摘要
针对某型航空发动机的涡轮叶片,开展了应力计算,进行给定转速和温度场条件下的弹塑性有限元分析,得到应力场;对叶片上的危险位置和最大应力值进行分析,计算提高工况时的涡轮叶片的应力场,分析温度场提高和转速提高对叶身应力分布的影响和最大应力值的变化程度;针对温度场和离心载荷分析计算的结果,对于涡轮叶片结构设计、故障预防维修以及航空发动机整体可靠性有重要意义。
The authors figure out the stress field of a certain type of aircraft engine turbine blades basing on the plastic finite element analysis under a certain rotate speed and temperature field. With the stress field, the authors finds the dangerous position and calculate the maximum stress on blade body, calculates the stress field of turbine blade when improving the condition, analyzes the change of stress on the body distribution and the increase of largest stress level when temperature field and rotate speed increased. The calculation depending on the analysis of the temperature field and centrifugal loads is valuable for structural design, failure prevention and maintenance of turbine blades.
出处
《装备制造技术》
2012年第6期5-8,19,共5页
Equipment Manufacturing Technology
关键词
涡轮叶片
应力分析
有限元
数值模拟
gas-turbine blade
stress analysis
finite element method
numerical simulation.
