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 ...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
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)
关键词
涡轮叶片
高温多轴疲劳
蠕变
疲劳寿命
非比例加载
turbine blade
multiaxial fatigue at high temperature
creep
fatigue life
non-proportional loading
