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为改善航空发动机叶片残余应力分布状态、消除喷丸对叶片表面造成的微损伤,提出了喷丸-电磁场复合调控新技术。采用X射线衍射技术分别测试了叶片残余应力在喷丸前、喷丸后和喷丸-电磁场复合调控工艺处理后的分布规律。通过叶片材料微观组织分析,探讨了喷丸-电磁场复合调控工艺影响钛合金叶片残余应力的机理。研究结果表明,喷丸-电磁场复合调控工艺使叶片表面残余压应力最大提升了7.7%,改善了喷丸造成的残余压应力分布不均匀状况,并在叶片近表层形成了较强的残余压应力场,残余压应力最大提升1.55倍。与喷丸处理叶片相比,经喷丸-电磁场复合工艺处理叶片的疲劳强度增加33%~36%。
In order to improve the residual stress distribution of aeroengine blades and eliminate the micro-damage caused by the shot peening on the blade surface, a new technique of shot peening-electromagnetic field composite control was proposed. X-ray diffraction techniques were used to test the distribution of leaf residual stress after shot peening, shot peening and shot peening-electromagnetic field composite control. Through the microstructure analysis of the blade material, the mechanism of the effect of the shot peening-electromagnetic field control on the residual stress of the titanium alloy blade was discussed. The results showed that the combined process of shot peening and electromagnetic field enhanced the residual compressive stress on the blade surface by 7.7% at the most, improved the uneven distribution of residual compressive stress caused by shot peening and formed strong residual compressive stress near the blade surface Field, the maximum increase of residual compressive stress 1.55 times. Compared with the shot peening blade, the fatigue strength of the blade by the shot peening-electromagnetic field composite process increased by 33% to 36%.