摘要
通过某型燃气轮机涡轮盘静强度分析结果,并考虑结构的几何特征,确定该涡轮盘榫槽底部冷却通气孔处和轮缘圆弧过渡处为裂纹萌生的关键位置。对涡轮盘冷却气路进口位置构造初始裂纹开展相应的裂纹扩展数值分析工作,结果表明:无论预置周向裂纹还是径向裂纹,在裂纹扩展过程中,Ⅰ型应力强度因子远大于Ⅱ型、Ⅲ型应力强度因子,起主导作用。按损伤容限检查周期规定,当该处裂纹长度小于15.77mm时,轮盘在当前设定的理想工况下不发生断裂。
Based on the static strength analysis results of the gas turbine's turbine disk and considering the geometrical characteristics of the structure,the critical location of crack initiation at the cooling hole of the turbine disk was determined.The initial crack is constructed at the inlet of the cooling path of the turbine disk,and the corresponding crack growth numerical analysis is carried out.The results shows the stress intensity factor of KⅠ,is far greater than that of KⅡ,KⅢin the process of crack growth,which plays the main role.According to the damage tolerance inspection cycle,when the crack length is less than 15.77mm,the wheel disc will not break under the current ideal condition.
作者
冯永志
李岩
刘鹤
石多奇
FENG Yong-zhi;LI Yan;LIU He;SHI Duo-qi(Harbin Electric Company Limited,Harbin 150028,China;Harbin Institute of Technology,Harbin 150001,China;Beijing University of Aeronautics and Astronautics,Beijing 100191,China)
出处
《汽轮机技术》
北大核心
2020年第4期263-266,共4页
Turbine Technology
基金
国家科技重大专项(2017-IV-0008-0045)。
关键词
裂纹
涡轮盘
燃气轮机
gas turbine
crack
damage tolerance
