Volume 32 Issue 1
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Effect of holeexpansion on hightemperature fatigue property of GH4169 superalloy hole structure[J]. Journal of Aerospace Power, 2017, 32(1): 89-95. doi: 10.13224/j.cnki.jasp.2017.01.013
Citation: Effect of holeexpansion on hightemperature fatigue property of GH4169 superalloy hole structure[J]. Journal of Aerospace Power, 2017, 32(1): 89-95. doi: 10.13224/j.cnki.jasp.2017.01.013
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Effect of holeexpansion on hightemperature fatigue property of GH4169 superalloy hole structure

doi: 10.13224/j.cnki.jasp.2017.01.013
  • Received Date: 2015-08-12
  • Publish Date: 2017-01-28
    Abstract
  • Fatigue specimen with central hole was designed based on the bolthole of a high pressure compressor disk. Of the asreceived (AR) specimens and after holeexpansion (HE), the surface profile and fatigue property in multiple alternating loads were characterized; moreover, failure analysis and the evolution of HE residual stress profile during fatigue cycle were investigated. Results showed that, after HE, the roughness of hole wall decreased, besides, the high temperature fatigue performances improved 1-3 times under multiple large load condition with the slight rise of fatigue data dispersion. The HE residual stress released to 60% during 20000 cycles at the maximum tensile stress of 663MPa,temperature of 600℃ and stress ratio of 01. Compared with the untreated specimens nucleating at machining marks, the HE crack initiated at metal accumulation by HE in the chamfer, presenting single source crack initiations.

     

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    • References(16)
  • [1]
    杨伟,徐伟.BR700系列发动机高压压气机设计及结构特征［J］.燃气涡轮试验与研究,2014,27(3):30-34. YANG Wei,XU Wei.HPC design and structure features of BR700 series engine［J］.Gas Turbine Experiment and Research,2014,27(3):30-34.(in Chinese)
    [2]
    陈光.CFM56系列发动机结构设计与研制特点［M］.北京:北京航空航天大学出版社,2006.
    [3]
    郑旭东,蔚夺魁.某发动机高压压气机篦齿盘均压孔孔边裂纹故障分析［J］.航空发动机,2013,39(3):49-54. ZHENG Xudong,YU Duokui.Study of vent hole crack failure for an aeroengine labyrinth seal disk［J］.Aeroengine,2013,39(3):49-54.(in Chinese)
    [4]
    刘庆瑞,刘玉萍.发动机第四级压气机盘裂纹失效分析［J］.航空发动机,1999(2):38-41. LIU Qingrui,LIU Yuping.Crack failure analysis of the 4th engine compressor disk［J］.Aeroengine,1999(2):38-41.(in Chinese)
    [5]
    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，2008. TAO Chunhu,ZHONG Peidao,WANG Renzhi,et al.Failure analysis and prevention for rotor in aeroengine［M］.信息不全，是否应该是期刊论文？(in Chinese)
    [6]
    李伟,董立伟,蔡向晖，等.某型发动机涡轮盘销钉孔结构分析与寿命评估［J］.航空动力学报,2009,24(8):1699-1706. LI Wei,DONG Liwei,CAI Xianghui,et al.Structure analysis and life evaluation of the pin holes in a turbine disc of a type of aeroengine［J］.Journal of Aerospace Power，2009，24(8):1699-1706.(in Chinese)
    [7]
    陈秋任,郭海丁,刘小刚.涡轮盘双轴对称异形孔结构建模与优化［J］.航空动力学报,2013,28(6):1250-1255. CHEN Qiuren,GUO Haiding,LIU Xiaogang.Modeling and optimization for the structure of biaxial symmetry noncircular hole of turbine disk［J］.Journal of Aerospace Power,2013,28(6):1250-1255.(in Chinese)
    [8]
    魏昕.镍基高温合金工件异形孔加工工艺的研究［J］.工具技术,2000,36(6):19-23. WEI Xin.Study on machining process of shaped hole in Nibase superheatresistant alloy work pieces［J］.Tool Engineering,2002,36(6):19-23.(in Chinese)
    [9]
    宋颖刚,王欣,王强.7050铝合金表面喷丸强化层内纳米结构微观组织结构分析［J］.电子显微学报,2015,34(1):18-24. SONG Yinggang,WANG Xin,WANG Qiang.Microstructures of nanocrystalline surface layer of 7050 aluminum alloy［J］.Journal of Chinese Electron Microscopy Society,2015,34(1):18-24.(in Chinese)
    [10]
    宋颖刚,高玉魁,陆峰，等.TC21钛合金喷丸强化层微观组织结构及性能变化［J］.航空材料学报,2010,30(2):40-44. SONG Yinggang,GAO Yukui,LU Feng,et al.Evolution of microstructure and properties of surface layer after shot peening TC21 titanium alloy［J］.Journal of Aeronautical Materials,2010,30(2):40-44.(in Chinese)
    [11]
    秦银雷,魏大盛,王延荣.航空发动机涡轮盘裂纹扩展分析［J］.航空发动机,2010,36(2):34-37. QIN Yinlei,WEI Dasheng,WANG Yanrong.Analysis of crack propagation for aeroengine turbine disk［J］.Aeroengine,2010,36(2):34-37.(in Chinese)
    [12]
    Smith R A,Miller K J.Prediction of fatigue regimes in notched components［J］.International Journal of Mechanical Science,1978,20(4):201-206.
    [13]
    Li J K,Yao M,Wang D,et al.An analysis of stress concentrations caused by shot peening and its application in predicting fatigue strength［J］.Fatigue Fracture and Engineering Material Structure，1992,15(12):1271-1279.
    [14]
    李金魁,姚枚,王仁智,等.喷丸强化的综合效应理论［J］.航空学报,1992,13(11):670-677. LI Jinkui,YAO Mei,WANG Renzhi,et al.Comprehensive effects theory for shot peening strengthening［J］.Acta Aeronautica et Astronautica Sinica,1992,13(11):670677.(in Chinese)
    [15]
    Prevey P S,Telesman J,Gabb T,et al.FOD resistance and fatigue crack arrese in low plasticity burnished IN718［R］.Chandler,AZ:The 5th National Turbine Engine High Cycle Fatigue Conference,2000.
    [16]
    胡奈赛,徐可为,方刚.喷丸件的残余应力松弛与位错亚结构变化［J］.中国表面工程,1992(1):24-28. HU Naisai,XU Kewei,FANG Gang.Residual stress relieving and evolution of dislocation［J］.China Surface Engineering,1992(1):2428.(in Chinese)
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