涡轮叶片高温多轴低周疲劳/蠕变寿命研究  

Research on low cycle-multiaxial fatigue-creep life prediction at high temperature for turbine blade

作　　者：彭立强[1] 王健[1] 

机构地区：[1]大连理工大学汽车工程学院,大连116023

出　　处：《航空动力学报》2009年第7期1549-1555,共7页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2007CB70770103)

摘　　要：针对航空发动机涡轮转子叶片工作环境,对Manson-Coffin多轴疲劳预测方程和SWT(Smith-Waston-Topper)公式进行修正,同时采用尚德广多轴疲劳损伤参量,给出涡轮叶片新的疲劳寿命预测方法,以适应涡轮叶片高温变幅非比例加载下疲劳损伤情况.通过算例计算了某涡轮叶片疲劳寿命及1000 h的总损伤,与叶片实际疲劳破坏相吻合,验证该高温多轴疲劳损伤计算模型的合理性和可行性.SHANG Deguang multiaxial fatigue damage model was used to amend Manson-Coffin equation of multiaxial fatigue prediction and SWT(Smith-Waston-Topper) formula,based on working condition of turbine rotor blade in aviation engine.A new method of fatigue life prediction of turbine blade was presented,which was adapted for non-proportional loading of turbine blade fatigue damage at high temperature.A case of turbine blade was calculated for fatigue life and the total damage of 1000 hours flying,in well agreement ...

关 键 词：涡轮叶片 高温多轴疲劳 蠕变 疲劳寿命 非比例加载 

分 类 号：V231.95[航空宇航科学与技术—航空宇航推进理论与工程]