机构地区: 南京航空航天大学能源与动力学院
出 处: 《机械工程材料》 2002年第7期1-3,27,共4页
摘 要: 对某发动机DZ4定向凝固高温合金涡轮叶片进行了有限元应力分析 ,应力分析中考虑了发动机实际工作过程中的离心载荷和不均匀温度场引起的热负荷。利用应力分析结果和该材料的疲劳特性计算了 1次飞行起落过程造成的发动机低循环疲劳损伤和 90 0h飞行的总损伤。根据损伤等效原理 ,确定了试验规定条件下与 90 Finite element stress analysis is performed on the directionally solidified superalloy turbine blade of an engine. Centrifugal loading and thermal loading due to non uniform temperature field are considered in the stress analysis. Using the stress analysis results and the material's low cycle fatigue characteristics, the low cycle fatigue damage during one flight and total damage in 900 flight hours are calculated. Based on damage equivalent principle, the equivalent test loading spectra of 900 flight hours and the formula for turning the test life into flight life are derived.