|
|
论文:2020,Vol:38,Issue(6):1291-1298 |
|
|
引用本文： |
|
|
吴英龙, 宣海军. 高温合金盘多源疲劳裂纹萌生及扩展特征[J]. 西北工业大学学报 |
|
|
WU Yinglong, XUAN Haijun. Initiation and Propagation Characteristics of Multi-Source Fatigue Crack in Superalloy Disk[J]. Northwestern polytechnical university |
|
|
|
|
|
|
|
| 高温合金盘多源疲劳裂纹萌生及扩展特征 |
|
| 吴英龙1,2, 宣海军1 |
|
1. 浙江大学 能源工程学院, 浙江 杭州 310027;
2. 温州大学 机电工程学院, 浙江 温州 325035 |
| 摘要: |
| 通过高速旋转低周疲劳实验及断口分析、裂纹扩展仿真分析，研究了某涡轮盘多源疲劳裂纹扩展特征。结果显示高温合金盘及其模拟件的疲劳萌生寿命N0分散性较小且相近；直接采用材料的S-N0曲线预测轮盘N0时偏不保守。轮盘偏心孔断口均为多源疲劳断口；裂纹表面特征L/d从7.5快速减小至2，明显不同于单源疲劳裂纹扩展。由于偏心孔处应力分布细长、GH698裂纹萌生寿命分散性小，偏心孔A面各处各自萌生裂纹相对容易，易出现多源疲劳。a≥1.23 mm阶段，2＃、5＃偏心孔裂纹扩展断口反推寿命变化较一致，单源疲劳裂纹扩展寿命仿真值与之误差在5％以内。0.61 mm≤a<1.23 mm阶段，5＃偏心孔多源裂纹扩展速率仿真值与断口反推值接近。准确的多源裂纹扩展仿真分析不仅需要准确定义初始裂纹，同时还需考虑各处已有的疲劳损伤对裂纹扩展的影响。 |
| 关键词:
高温合金
涡轮盘
低周疲劳
损伤容限
多源起裂
|
|
| Initiation and Propagation Characteristics of Multi-Source Fatigue Crack in Superalloy Disk |
|
| WU Yinglong1,2, XUAN Haijun1 |
|
1. College of Energy Engineering, Zhejiang University, Hangzhou 310027, China;
2. College of Mechanical and Electrical Engineering, Wenzhou University, Wenzhou 325035, China |
| Abstract: |
| The multi-source fatigue crack growth characteristics of a turbine disk were studied via high-speed rotating low cycle fatigue test, fracture analysis and crack growth simulation analysis. The results show that the fatigue initiation life N0 of Superalloy disk and its simulation parts is less dispersive and similar, and the S-N0 curve of the material is not conservative to predict the N0 of the disk. The fracture of eccentric hole of disk is multi-source fatigue fracture, and the surface characteristic of the crack L/D decreases rapidly from 7.5 to 2, which is obviously different from the single source fatigue crack growth. Because of the long and thin stress distribution at the eccentric hole and the small dispersivity of GH698 crack initiation life, it's relatively easy to crack on the plane A of the eccentric hole, which is prone to multi-source fatigue. At the stage of a ≥ 1.23 mm, the reverse life of crack propagation fracture of 2# and 5# eccentric holes is consistent, and the error between the simulation value of single source fatigue crack propagation life and the reverse life is below 5%. In the stage of 0.61 mm ≤ a<1.23 mm, the simulation crack growth rate of 5# eccentric hole of multi-source is close to that of fracture inversion. Accurate simulation analysis of multi-source crack growth needs to define the initial crack accurately, at the same time, consider the influence of existing fatigue damage on crack growth. |
| Key words:
superalloy
turbine disk
LCF
damage tolerance
multi-source initiation
|
|
| 收稿日期: 2020-02-12
修回日期:
|
| DOI: 10.1051/jnwpu/20203861291 |
| 基金项目: 国家科技重大专项（2017-IV-0012-0049）资助 |
| 通讯作者:
Email： |
| 作者简介: 吴英龙(1984-),浙江大学博士后,主要从事损伤容限分析研究。
|
|
|
|
|
|
|
|
参考文献: |
|
|
[1] 陶春虎, 钟培道, 王仁智, 等. 航空发动机转动部件的失效与预防[M]. 北京:国防工业出版社, 2000 TAO Chunhu, ZHONG Peidao, WANG Renzhi, et al. Failure and Prevention of Aero-Engine Rotating Component[M]. Beijing:National Defense Industry Press, 2000(in Chinese)
[2] 陈光. 涡轮盘中隐藏多年的瑕疵导致波音767烧毁[J]. 航空动力,2019(6):56-58 CHEN Guang. A Hidden Defect in the Turbine Disk Result in a Boeing 767 Burned[J]. Aerospace Power, 2019(6):56-58(in Chinese)
[3] PHILLIPS P J, UNOCIC R R, MILLS M J. Low Cycle Fatigue of a Polycrystalline Ni-Based Superalloy:Deformation Substructure Analysis[J]. International Journal of Fatigue, 2013, 57:50-57
[4] ABIKCHI M, BILLOT T, CRÉPIN J, et al. Fatigue Life and Initiation Mechanisms in Wrought Inconel 718 DA for Different Microstructures[C]//13th International Conference on Fracture, Beijing, China, 2013
[5] SWEENEY C A, VORSTER W, LEEN S B, et al. The Role of Elastic Anisotropy, Length Scale and Crystallographic Slip in Fatigue Crack Nucleation[J]. Journal of the Mechanics and Physics of Solids, 2013, 61(5):1224-1240
[6] 秦鹤勇,陈刚,沈文涛,等. GH4698合金高温低周疲劳性能分析[J]. 锻压装备与制造技术, 2014, 49(6):92-96 QIN Heyong, CHEN Gang, SHEN Wentao, et al. Analysis of High Temperature Low Cycle Fatigue Properties for GH4698 Alloy[J]. Metal Forming Equipment and Manufacturing Technology, 2014, 49(6):92-96(in Chinese)
[7] SWEENEY C A, O'BRIEN B, DUNNE F P E, et al. Strain-Gradient Modelling of Grain Size Effects on Fatigue of CoCr Alloy[J]. Acta Materialia, 2014, 78:341-353
[8] 王欢,袁超,郭建亭,等. GH4698合金的疲劳裂纹扩展行为[J]. 中国有色金属学报,2015,25(1):23-29 WANG Huan, YUAN Chao, GUO Jianting, et al. Fatigue Crack Propagation Behavior of GH4698 Alloy[J]. Chinese Journal of Nonferrous Metals, 2015, 25(1):23-29(in Chinese)
[9] 郑小梅,孙燕涛,杨兴宇,等. 某涡扇发动机高压涡轮盘螺栓孔低循环疲劳模拟件设计[J]. 航空动力学报, 2018, 33(10):2351-2358 ZHENG Xiaomei, SUN Yantao, YANG Xingyu, et al. Design of Low Cycle Fatigue Simulating Specimen for Bolt Holes of a Turbofan Engine High Pressure Turbine Disc[J]. Journal of Aerospace Power, 2018, 33(10):2351-2358(in Chinese)
[10] 侯俊玲,李群,左宏. 基于M-积分的镍基合金多裂纹扩展研究[C]//2018年全国固体力学学术会议, 哈尔滨, 2018 HOU Junling, LI Qun, ZUO Hong. Multiple Crack Growth of Nickel Base Alloy Based on M-Integral[C]//2018 National Conference on Solid Mechanics, Harbin, 2018(in Chinese)
[11] 朱强. GH4698镍基合金高温低周疲劳行为及断裂机理[D]. 哈尔滨:哈尔滨工业大学, 2016 ZHU Qiang. High Temperature Low Cycle Fatigue Behavior and Fracture Mechanism of GH4698 Nickel-Based Alloy[D]. Harbin:Harbin Institute of Technology, 2016(in Chinese)
[12] 刘红彬,陈伟,刘林. 某轮盘螺栓孔处疲劳寿命预测方法与验证[J]. 西北工业大学学报, 2019, 37(4):744-750 LIU Hongbin, CHEN Wei, LIU Lin. Prediction Method and Verification of Fatigue Life for a Turbine Disk with Bolt Hole[J]. Journal of Northwestern Polytechnical University, 2019, 37(4):744-750(in Chinese)
[13] 赵荣国. 航空发动机涡轮盘用GH4133B合金疲劳裂纹扩展行为研究[J]. 机械工程学报, 2011,47(18):55-65 ZHAO Rongguo. Probabilistic Fatigue Crack Propagation Life Prediction of GH4133B Superalloy Used in Turbine Disk of Aero-Engine[J]. Journal of Mechanical Engineering, 2011,47(18):55-65(in Chinese)
[14] CLÁUDIO R A, BAPTISTA R, INFANTE V, et al. Life Prediction Using Finite Elements in Complex Geometries[C]//Eighth Portuguese Conference on Fracture, 2002
[15] BERES W, Dudzinski D, Murzionak A. Fatigue Crack Growth Rate Evaluation in a Turbine Disc after Spin Rig Testing[C]//12th International Conference on Fracture, Ottawa, 2009
[16] DAS P S. Three-Dimensional Structural Evaluation of a Gas Turbine Engine Rotor[C]//ASME Turbo Expo 2014:Turbine Technical Conference and Exposition, Germany, 2014:16-20
[17] 陆山,黄其青. 涡轮盘销钉孔损伤容限分析新方法及其应用[J]. 航空动力学报,2002,17(1):87-92 LU Shan, HUANG Qiqing. New Method and Application of Damage Tolerance Analysis of Pin Holes in Turbine Disks[J]. Journal of Aerospace Power, 2002,17(1):87-92(in Chinese)
[18] 刘成立,吕震宙,徐有良. 粉末冶金涡轮盘裂纹扩展可靠性分析方法[J]. 稀有金属材料与工程, 2006, 35(2):232-236 LIU Chengli, LYU Zhenzou, XU Youliang. Reliability Analysis for the Crack Growth of Powder Metallurgy Turbine Disk[J]. Rare Metal Materials and Engineering, 2006, 35(2):232-236(in Chinese)
[19] 陶春虎,习年生,张卫方, 等. 断口反推疲劳应力的新进展[J]. 航空材料学报, 2000,30(3):158-163 TAO Chunhu, XI Niansheng, ZHANG Weifang. Resent Development of Fractographic Restrostimationon Determining Fatigue Stress[J]. Journal of Aeronautical Materlals, 2000,30(3):158-163(in Chinese)
[20] HUTCHINSON J W. Crack Tip Shielding by Microcracking in Brittle Solids[J]. Aeta Metall, 1987, 35:1605-1619 |
|
|
|
相关文献: |
|
|
1．肖阳, 秦海勤, 徐可君, 王永旗.不同保载时间下FGH96粉末高温合金疲劳-蠕变试验研究[J]. 西北工业大学学报, 2020,38(4): 873-880 |
|
|
|
|
|
|
