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  • ISSN：0577-6686
机械工程学报

机械工程学报 ›› 2015, Vol. 51 ›› Issue (18): 71-82.doi: 10.3901/JME.2015.18.071

• 材料科学与工程 • 上一篇    下一篇

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航空发动机涡轮盘用GH4133B合金疲劳裂纹扩展寿命概率预测

赵荣国1, 刘亚风1, 蒋永洲2, 李其棒1, 言怡1, 刘学晖3   

  1. 湘潭大学土木工程与力学学院 湘潭 411105；空军航空大学航空理论系 长春 130022；中国航空工业集团黎阳航空发动机公司 安顺 561102
  • 出版日期:2015-09-15 发布日期:2015-09-15
  • 基金资助:
    湖南省教育厅重点资助项目(14A144)

Probabilistic Fatigue Crack Propagation Life Prediction of GH4133B Superalloy Used in Turbine Disk of Aero-engine

ZHAO Rongguo1, LIU Yafeng1, JIANG Yongzhou2, LI Qibang1, YAN Yi1, LIU Xuehui3   

  1. College of Civil Engineering and Mechanics, Xiangtan University, Xiangtan 411105; Department of Aviation Theory, Air Force Aviation University, Changchun 130022;Liyang Aero-Engine Corporation, Aviation Industry Corporation of China, Anshun 561102
  • Online:2015-09-15 Published:2015-09-15

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摘要： 镍基高温合金的概率寿命预测要求模拟多种复杂随机现象。针对室温下航空发动机涡轮盘用GH4133B合金的疲劳裂纹扩展试验数据，采用Paris公式和含门槛值Kth的修正Paris公式，对不同应力比下的疲劳裂纹扩展速率进行概率预测。基于Paris公式和修正Paris公式的积分式计算不同存活概率P下的理论疲劳剩余寿命Nfp，并与试验疲劳剩余寿命Nft对比。结果表明，当P=50%时，基于修正Paris公式的Nfp与Nft吻合；当P=90%时，基于Paris公式和修正Paris公式的Nfp均与Nft吻合；当P=99%时，基于修正Paris公式的Nfp具有高可靠度。基于疲劳寿命试验数据的非线性回归分析绘制Nf-Fp,m-Fp,a曲面，引入参量表征平均载荷Fp,m和载荷幅值Fp,a对疲劳寿命Nf的影响，结果表明，在所研究的应力比范围内Fp,m对Nf影响大。

关键词: 概率, 疲劳裂纹扩展, 寿命预测, 涡轮盘, 应力比

Abstract: Probabilistic life prediction of nickel-base superalloy requires the modelling multiple complex random phenomena. The fatigue crack growth rates at various stress ratios are probabilistically predicted using the Paris formula and the modified Paris formula with threshold value Kth for fatigue crack growth test data of GH4133B superalloy used in turbine disk of aero-engine at room temperature. The theoretic fatigue crack growth lives Nfp at various survival probabilities P predicted by integral based on the Paris formula and the modified Paris formula are calculated and compared with the test ones Nft. It is shown that Nfp obtained by integral based on the modified Paris formula is well fitted with Nft at P=50%, while both Nfp obtained by integral based on the Paris formula and that obtained by integral based on the modified Paris formula are all well fitted with Nft at P=90%, and Nfp obtained by integral based on the modified Paris formula possesses a high reliability at P=99%. A 3D Nf-Fp,m-Fp,a fatigue life surface are plotted based on the nonlinear regression analysis of fatigue life test data, and a parameter  is introduced to characterize the effect of mean load Fp,m and load amplitude Fp,a on fatigue life Nf. It is suggested that the effect of Fp,m on Nf is larger than that of Fp,a on Nf.

Key words: fatigue crack propagation, life prediction, probability, stress ratio, turbine disk

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