期刊文献+

航空发动机外物损伤试验技术研究 被引量:7

EXPERIMENTAL TECHNIQUE FOR INVESTIGATION ON FOREIGN OBJECT DAMAGE OF AEROENGINE
下载PDF
导出
摘要 A method to determine the size of notch on first stage blade of compressor with a stress concentrated factor (K t) of three is briefly introduced,which is required for foreign object damage (FOD)testing of aeroengines.It is based on 8-node and 20-node finite element appoaches respectively.The 8-node super-parameter element approach is used to calculate the stress distribution of a whole blade without and with notch,and the 20-node 3D iso-parameter finite element programm is applied to computation of local stress distribution around a notch of blade.The practical testing techniques and test results are also presented. A method to determine the size of notch on first stage blade of compressor with a stress concentrated factor (K t) of three is briefly introduced,which is required for foreign object damage (FOD)testing of aeroengines.It is based on 8-node and 20-node finite element appoaches respectively.The 8-node super-parameter element approach is used to calculate the stress distribution of a whole blade without and with notch,and the 20-node 3D iso-parameter finite element programm is applied to computation of local stress distribution around a notch of blade.The practical testing techniques and test results are also presented.
出处 《航空动力学报》 EI CAS CSCD 北大核心 1990年第3期227-228,共2页 Journal of Aerospace Power
  • 相关文献

同被引文献91

引证文献7

二级引证文献108

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部