某型发动机一级风扇机匣包容性数值仿真

何庆; 宣海军; 刘璐璐

某型发动机一级风扇机匣包容性数值仿真

浙江大学化工机械研究所高速旋转机械实验室, 杭州 310027

基金项目: 航空推进技术验证计划(1104-03); 浙江省自然科学基金(Y1090245)

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出版历程
- 收稿日期: 2011-03-17
- 修回日期: 2011-07-22
- 刊出日期: 2012-02-28

Numerical analysis of real aero-engine first-stage fan blade containment

High-speed Rotating Machinery Laboratory, Institute of Chemical Machinery, Zhejiang University, Hangzhou 310027, China

摘要

摘要: 为研究航空发动机机匣/叶片包容性过程机理,以某型发动机一级风扇机匣/叶片为对象,建立了三种有限元模型,研究了最高工作转速下的非包容过程,分析了完整叶片等对非包容过程的影响.结果表明:该型发动机一级风扇机匣是非包容的;机匣初始裂纹的主要失效模式为双向拉伸应力下的拉伸失效,随后裂纹扩展产生大范围的撕裂;断叶受较复杂载荷的作用,最终在凸肩处断裂成二部分;断叶与机匣的撞击过程可分成三个阶段,第一次撞击为叶尖与机匣的轻微撞击,第二次撞击作用力最大,而第三次撞击受断叶后侧完整叶片的作用非常明显.受完整叶片的撞击,断叶动能有明显的增加.
- 航空发动机 /
- 风扇机匣 /
- 叶片包容 /
- 数值模拟 /
- 非包容
Abstract: To study the mechanism of the aero-engine fan blade containment process at the maximum operating speed and the effects of multiple blade interaction on it, several numerical simulations with three different computational models based on the real aero-engine first-stage fan component were carried out. Results show that uncontained failure is observed under the impact of the released blade. Initial cracks on the casing are caused by biaxial tensile stresses, and large-scale tearing is likely to arise along the initial cracks. The released blade suffers from complicated force and is torn into two parts. There are three major impacts during the containment process. The first impact is the interaction between the blade tip and the casing, which is slight and lasts for a short time. The impact force reaches maximum during the second impact. The influences of the remaining rotating blades afterward are noticeable during the third impact. Under the impact of the remaining rotating blades, the increase of the kinetic energy of the released blade is obvious.
- aero-engine /
- fan case /
- blade containment /
- numerical simulation /
- uncontained

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