摘要
为了研究定向凝固涡轮叶片不同部位材料疲劳性能及差异,根据典型涡轮叶片的工艺和几何特征,设计了两类叶片模拟件和用于对比研究的带缺口的对比试件,在此基础上开展了高温低循环疲劳试验和对比分析研究。试验结果表明:缘板模拟件、叶冠模拟件的材料疲劳性能分别为对比试件(和叶身中部材料性能基本相当)的5.93%和7.68%。这说明叶片不同部位的材料疲劳性能差异明显,在定向凝固涡轮叶片的结构、寿命设计中,需要考虑这种差异。研究结果对于定向凝固涡轮叶片设计、分析方法的完善和成形工艺的改进具有重要意义。
Due to the geometry characteristics,the microstructure of different directional solidification（DS） blade regions is different during the solidification process,which suggests that the mechanical properties may also show variation among these regions.Three types of DS specimens（platform-like,shroud-like and notched） are designed to investigate the differences through high temperature low cycle fatigue tests.Tests results show that the fatigue performances of the shroud-like specimen and the platform-like specimen are respectively 7.68% and 5.93% those of the notched specimen.Therefore,the difference of fatigue property among different regions on a DS turbine blade should be considered in blade structure design and fatigue life prediction.The research results may also help to improve the fabrication processes of directional turbine blade solidification.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2011年第10期1930-1936,共7页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(10872015)
航空科学基金(2008ZB51017)
北京航空航天大学博士创新基金~~
关键词
涡轮叶片
低循环疲劳
叶片模拟件
定向凝固
显微组织
turbine blade
low cycle fatigue
blade-like specimen
directional solidification
microstructure
