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工程设计学报
工程设计学报  2016, Vol. 23 Issue (2): 152-159,165    DOI: 10.3785/j.issn.1006-754X.2016.02.008
建模、分析、优化和决策     
涡轮盘篦齿裂纹扩展的有限元数值模拟
任远1, 张成成1, 高靖云1, 李孟光2
1. 中航商用航空发动机有限责任公司 上海商用飞机发动机工程技术研究中心, 上海 200240;
2. 上海量维信息科技有限公司, 上海 200233
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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摘要： 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    
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.
Key words: sealing labyrinth crack    turbine disc    crack growth    stress intensity factor    fatigue life
收稿日期: 2015-10-19 出版日期: 2016-04-28
CLC:  V231.95  
基金资助:

上海市“引进技术消化与吸收”专项资金资助(12XI-04);上海科委科研计划项目(13DJ1400200).
作者简介: 任远(1982—),男,四川南充人,工程师,博士,从事航空发动机结构寿命与可靠性技术研究,E-mail:renyuan@acae.com.cn.http://orcid.org//0000-0001-8644-1234
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任远, 张成成, 高靖云, 李孟光. 涡轮盘篦齿裂纹扩展的有限元数值模拟[J]. 工程设计学报, 2016, 23(2): 152-159,165.

REN Yuan, ZHANG Cheng-cheng, GAO Jing-yun, LI Meng-guang. Finite element simulation for the growth of the sealing labyrinth crack in turbine disc. Chinese Journal of Engineering Design, 2016, 23(2): 152-159,165.

链接本文:

https://www.zjujournals.com/gcsjxb/CN/10.3785/j.issn.1006-754X.2016.02.008    或    https://www.zjujournals.com/gcsjxb/CN/Y2016/V23/I2/152

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