Volume 26 Issue 9
Sep.  2011
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2011  >  26(9): 2044-2048
CHEN Ai-jun, CHEN Cheng, ZHANG Ding-guo, LIAO Lian-fang. Fracture mechanics analysis for rotating blade model of aero-engine[J]. Journal of Aerospace Power, 2011, 26(9): 2044-2048.
Citation: CHEN Ai-jun, CHEN Cheng, ZHANG Ding-guo, LIAO Lian-fang. Fracture mechanics analysis for rotating blade model of aero-engine[J]. Journal of Aerospace Power, 2011, 26(9): 2044-2048.
shu

Fracture mechanics analysis for rotating blade model of aero-engine

  • 1.

    School of Sciences, Nanjing University of Science and Technology, Nanjing 210094, China

  • 2.

    Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

  • Received Date: 2010-10-07
  • Rev Recd Date: 2011-01-22
  • Publish Date: 2011-09-28
    Abstract
  • An analysis model for the cracked plate of blade was established using fracture mechanics method.Firstly,the weight function for blade containing a single edge crack was derived from one reference stress intensity factor under uniform load.Secondly,the stress intensity factor at the tip of crack of rotating blade was calculated using weight function method.Finally,critical rotate speed of blade was inferred on the basis of fracture criterion.The analysis of examples shows that the depth and position of crack in blade have much influence on the stress intensity factor and critical rotating speed.

     

    • FullText(HTML)
  • loading
    • References(12)
  • [1]
    Frankenberger C E.FAA T53-L-13L turbine fragment containment test .DOT/FAA/AR-98/22,1998.
    [2]
    Sarkar S,Atluri S N.Effects of multiple blade interaction on the containment of blade fragments during a rotor failure[J].Finite Element in Analysis and Design,1996,23(2-4):211-223.
    [3]
    Kraus A,Frischbier J.Containment and penetration simulation in case of blade loss in a low pressure turbine . Bad Mergentheim,Germany:DYNAmore LS-DYNA Forum,2002.
    [4]
    Carney K,Pereira M,Revilock D,et al.Jet engine fan blade containment using two alternate geometries .ULM,Germany:4th European LS-DYNA Users Conference,2003.
    [5]
    宣海军,洪伟荣,吴荣仁.航空发动机涡轮叶片包容试验及数值模拟[J].航空动力学报,2005,20(5):762-767. XUAN Haijun,HONG Weirong,WU Rongren.Aero-engine turbine blade containment tests and numerical simulation [J].Journal of Aerospace Power,2005,20(5):762-767. (in Chinese)
    [6]
    于亚彬,陈伟.模型机匣/叶片包容性数值分析[J].航空动力学报,2005,20(3):429-433. YU Yabin,CHEN Wei.Numerical analysis of the modeled blade/casing containment[J].Journal of Aerospace Power, 2005,20(3):429-433.(in Chinese)
    [7]
    曹俊俊,陈爱军,章定国,等.双层模型机匣和叶片的包容性问题数值模拟[J].航空计算技术,2009,39(6):33-36. CAO Junjun,CHEN Aijun,ZHANG Dingguo,et al.Numerical simulation of the double-layered aero-engine case and blade containment[J].Aeronautical Computing Technique,2009,39(6):33-36.(in Chinese)
    [8]
    范志强,高德平,姜涛,等.模型机匣的包容性试验和数值模拟[J].南京航空航天大学学报,2006,38(5):551-556. FAN Zhiqiang,GAO Deping,JIANG Tao,et al.Experimental study and numerical simulation of model casing containment[J].Journal of Nanjing University of Aeronautics and Astronautics,2006, 38(5):551-556.(in Chinese)
    [9]
    Rice J R.Some remarks on elastic crack-tip stress fields[J].Int.Journal Solids Structures,1972,8(6):751-758.
    [10]
    Petroski H J,Achenbach J D.Computation of the weight function from a stress intensity factor[J].Engineering Fracture Mechanics,1978,10(2):257-266.
    [11]
    丁遂栋.断裂力学[M].北京:机械工业出版社,1997.
    [12]
    刘鸿文.材料力学[M].北京:高等教育出版社,2004.
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(872.0KB)
    XML

    Article Metrics

    Article views (2187) PDF downloads(12) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return