心
1998年第A01期128-131,共4页
The Chinese Journal of Nonferrous Metals
关键词
钛合金
疲劳裂纹扩展
门槛值
飞机
titanium alloy fatigue crack propagation threshold
