基于损伤力学的GH4169合金低循环裂纹萌生寿命预测
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摘要
为了更准确地预估高温材料的低循环疲劳裂纹萌生寿命,将低循环疲劳的裂纹萌生过程视作损伤累积过程,基于连续损伤力学建立了损伤累积模型。结合360℃、650℃下GH4169合金的低循环疲劳寿命数据拟合出模型的具体表达式,进而开展了对低循环疲劳裂纹萌生寿命的预测试验。结果表明:该方法针对GH4169合金低循环疲劳裂纹萌生寿命的预测结果较为理想,其分散带基本在2倍以内,且能很好的反映变幅加载对GH4169合金低循环疲劳裂纹萌生寿命的影响。
In order to predict the low cycle fatigue crack initiation life of high temperature materials, the low cycle fatigue crack initiation life was regarded as a process of damage accumulation and a damage accumulation model was established based on the continuum damage mechanics. Parameters for low cycle fatigue life of GH4169 alloy at the temperatures of 360 ℃ and 650 ℃ were fitted to obtain the definite expression of the model, and low cycle fatigue crack initiation life predictions test were carried out. The results show that the low cycle fatigue crack initiation life used by the approach gives better estimation within about twice of scatter band for GH4169 alloy and a definite influence of variable amplitude loading on the low cycle fatigue crack initiation life of GH4169 alloy can be greatly reflected.
In order to predict the low cycle fatigue crack initiation life of high temperature materials, the low cycle fatigue crack initiation life was regarded as a process of damage accumulation and a damage accumulation model was established based on the continuum damage mechanics. Parameters for low cycle fatigue life of GH4169 alloy at the temperatures of 360 ℃ and 650 ℃ were fitted to obtain the definite expression of the model, and low cycle fatigue crack initiation life predictions test were carried out. The results show that the low cycle fatigue crack initiation life used by the approach gives better estimation within about twice of scatter band for GH4169 alloy and a definite influence of variable amplitude loading on the low cycle fatigue crack initiation life of GH4169 alloy can be greatly reflected.
引文
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[15]王延荣,李宏新,袁善虎,等.确定总应变寿命方程参数的一种方法[J].航空动力学报,2014,29(4):881-886.WANG Yanrong,LI Hongxin,YUAN Shanhu,et al.A method for determination of parameters in total strain life equation[J].Journal of Aerospace Power,2014,29(4):881-886.(in Chinese)
[2]Andersson H,Persson C,Hansson T.Crack growth in IN718 at high temperature[J].International Journal of Fatigue,2001,23(9):817-827.
[3]Burger J L,Biederman R R,Couts W H.The effects of starting condition on the aging response of as-forged alloy 718[C]//Proceedings of the International Symposium on the Metallurgy and Applications of Superalloy 718.Tms,1989:207-217.
[4]Sundararaman M,Mukhopadhyay P,Banerjee S.Precipitation and room temperature deformation behavior of Inconel 718[C]//Proceedings of the International Symposium on Superalloys 718,625,706 and Various Derivatives S.Tms,1994:419-440.
[5]Manson S S.Behavior of materials under conditions of thermal stress[M].Washington:NACA,1953:636-670.
[6]Cof覱n L F.A study of the effect of cyclic thermal stresses on a ductile metal[J].American Society of Mechanical Engineers,1954,76:931-950.
[7]Morrow J D.Cyclic plastic strain energy and fatigue of metals[R].ASTM STP 378,1965.
[8]中国航空材料手册编辑委员会.中国航空材料手册[M].北京:中国标准出版社,1988:323-359.Editorial Board of China Aeronautical Materials Handbook.China aeronautical materials handbook[M].Beijing:China Standard Press,1988:323-359.(in Chinese)
[9]刘新东,郝际平.连续介质损伤力学[M].北京:国防工业出版社,2011:180-210LIU Xindong,HAO Jiping.Continuum damage mechanics[M].Beijing:National Defense Industry Press,2011:180-210.(in Chinese)
[10]Deguang S,Weixing Y.Study on nonlinear continue damage cumulative model for uniaxial fatigue fatigue[J].Acta Aeronautica et Astronautica Sinica,1998,19(6):647-656.
[11]Lemaitre J.Evaluation of dissipation and damage in metals submitted to dynamic loading[J].Mechanical Behavior of Materials,1972,76(6):540-549.
[12]魏大盛,王延荣,王相平,等.基于应力循环特征的裂纹萌生寿命预测方法[J].航空动力学报,2012,27(10):2342-2347.WEI Dasheng,WANG Yanrong,WANG Xiangping,et al.Life prediction method based on characteristic of cyclic stress[J].Journal of Aerospace Power,2012,27(10):2342-2347.(in Chinese)
[13]Rabotnov Y N.Paper 68:On the equation of state of creep[C]//Proceedings of the Institution of Mechanical Engineers.Los Angeles:SAGE Publications,1963:2117-2122.
[14]Liu N,Gong Z,Tang Y,et al.A study on fatigue damage accumulation based on continuum damage mechanics[C]//Quality,Reliability,Risk,Maintenance,and Safety Engineering(ICQR2MSE).Chengdu:IEEE,2012:867-870.
[15]王延荣,李宏新,袁善虎,等.确定总应变寿命方程参数的一种方法[J].航空动力学报,2014,29(4):881-886.WANG Yanrong,LI Hongxin,YUAN Shanhu,et al.A method for determination of parameters in total strain life equation[J].Journal of Aerospace Power,2014,29(4):881-886.(in Chinese)