• 首页本刊介绍编委会投稿须知审稿编辑流程期刊征订广告征订English
  • 选择皮肤:
李迪,陈云永,廖连芳.空心风扇叶片高循环疲劳试验设计与验证[J].航空动力学报,2017,32(6):1359~1365
空心风扇叶片高循环疲劳试验设计与验证
Experimental design and verification of hollow fan blade high cycle fatigue
投稿时间:2015-09-22  
DOI:10.13224/j.cnki.jasp.2017.06.011
中文关键词:  空心风扇叶片  高循环疲劳  圆弧形燕尾榫头  试验设计  验证
英文关键词:hollow fan blade  high cycle fatigue  curved dovetail root  experimental design  verification
基金项目:
作者单位
李迪 中国航空发动机集团有限公司 商用航空发动机有限责任公司 设计研发中心上海 201108 
陈云永 中国航空发动机集团有限公司 商用航空发动机有限责任公司 设计研发中心上海 201108 
廖连芳 中国航空发动机集团有限公司 商用航空发动机有限责任公司 设计研发中心上海 201108 
摘要点击次数: 219
全文下载次数: 
中文摘要:
      基于实际大涵道比航空涡扇发动机宽弦风扇叶片的结构特征,设计、加工了空心风扇叶片结构模拟件,完成了空心风扇叶片高循环疲劳试验设计,并着重对其叶身空心结构部分抗疲劳能力进行了试验验证.试验结果表明试验夹具和试验件的设计能够完成空心风扇叶片高循环疲劳考核的目的.同时,该空心风扇叶片结构叶身部分对应1×107次循环的高循环疲劳强度介于370MPa至400MPa之间,满足其在最大工作状态下疲劳强度不小于324MPa的高循环疲劳设计要求.因试验件数量相对较少,仅获得了给定应力水平下的高循环疲劳寿命数据,后续可按照该技术途径和方法流程适当增加试验件数量,以获取疲劳极限进而构建其应力-疲劳寿命曲线,为工程研制奠定基础并积累数据.
英文摘要:
      Based on the structure feature of wide chord blade of actual high bypass ratio turbo-fan engine, the design and manufacturing of hollow fan blade specimen were finished, followed by high cycle fatigue experimental design and emphasized verification of the fatigue endurance of hollow structure. The experiment results indicate that the design of fixture and fan blade specimen could accomplish the high cycle fatigue experiment on hollow fan blade. Meanwhile, the high cycle fatigue strength of the hollow fan blade which lies between 370MPa and 400MPa for 1×107 cycle could fulfill the high cycle fatigue design requirement that the hollow fan blade should have high cycle fatigue strength no less than 324MPa under maximum operating condition. However, due to the lack of sufficient quantity of specimens, high cycle fatigue data were only derived under limited stress levels. Further research could be carried out similarly with increased quantity to estimate the fatigue endurance and then construct the stress-fatigue curve, providing prime data base for engineering research.
查看全文  查看/发表评论  下载PDF阅读器
关闭
.