航空发动机涡轮盘榫槽应力梯度模拟件设计与验证  

Design of Stress Gradient Simulated Specimen of Aeroengine Disc Groove and Test Verification

作　　者：腾雪峰 尚柏林[3] TENG Xuefeng;SHANG Bolin(School of Power and Energy,Nanchang Hangkong University,Nanchang 330063,China;Engineering Research Center of Aero-engine Technology for General Aviation,Ministry of Education,Nanchang 330063,China;School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]南昌航空大学动力与能源学院,南昌330063 [2]通航涡轮动力技术教育部工程研究中心,南昌330063 [3]西北工业大学航空学院,西安710072

出　　处：《失效分析与预防》2025年第1期11-17,59,共8页Failure Analysis and Prevention

基　　金：国家科技重大专项(J2019-Ⅳ-0017-0085)。

摘　　要：结构特征模拟件高温疲劳试验是航空发动机轮盘强度设计的重要参考。为研究某涡轮盘榫槽低循环疲劳性能和失效破坏机理,本文基于几何特征相同、应力梯度一致的原则,设计了一种航空发动机涡轮盘榫槽应力梯度模拟件。采用数字图像相关法获得模拟件的应变分布特征,验证榫槽模拟件考核部位的应力梯度与设计目标吻合;应力梯度模拟件在高温疲劳载荷下的断裂破坏均出现在预期考核位置。结果表明:FGH96榫槽应力梯度模拟件在550℃高温疲劳载荷下,出现类解理萌生裂纹,断口扩展区可见明显的疲劳条带特征;在疲劳寿命后期,断口局部观察到明显的解理面和韧窝特征。The high temperature fatigue test of mockup featuring structural characteristicses is an important reference for the strength design of aeroengine disc.To investigate the low-cycle fatigue performance and failure mechanism of a turbine disc groove,based on the principle of the same geometric characteristics and the same stress gradient,a stress gradient mockup for turbine disc groove of an aeroengine was designed.The strain distribution characteristics of the mockup were obtained using the digital image correlation method,and the stress gradient of the mockup was consistent with the design target.Under high temperature fatigue loads,the fracture failure of the stress gradient simulated specimen all occurred at the expected test positions.The high temperature fatigue test revealed that class cleavage initiation cracks appeared in the FGH96 stress gradient simulated specimen under the fatigue load at 550℃,and the fracture showed obvious fatigue band characteristics.In the later stage of fatigue life,obvious cleavage surface and dimple characteristics were observed at the fracture site.

关 键 词：涡轮盘 模拟试验件 高温疲劳 结构强度 应力梯度 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]