基于断口分析的钛合金轮内部缺陷损伤容限

吴英龙; 宣海军; 单晓明

doi:10.13224/j.cnki.jasp.2020.02.015

基于断口分析的钛合金轮内部缺陷损伤容限

doi: 10.13224/j.cnki.jasp.2020.02.015

基金项目: 民机专项研究项目(MJ-2014-D-19)

计量
- 文章访问数: 441
- HTML浏览量: 1
- PDF量: 474
- 被引次数: 0
出版历程
- 收稿日期: 2019-09-30
- 刊出日期: 2020-02-28

Damage tolerance of titainum alloy wheel with internal defects based on fracture analysis

1.
School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,China
2.
High-speed Rotating Machinery Laboratory,College of Energy Engineering,Zhejiang University,Hangzhou 310027,China
3.
.Hunan Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China

摘要

摘要: 为进行某轮损伤容限设计,开展了裂纹扩展断口分析和仿真分析研究。由断口分析可知:疲劳源为一处内部自然缺陷;依据疲劳辉纹确定了裂纹扩展速率;在裂纹长度为2 mm附近,裂纹扩展速率明显增大,为第一、第二加载阶段转换区域;裂纹稳定扩展区裂纹长度与裂纹扩展速率呈双对数线性关系;应用列表梯度法和Paris公式法反推了第二加载阶段的疲劳寿命,与该阶段实际循环次数的最大误差是163%。裂纹稳定扩展阶段裂纹扩展仿真值与断口反推值吻合;非稳定扩展阶段仿真值与断口反推值的最大误差为-215%;基于以上研究,合理确定了某离心轮内部裂纹表面扩展停机检测周期。该类轮非稳定、失稳扩展阶段寿命占内部裂纹表面扩展阶段寿命的比例达248%~357%,因此准确计算具有重要意义。
- 损伤容限 /
- 内部缺陷 /
- 钛合金轮 /
- 断口分析 /
- 裂纹扩展
Abstract: In order to carry out the damage tolerance design of wheel, the crack propagation characteristics were studied by fractographic restrostimation and crack propagation simulation analysis. The crack growth rate was determined according to the fatigue striation. Close to crack length of 2 mm, the crack growth rate increased significantly, acting as the transition region of the first and second loading stages; in the stable crack growth zone, crack length had a bilinear logarithmic relationship with the crack growth rate; the list gradient method and Paris formula method were used to reversely calculate the fatigue life, and the fatigue life was 163% higher than the cycles of the second loading stage. The simulated values of crack growth in the stable stage of crack propagation coincided with the values of fracture inversion, but the simulated values in the unstable stage were less than the values of fracture inversion, and the error was -215%. Based on the above research, a reasonable table for a centrifugal wheel was determined. The life of wheels in unstable stage accounted for 248%-357% of the life of internal crack surface growth stage, so accurate calculation was of great significance.
- damage tolerance /
- internal defects /
- titanium alloy wheel /
- fracture analysis /
- crack propagation

HTML

参考文献(18)

[1]	张利军,何春艳,薛祥义,等.钛合金冶金缺陷实例分析［J］.理化检验-物理分册,2013,49(12):819-822. ZHANG Lijun,He Chunyan,XUE Xiangyi,et al.Cases analysis on titanium alloy metallurgical defect［J］.Physical Testing and Chemical Analysis:Part A Physical Testing,2013,49(12):819-822.(in Chinese)
[2]	National Transportation Safety Board.Aircraft accident report-United Airlines Flight 232 McDonnell Douglas DC-10-10 Sioux Gateway Airport［R］.National Transportation Safety Board,NTSB/AAR-SO/06,1990.
[3]	U.S.Federal Aviation Administration.Airworthiness standards:aircraft engines:FAR33［S］.New York:Federal Aviation Administration,2009:9-11.
[4]	中国民用航空局.航空发动机适航规定:CCAR-33-R2［S］.北京:中国民用航空局,2011:34-35.
[5]	U.S.Department of Defense,Joint services specification guide engines,aircraft,turbine:JSSG-2007A［S］.New York:Department of Defense,2004:248-249.
[6]	LEVENRANT G R,MCCLUNG R C,WU Y T,et al.Turbine rotor material design［R］.Federal Aviation Administration,Department of Transportation,DOT/FAA/AR-00/64,2000.
[7]	MCCLUNG R C,LEVENRANT G R,ENRIGHT M P,et al.Turbine rotor material design:Phase Ⅱ［R］.Federal Aviation Administration,Department of Transportatio,DOT/FAA/AR-07/13,2008.
[8]	MOGILEVSKAYA S G,CROUCH S L,BALLARINIR,et al.Interaction between a crack and a circular inhomogeneity with interface stiffness and tension［J］.International Journal of Fracture,2009,159(2):191-207.
[9]	张纪奎,郦正能,邱志平,等.钛合金结构损伤容限设计可行性研究［J］.航空学报,2009,30(4):763-767. ZHANG Jikui,LI Zhengneng,QIU Zhiping,et al.Feasibility study on damage tolerance design of titanium alloys［J］.Acta Aeronautica et Astronautica Sinica,2009,30(4):763-767.(in Chinese)
[10]	张国栋,于慧臣,何玉怀,等.损伤力学方法在材料低周疲劳试验中的应用研究［J］.航空动力学报,2007,22(9):1544-1549. ZHANG Guodong,YU Huichen,HE Yuhuai,et al.Application research of damage dynamics for low cycle fatigue test［J］.Journal of Aerospace Power,2007,22(9):1544-1549.(in Chinese)
[11]	吕志阳,熊峻江,马少俊,等.4种典型航空钛合金材料高温裂纹扩展性能对比试验［J］.航空动力学报,2017,32(11):2713-2720. L Zhiyang,XIONG Junjiang,MA Shaojun,et al.Comparative experiment of high-temperature crack propagative behaviors for four kinds of typical titanium alloys［J］.Journal of Aerospace Power,2017,32(11):2713-2720.(in Chinese)
[12]	邹煜申.含硬α夹杂钛合金轮盘疲劳裂纹扩展特性研究［D］.杭州:浙江大学,2018. ZOU Yushen.Research on fatigue crack growth characteristic of titanium disk with interior hard alpha［D］.Hangzhou:Zhejiang University,2018.(in Chinese)
[13]	江有为.某GH4169涡轮盘裂纹扩展研究［D］.杭州:浙江大学,2016. JIANG Youwei.Fatigue crack growth research of a GH4169 power turbine disc［D］.Hangzhou:Zhejiang University,2016.(in Chinese)
[14]	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,et al.Resent development of fractographic restrostimationon determining fatigue stress［J］.Journal of Aeronautical Materials,2000,30(3):158-163.(in Chinese)
[15]	张卫方,陶春虎,习年生,等.断口反推疲劳应力及其在叶片断裂分析中的应用［J］.材料工程,2003(1):38-41. ZHANG Weifang,TAO Chunhu,XI Niansheng,et al.Fractography retroestimating fatigue stress and its application on blade fracture analysis in engineering［J］.Journal of Materials Engineering,2003(1):38-41.(in Chinese)
[16]	张智轩,石多奇,杨晓光.含销钉孔边裂纹的某压气机轮盘裂纹扩展分析［J］.航空动力学报,2016,31(3):567-574. ZHANG Zhixuan,SHI Duoqi,YANG Xiaoguang.Analysis of crack propagation for a compressor disk with cracks on pin holes［J］.Journal of Aerospace Power,2016,31(3):567-574.(in Chinese)
[17]	DAS P S.Three-dimensional structural evaluation of a gas turbine engine rotor［R］.Düsseldorf,Germany:ASME Turbo Expo,2014.
[18]	刘睿.钛合金动态断裂韧性测试方法及断裂行为的研究［D］.北京:北京有色金属研究总院,2010. LIU Rui.Study on the dynamic fracture toughness test method and fracture behavior of titanium alloys［D］.Beijing:General Research Institute of Nonferrous Metals,2010.(in Chinese)