直接时效GH4169高温合金疲劳裂纹扩展性能试验

何玉怀; 于慧臣; 郭伟彬; 沈莉莉; 苏彬

直接时效GH4169高温合金疲劳裂纹扩展性能试验

北京航空材料研究院, 北京 100095

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出版历程
- 收稿日期: 2005-11-15
- 修回日期: 2005-02-10
- 刊出日期: 2006-04-28

Experimental Study on Fatigue Crack Growth Behavior of Direct Aging GH4169 Superalloy

Beijing Institute of Aeronautical Materials, Beijing 100095, China

摘要

摘要: 对直接时效GH 4169高温合金的疲劳裂纹扩展性能进行了试验研究。分别研究了厚度、温度、应力比等因素对直接时效GH 4169高温合金疲劳裂纹扩展性能的影响。结果表明,在4¹0 mm的厚度范围内,厚度对直接时效GH 4169高温合金疲劳裂纹扩展性能几乎没有影响,但厚度为2 mm且应力比为0.1时其裂纹扩展速率稍有下降;应力比对直接时效GH 4169高温合金疲劳裂纹扩展的影响随着应力比的提高逐渐减小;温度的提高对直接时效GH 4169的裂纹扩展速率有明显的加速作用,但是随着应力强度因子范围的增加,其影响逐渐减小,氧化作用是加速其裂纹扩展的主要机理。
- 航空、航天推进系统 /
- 疲劳裂纹扩展 /
- 应力强度因子 /
- 应力比 /
- 高温合金
Abstract: Fatigue crack growth tests were conducted on a CT specimen of a nickel base superalloy direct aging GH4169.The effects of thickness,temperature and stress ratio on fatigue crack growth behavior were studied separately.The key results are as follows:thickness has no effect on fatigue crack growth behavior in the thickness range from 4 mm to 10 mm,but as thickness is decreased to 2 mm,the fatigue crack growth rate decreases when stress ratio is 0.1;the effect of stress ratio on fatigue crack growth rate diminishes as stress ratio increases;increasing temperature accelerates fatigue crack growth rate,but the effect of temperature diminishes with the increase of stress intensity factor and the main mechanism for accelerating fatigue crack growth is oxidation.
- aerospace propulsion system /
- fatigue crack /
- crack growth rate /
- stress intensity factor /
- stress ratio

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参考文献(10)

[1]	《中国航空材料手册》编辑委员会.变形高温合金铸造高温合金[M].中国航空材料手册第二卷.第二版.北京:中国标准出版社,2002:323～359.
[2]	北京航空材料研究院.航空发动机设计用材料数据手册[M].第一册.北京:中国航空发动机总公司,1989:668～716.
[3]	北京航空材料研究院.航空发动机设计用材料数据手册[M].第二册.北京:国防工业出版社,1993:95～170.
[4]	北京航空材料研究院.航空发动机设计用材料数据手册[M].第三册.北京:航空工业出版社,2006.
[5]	GJB/Z 18-91金属材料力学性能数据表达准则[S].95.
[6]	王中光译.材料的疲劳[M].北京:国防工业出版社,1993:226～232.
[7]	Gayda J,Gabb T P,Miner R V.Fatigue Crack Propagation of Nickel-Base Superalloys at 650C '[A].ASTM STP[C].942,1988:293～309.
[8]	Shahinian P,Sadanands K.Crack Growth Behavior under Creep-Fatigue Conditions in Alloy 718' AD Report[R].A040735,1977.
[9]	Ricker R E,Duquette D J.The Role of Environment on Time Dependent Crack Growth' AD Report[R].AD 109388,1981.
[10]	Michael L Heil.Crack Growth in Alloy 718 under ThermalMechanical Cycling[D].Dissertation,1986.