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综合运用显、隐式有限元算法对航空发动机叶片进气边受不同形状外物的撞击进行数值分析,在Ansys/LS-DYNA中进行不同形状外物撞击的瞬态显式分析,然后通过显—隐式算法的转换,获得受不同形状的外物撞击后叶片中的残余应力场分布。结果表明,外物的形状对叶片所受的损伤是有影响的,外物撞击部位的形状越尖锐,撞击叶片后叶片中分布的最大残余拉应力值越大,导致叶片的抗疲劳强度受削弱较大;几何外形相近的外物撞击后,叶片中的残余应力场分布趋势相近。
The explicit and implicit finite element method was used to analyze the impact of the aeronautic engine blades on the foreign objects of different shapes by numerical simulation. Transient explicit analysis of the shocks of different shapes on Ansys / LS-DYNA was performed. Then, - implicit algorithm conversion, access to different shapes of foreign objects hit the blade after the residual stress field distribution. The results show that the shape of the foreign objects has an impact on the damage suffered by the leaves, and the sharper the shape of the impact point of the foreign objects, the greater the maximum residual tensile stress distributed in the blades after impacting the blades, resulting in weakened the fatigue resistance of the leaves Larger; the geometric shapes of similar foreign objects impact, the leaves of the residual stress field distribution trends similar.