摘要
根据某型航空发动机低压涡轮盘的实际结构进行有限元建模,并根据涡轮盘的载荷特点,采用循环对称基本理论对其1/64扇区的载荷进行了计算。对涡轮盘的离心负荷的热弹性应力进行了综合考察与分析,计算得出最大应力集中发生在涡轮盘中心孔处,对进行同类型的涡轮盘强度分析与寿命计算具有借鉴作用。
Finite element modeling for a certain type of dual - rotor aero - engine low - pressure turbine disk, and calculation of 1 / 64 of the turbine disk load by using cyclic symmetry of basic theory in accordance with its characteristics. A comprehensive consideration hot elastic stress of centrifugal load is analysised for turbine disk. Calculated the maximum stress concentration occurred in the turbine disk center hole, and it has with reference to analysis of intensity and calculation of life expectancy the same type of turbine disk started.
出处
《沈阳航空工业学院学报》
2009年第4期1-4,8,共5页
Journal of Shenyang Institute of Aeronautical Engineering
关键词
涡轮盘
强度
强度计算
有限元分析
finite elementmethod
strengh calculation
strengh
turbine disic
