摘要
对于航空发动机涡轮盘来说,主要存在蠕变失效和疲劳失效这两种失效模式;在循环工作条件下,蠕变损伤和疲劳损伤不断累积,且蠕变损伤和疲劳损伤存在交互作用。此外,由于金属材料在高温和高应力下存在明显的蠕变变形,从而造成涡轮盘存在应力松弛现象。因此,蠕变-疲劳损伤分析就成为涡轮盘寿命预测的重要组成部分。基于线性损伤累积理论,提出了在典型梯形循环转速谱作用下考虑应力松弛的涡轮盘蠕变-疲劳寿命的工程化快速算法。并利用算例验证了该方法的有效性。
For turbine discs, the hot section components of gas turbine engine,fatigue and creep are two important failure mechanisms. Creep damage and fatigue damage manner, and the interaction between creep damage increase with applied loading cycles in a cumulative and fatigue damage may be significant. Metallic material under high level stresses at elevated temperature can produce creep deformation significantly. For turbine discs, stress relaxation may be occurred. So, analysis for creep-fatigue damage plays an important role in the life prediction of turbine discs. In this paper, a convenient method for creep-fatigue life estimate method of a disk was proposed with the influence of stress relaxation, based on linear damage accumulation rule. Finally, a numerical example was given to demonstrate the efficiency and accuracy of the method.
出处
《科学技术与工程》
2008年第6期1496-1500,共5页
Science Technology and Engineering
关键词
涡轮盘
失效模式
应力松弛
蠕变-疲劳寿命
线性损伤累积理论
turbine disc failure mechanisms stress relaxation creep-fatigue life linear damage accumulation rule
