Effect of holeexpansion on hightemperature fatigue property of GH4169 superalloy hole structure

王欣; 胡仁高; 胡博; 赵振业; 罗学昆; 古远兴; 宋颖刚

doi:10.13224/j.cnki.jasp.2017.01.013

Chinese

您当前的位置：

首页 >

文章列表页 >

Effect of holeexpansion on hightemperature fatigue property of GH4169 superalloy hole structure

更新时间：2026-07-07

- Effect of holeexpansion on hightemperature fatigue property of GH4169 superalloy hole structure
- Vol. 32, Issue 1, Pages: 89-95(2017)
- 作者机构：
  
  1. 中国航空发动机集团有限公司北京航空材料研究院表面工程研究所,北京,100095
  2. 中国航空发动机集团有限公司四川燃气涡轮研究院强度技术研究室,成都,610500
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.01.013
  CLC：
- Published：2017
- 稿件说明：
移动端阅览
王欣, 胡仁高, 胡博, 赵振业, 罗学昆, 古远兴, 宋颖刚. 孔挤压对于高温合金GH4169孔结构高温疲劳性能的影响[J]. 航空动力学报, 2017, 32(1): 89-95.

doi: 10.13224/j.cnki.jasp.2017.01.013
王欣, 胡仁高, 胡博, 赵振业, 罗学昆, 古远兴, 宋颖刚. 孔挤压对于高温合金GH4169孔结构高温疲劳性能的影响[J]. 航空动力学报, 2017, 32(1): 89-95. DOI： 10.13224/j.cnki.jasp.2017.01.013.

doi: 10.13224/j.cnki.jasp.2017.01.013 DOI：

摘要

根据高压压气机盘螺栓孔结构，设计中心孔板材疲劳试样.表征了孔挤压强化后的表面轮廓，分析了在多种交变载荷条件下孔挤压前后试样的疲劳寿命，并进行了断口观察和疲劳过程中孔挤压残余应力的演化分析.结果表明:孔挤压强化减小了孔壁表面粗糙度，并使孔结构在多种高温大应力条件下（825MPa/600℃、825MPa/400℃和663MPa/600℃）的高温疲劳性能提高1～3倍，但疲劳数据分散度略有增大.孔挤压残余应力在最大拉应力为663MPa，温度为600℃，应力比为01条件下20000次疲劳试验中松弛到60%.原始试样的多源疲劳断口主要起源于孔边的加工刀痕，而挤压强化试样断口起源于孔挤压在倒角区域流动金属堆积处，为单源疲劳断口.

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.

关键词

Keywords

references

Views

478

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Influence of small hole on thermal mechanical fatigue in single crystal superalloy DD6

Numerical simulation on laser shock peening of TC4 titanium alloy

Improving fatigue performance of titanium alloy simulated-blade subjected to foreign object damage by laser shock peening

Numerical analysis on residual stress of foreign object damage on the leading edge of titanium alloy blade

Numerical simulation on cold expansion strenghthening ,technology process of GH4169,

Related Author

Shibai TANG

Junjie YANG

Fulei JING

LI Dongchun

WANG Changkai

CUI Wenbin

DING Junliang

CHENG Li

Related Institution

Institute for Aero Engine，Tsinghua University

Aero Engine Academy of China，Aero Engine Corporation of China

Collaborative Innovation Center for Advanced Aero-Engines

Aeronautics Engineering College,Air Force Engineering University

Process and Technology Center, Xi'an Aero-Engine(Group) Limited Company, Aviation Industry Corporation of China

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰