镍基合金涡轮叶片的服役损伤机理与性能衰减  

Service damage mechanism and performance attenuation of nickel-based alloy turbine blades

作　　者：陈操 韩雷 张钰 闫晓军[4] CHEN Cao;HAN Lei;ZHANG Yu;YAN Xiaojun(AVIC CAPDI Integration Equipment Co.,Ltd.,Beijing 100120,China;Department of Aeronautics and Astronautics,Fudan University,Shanghai 200433,China;China Ship Development and Design Center,Wuhan 430064,China;School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]中航工程集成设备有限公司,北京102206 [2]复旦大学航空航天系,上海200433 [3]中国舰船研究设计中心,武汉430064 [4]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空材料学报》2021年第4期96-108,共13页Journal of Aeronautical Materials

基　　金：国家自然科学基金(51975127);中国上海国际一带一路合作项目(20110741700);复旦研究启动基金(FDU38341)。

摘　　要：通过开展多尺度观察与疲劳性能实验,研究K403制涡轮叶片的服役损伤演化机理与疲劳性能衰减行为。结果表明:外场服役过程中,叶片内部的枝晶分离与破碎,γ'相聚合、筏化,MC碳化物分解、有害相析出以及晶界弱化等都会对涡轮叶片的疲劳性能产生不利影响;同时,基体元素的大量流失致使合金基体软化;另外,服役过程中形成的大量孔洞和微裂纹,也会进一步降低涡轮叶片的服役性能。经过长期服役后,K403制涡轮叶片的固溶强化、析出强化、弥散强化和晶界强化效果均被削弱,从而导致涡轮叶片的疲劳性能发生严重退化、寿命降低;同时,涡轮叶片的起裂源由亚表面金属学孔洞起裂逐渐转变为碳化物起裂。Multi-scale morphology observations and fatigue performance tests were carried out to study the damage evolution mechanism and fatigue performance attenuation behavior of K403 turbine blades in service.During service in field,the dendrite separation and breakage,γ'phase polymerization and rafting,MC carbide decomposition,harmful phase precipitation and grain boundary weakening are having adverse effects on the fatigue performance of turbine blades.Meanwhile,the loss of alloying elements in matrix causes the alloy matrix to soften.In addition,a large number of pores and microcracks formed in the process of service further deteriorate the service performance of turbine blades.Therefore,after long-term operations,the solid solution strengthening,precipitation strengthening,dispersion strengthening and grain boundary strengthening effects of K403 turbine blades are all weakened,which led to serious degradation of the fatigue performance of these turbine blades with the fatigue life reduced.Besides,the crack initiation source of turbine blade is gradually transformed from subsurface metallic pore initiation to carbide initiation.

关 键 词：镍基高温合金 涡轮叶片 服役损伤 微观组织演变 疲劳失效 

分 类 号：TG146.34[一般工业技术—材料科学与工程]