摘要
对直接时效GH4169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GH4169高温合金疲劳裂纹扩展性能的影响。结果表明，在4～10mm的厚度范围内，厚度对直接时效GH4169高温合金疲劳裂纹扩展性能几乎没有影响，但厚度为2mm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GH4169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GH4169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。
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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2006年第2期349-353,共5页
Journal of Aerospace Power
关键词
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
aerospace propulsion system
fatigue crack
crack growth rate
stress intensity factor
stress ratio
superalloy
