摘要
以拉伸应变能寿命预测模型为理论基础,提出了低循环疲劳模拟试验件(简称模拟件)设计的基本准则。针对某涡扇发动机高压涡轮盘螺栓孔部位进行了模拟件优化设计,设计时综合考虑了试验器能力、螺纹连接强度和所需毛坯盘数量等限制因素。优化目标为模拟件与螺栓孔虚拟裂纹0.8mm内第一主应力和第一主应变分布一致,以及最大应力点第二主应力与第一主应力比值一致。对设计结果进行了弹塑性校核。采用该模拟件构型进行了试验研究,由模拟件试验数据得到的安全寿命和轮盘试验给出的安全寿命的差距为4.48%。
Basic criterion of low cycle fatigue simulating specimen design was proposed based on the theory of tensile strain energy life prediction model.Simulating specimen for bolt holes of a turbofan engine high pressure turbine disc was optimized in design while comprehensively considering the ability of the test machine,thread connection strength and required number of bank disc.The optimizing objectives were as follows：the distribution of the first principal stress and strain within 0.8 mm on the virtuak crack of the simulating specimen was consistent with the real bolt holes,and the ratio of the second principal stress to the first principal stress at the maximum stress point of the simulating specimen was consistent with the real bolt holes.Elastic plastic analysis was conducted to check the stress/strain consistency.The difference between safe life obtained by simulating specimen test and real turbine disc test was 4.48%.
作者
郑小梅
孙燕涛
杨兴宇
肖新红
廖学军
ZHENG Xiaomei;SUN Yantao;YANG Xingyu;XIAO Xinhong;LIAO Xuejun(Beijing Aeronautical Engineering Technical Research Center,Beijing 100076,China;Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2018年第10期2351-2358,共8页
Journal of Aerospace Power
关键词
涡扇发动机
高压涡轮盘
螺栓孔
模拟件
低循环疲劳
安全寿命
turbofan engine
high pressure turbine disc
bolt hole
simulating specimen
low cycle fatigue
safe life
