航空发动机钛合金叶片喷丸强化残余应力研究

发布时间：2018-03-20 08:19

本文选题：钛合金　切入点：风扇叶片　出处：《表面技术》2016年04期 　论文类型：期刊论文

【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。
[Abstract]:Objective to study the residual stress field of titanium alloy blade of aero-engine, to master the distribution of residual stress after shot peening and after application, and to provide the basis for evaluating the safety and reliability of blade. Methods the surface residual stress field of aero-engine titanium alloy fan blade and compressor blade after shot peening was measured and studied by X-ray diffraction. The distribution of residual stress along the layer depth after peening and the law of residual stress attenuation after use. Results the residual stress of fan blade after shot peening was distributed in -600 ~ 800MPa, with the mean residual stress of -682MPa, and the residual stress of compressor blade was 90%. The residual stress of the fan blade and compressor blade after shot peening is about -610 MPA, and there is a maximum residual compressive stress at 11 渭 m and 13 渭 m in the subsurface layer. The residual compressive stress decreased gradually with the increase of depth. The stress distribution of fan blade was -460 ~ 720MPa after using 300h, and that of compressor blade was -430- 700MPa after using 600h. The stress distribution of compressor blade was -430- 700MPa after using 300h. The stress distribution at -360 ~ 620 MPa after 600 h use of -470 ~ 670 MPa. Conclusion the residual compressive stress on the surface of titanium alloy blade is relatively uniform after shot peening. After shot peening, the residual compressive stress of titanium alloy blade first increases and then decreases with the increase of layer depth, and the depth of residual stress field is about 50 渭 m. The attenuation of residual compressive stress increases gradually.
【作者单位】：西安航空动力股份有限公司;
【分类号】：V263

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