表面技术2016，Vol.45Issue(4)：208-212,5.DOI:10.16490/j.cnki.issn.1001-3660.2016.04.035
航空发动机钛合金叶片喷丸强化残余应力研究
Shot-peened Residual Stress of Aeroengine Titanium Alloy Blades
张彩珍 1杨健 1魏磊 1李跃辉 1吕建勋 1陈林洪1
作者信息
- 1. 西安航空动力股份有限公司,西安710021
- 折叠
摘要
Abstract
Objective The residual stress field of aeroengine titanium alloy blades was studied, and the residual stress distribu-tion of blades after shot peening and after use was mastered, in order to provide a basis for evaluating the safety and reliability of the blades, and to provide data support for predicting the residual life of the blades. Methods The surface residual stress field after shot peening, the residual stress distribution along the deep layer, and the residual stress of aeroengine fan blades and compressor blades after use were studied using X-ray diffraction technology. Results After shot peening, about 90% of residual stress of the fan blades was distributed in the range of -600~-800 MPa, and the average residual stress value was about -682 MPa. About 90% of residual stress distribution of the compressor blades was distributed in the range of-500~-700 MPa, and the average re-sidual stress was about -603 MPa. After shot peening, the surface residual stress of the fan blade and compressor blade was about-610 MPa, and there was a maximum residual stress in the subsurface layer, the values were-739 MPa at 11μm and-683 MPa at 13μm, respectively, and then the residual stress decreased gradually with increasing depth. The residual stress distribution of the fan blades was-460~-720 MPa after using for 300 hours, and-430~-700 MPa after using for 600 hours. The residual stress distribu-tion of the compressor blades was-470~-670 MPa after using for 300 hours, and-360~-620 MPa after using for 600 hours. Con-clusion The residual compressive stress of Titanium alloy blade after shot peening first decreased and then increased with the increase of the layer depth, and the depth of the residual stress field was about 50 μm. The residual stress of titanium alloy blade after use showed an attenuation trend, and the residual compressive stress attenuation increased gradually with the increase of using time.关键词
钛合金/风扇叶片/压气机叶片/残余应力/X射线衍射分析/喷丸Key words
titanium alloy/fan blade/compressor blade/residual stress/X-ray diffraction analysis/shot peening分类
矿业与冶金引用本文复制引用
张彩珍,杨健,魏磊,李跃辉,吕建勋,陈林洪..航空发动机钛合金叶片喷丸强化残余应力研究[J].表面技术,2016,45(4):208-212,5.
