摘要
目的研究航空发动机钛合金叶片残余应力场,掌握叶片喷丸后和使用后的残余应力分布规律,为评估叶片的安全性和可靠性提供依据,为预测叶片剩余寿命提供数据支持。方法利用X射线衍射技术测试并研究航空发动机钛合金风扇叶片和压气机叶片喷丸后表面残余应力场、喷丸后残余应力沿层深的分布规律和使用后的残余应力衰减规律。结果喷丸后风扇叶片残余应力的90%分布在-600^-800 MPa,其残余应力均值为-682 MPa;压气机叶片残余应力的90%分布在-500^-700 MPa,其残余应力均值为-603 MPa。喷丸后风扇叶片和压气机叶片的表面残余应力约为-610 MPa,在次表面层11μm和13μm处存在一个最大残余压应力,分别为-739 MPa和-683 MPa,随后残余压应力随着深度的增加而逐渐减小。风扇叶片使用300 h后应力分布在-460^-720 MPa,使用600 h后应力分布在-430^-700MPa;压气机叶片使用300 h后应力分布在-470^-670 MPa,使用600 h后应力分布在-360^-620 MPa。结论喷丸后钛合金叶片表面存在较大的残余压应力且分布较为均匀;喷丸后钛合金叶片残余压应力随层深的增加先增大后减小,残余应力场深度约为50μm;使用后的钛合金叶片残余应力有衰减趋势,而且随着使用时间的增加,残余压应力衰减量逐渐增加。
Objective The residual stress field of aeroengine titanium alloy blades was studied,and the residual stress distribution 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. About90% of residual stress distribution of the compressor blades was distributed in the range of-500 --700 MPa,and the average residual 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 at13 μm,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 distribution of the compressor blades was-470 --670 MPa after using for 300 hours,and-360 --620 MPa after using for 600 hours. Conclusion 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.
出处
《表面技术》
EI
CAS
CSCD
北大核心
2016年第4期208-212,共5页
Surface Technology
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
titanium alloy
fan blade
compressor blade
residual stress
X-ray diffraction analysis
shot peening
