• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>Proceeding of An International Conference the Importance of understanding the fundamentals of the fatigue Process in Counteracting Its Effects in Engineering Components and Structures,and to Reflect on the Contributions of K.J.Miller Sheffield/United >Life assessment of fracture ciritical aeroengine parts
【24h】

Life assessment of fracture ciritical aeroengine parts

机译：航空发动机关键零件的寿命评估

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

The paper reviews European and US Defence Standards and Civil Regulatory requirements relating to the determination and the declaration of aeroengine disc lives.The specific fatigue models on which the various lifiing procedures are based include: crack initiation based methods (such as 'life-to-first-crack'),crack propagation based procedures (such as 'database lifing' and 'damage tolerance') and total life concepts (such as '2/3' dysfunction and 'retirement-for-cause').In the selection of a particular procedure to calculate the life of a component,consideration must be given to the type of material (titanium,nickel,etc.) its processing route ()conventional wrought or high strength powder,etc.) and to the design life required.The necessity for statistical assessment of the experimental data is considered with reference to the determination of safe component service lives.
机译：本文回顾了与航空发动机盘寿命的确定和声明有关的欧洲和美国国防标准以及民用法规要求。各种限制程序所基于的特定疲劳模型包括：基于裂纹萌生的方法（例如``寿命至第一裂纹），基于裂纹传播的过程（例如``数据库生命''和``破坏容忍''）以及总寿命概念（例如``2/3''功能障碍和``因果退休''）。计算组件寿命的特定程序，必须考虑材料的类型（钛，镍等），其加工路线（常规锻造或高强度粉末等）以及所需的设计寿命。考虑到安全部件使用寿命的确定，考虑了对实验数据进行统计评估的必要性。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号