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| Finite element simulation for the growth of the sealing labyrinth crack in turbine disc |
| REN Yuan1, ZHANG Cheng-cheng1, GAO Jing-yun1, LI Meng-guang2 |
1. Shanghai Center of Research for Commercial Aircraft Engine Engineering Techniques, AVIC (Aviation Industry Corporation of China) Commercial Aircraft Engine Co., Ltd., Shanghai 200240, China;
2. Multiangle Virtual Technology Incorporation, Shanghai 200233, China |
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Abstract In order to investigate the growth mechanism of sealing labyrinth crack, the propagation process, which started from the tooth tip and stops when the crack was about to penetrate through the labyrinth seal ring, was numerically simulated. The finite element model of the turbine disc with a sealing labyrinth crack was established using submodeling method, and the stress intensity factors along the crack front were calculated with M integral. After determining the local direction and extension distance of each node along the sealing labyrinth crack front, the new crack front was fitted with spline curve, and then self-adaption mesh generation was used for updating the finite elements in the vicinity of the crack. The results of numerical simulation indicated that the top of the root fillet could be regarded as the demarcation point between the slow crack-growth stage and the fast crack-growth stage. The sealing labyrinth crack grew with a low velocity as a penetrating crack before the demarcation point, and it began to transfer to a surface crack with a much higher average velocity after the demarcation point. The crack growth life before the demarcation point was several times longer than the life after the demarcation point. From the results of numerical simulation,it can also be concluded that both increasing the radius of root fillet and reducing the space between adjacent sealing labyrinths are helpful for resisting the growth of the sealing labyrinth crack.
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Received: 19 October 2015
Published: 28 April 2016
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涡轮盘篦齿裂纹扩展的有限元数值模拟
为了详细考察篦齿裂纹的扩展规律,对篦齿裂纹从齿尖一直扩展到即将完全穿透篦齿环的过程进行了数值模拟.含篦齿裂纹的涡轮盘有限元模型采用子模型法建立,使用M积分计算裂纹前沿的应力强度因子;在确定篦齿裂纹前沿每一节点处的局部扩展方向及距离后,通过样条曲线拟合出新裂纹前沿,并依靠自适应网格划分实现裂纹区有限元网格的更新.数值模拟结果表明,篦齿根部过渡圆角顶部可以视为裂纹缓慢扩展阶段与快速扩展阶段的分界点,在此之前篦齿裂纹以穿透型裂纹的形态以较低的速度进行扩展,在此之后篦齿裂纹开始向表面裂纹进行转化,并且平均扩展速度大大增加,分界点前的裂纹扩展寿命是之后的数倍.此外,由数值模拟结果还可以发现,增大篦齿根部过渡圆角半径以及减小相邻篦齿的间距,均有助于延缓篦齿裂纹的扩展.
关键词：
篦齿裂纹,
涡轮盘,
裂纹扩展,
应力强度因子,
疲劳寿命
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