保载条件下FGH95材料的疲劳特性及寿命建模

魏大盛; 杨晓光; 王延荣; 于慧臣; 石多奇

保载条件下FGH95材料的疲劳特性及寿命建模

1.
北京航空航天大学能源与动力工程学院, 北京 100083
2.
北京航空材料研究院, 北京 100095

计量
- 文章访问数: 1793
- HTML浏览量: 125
- PDF量: 503
- 被引次数: 0
出版历程
- 收稿日期: 2006-03-02
- 修回日期: 2006-06-26
- 刊出日期: 2007-03-28

Fatigue characteristics of FGH95PM superalloy under dwell condition and modeling for life prediction

1.
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Beijing Institute of Aeronautical Materials, Beijing 100095, China

摘要

摘要: 针对FGH95粉末冶金材料进行了650℃时不同保载形式(拉伸保载、压缩保载和拉压保载)的疲劳试验, 分析了其变形特征和疲劳寿命分布特征以及保载对疲劳寿命的影响.并据此, 为改进保载条件下疲劳寿命的建模, 提出了迟滞环位置-形状修正因子的概念, 进而得到了一种修正的非弹性应变能~寿命方程.经对该材料疲劳试验寿命的建模和计算分析表明:该方法相比其他几种工程上经常采用的寿命预测方程, 较好地解决粉末冶金材料高温保载疲劳时的寿命建模问题, 且该方程对试验寿命预测的精度更高, 形式简单, 具有明显的物理意义.
- 航空、航天推进系统 /
- 粉末高温合金 /
- 寿命预测 /
- 疲劳 /
- 保载 /
- 涡轮盘材料
Abstract: This paper performs describes under different dwell conditions of FGH95 powder metallurgy superalloy at 650℃,and analyses its features of deformation and life distribution,and studies the obvious effect on life due to dwell.Then for improving the life modeling under dwell conditions,a modified factor of position-shape of hysteresis loop is presented,and a modified life equation as function of inelastic energy is established.Comparing with the predictive results of other life equations,the modified life equation has higher predictive precision,more compact form and clearer physical meaning.So life prediction of PM FGH95 under dwell conditions can be solved better.
- aerospace propulsion system /
- powder metallurgy superalloy /
- life prediction /
- fatigue /
- dwell /
- turbine disk material

HTML

参考文献(15)

[1]	Shahani V,Popp R P.Evaluation of cyclic behavior of aircraft turbine disk alloys[R].NASA-CR-159433,1978.
[2]	Cowles B A,Warren J R.Evaluation of the cyclic behavior of aircraft turbine disk alloys:part Ⅱ[R].NASA-CR-165123,1980.
[3]	Stoloff N S,Duquette D J,Choe S J,et al.Fatigue crack growth and low cycle fatigue of two nickel base superalloys[R].NASA-CR-174534,1983.
[4]	Gayda J,Gabb T P,Miner R V.Fatigue crack propagation of nickel-base superalloys at 650℃[R].NASA-TM-87150,1985.
[5]	Goswami T.Dwell sensitivity:part-I behavior and modeling[J].Mechanics of Materials,1995,22:105-130.
[6]	Goswami T,Hnninen H.Dwell effects on high temperature fatigue behavior:Part I[J].Materials and Design,2001,22:199-215.
[7]	Goswami T.A new dwell sensitivity damage parameter[J].Materials and Design,2004,25:191-197.
[8]	Bernstein H L.An evaluation of four current models to predict the creep-fatigue interaction in Rene 95[R].AFML-TR-79-4075,1979.
[9]	Saltsman J F,Halford G R.Procedures for characterizing an alloy and predicting cyclic life with the total strain version of strainrange partitioning[R].NASA-TM-4102,1989.
[10]	宋迎东.粉末冶金涡轮盘强度与寿命研究[D].南京:南京航空航天大学,1997.
[11]	王安强,岳珠峰,杨治国.镍基粉末冶金高温合金的压缩疲劳性能研究[J].航空动力学报,2005,20(3):440-443.WANG Anqiang,YUE Zhufeng,YANG Zhiguo.Study of compression fatigue mechanism of Ni-based powder metallurgy superalloys[J].Journal of Aerospace Power,2005,20(3):440-443.
[12]	王永廉.高温低周疲劳寿命预测模型[J].南京航空航天大学学报,1994,26(3):311-318.WANG Yonglian.High temperature low cycle fatigue life prediction models[J].Journal of Nanjing University of Aeronautics and Astronautics,1994,26(3):311-318.
[13]	胡绪腾,宋迎东.一种修正的应变范围区分法[J].航空动力学报,2005,20(3):418-423.HU Xuteng,SONG Yingdong.Modified strain range partition method[J].Journal of Aerospace Power,2005,20(3):418-423.
[14]	Chen L J,Wang Z G,Yao G,et al.An assessment of three creep-fatigue life prediction methods for nicked-based superalloy GH4049[J].Fatigue Fract Engng Mater Struct,2000,23:509-519.
[15]	Ostergren W J.A damage function and associated failure equations for predicting hold time and frequency effects in elevated temperature,low cycle fatigue[J].Journal of Testing and Evaluation,1976,4(5):327-339.