机构地区: 南京航空航天大学能源与动力学院动力工程系
出 处: 《机械工程材料》 1999年第2期9-11,37,共4页
摘 要: 简要地阐述了航空发动机涡轮盘材料的发展。对FGH95粉末冶金高温合金与GH169锻造高温合金构件的应力分布以及疲劳寿命进行了对比研究。结果表明,采用FGH95时,涡轮盘应力集中区域的应力值与GH169基本相当,但应变幅值减小。粉末冶金FGH95构件的抗低周疲劳能力远高于锻造GH169,相差几个数量级。 Abstract Development of aeroengine turbine materials is expounded. Comparative analysis of stress distribution and fatigue life between powder metallurgy (PM) FGH95 and wrought GH169 components is carried out. The results show that the stress distributions are similar, however, the strain amplitudes of FGH95 component is smaller. The ability of resistance to low cycle fatigue of PM FGH95 is much higher than that of GH169.