航空发动机涡轮叶片冷却气膜孔加工去除重熔层技术

为提高叶片工作时的冷却效果，叶片的气膜孔设计的越来越复杂，涡轮叶片的冷却气膜孔加工作为一项重要的技术至为关键。现有的条件下对气膜孔的加工进一步研究，基于挤压磨粒流加工理论，采用挤压磨粒流加工工艺试验方法，对叶片冷却气膜孔做控制磨粒流孔径增加量从而去除重熔层的实验。当磨粒流孔径伽．3增加量为0．04时，孔径蜘．5增加量为0．02时，就可消除重熔层的结果，说明了通过磨粒流去除重熔层和微裂纹具有非常满意的去除效果。

Removal Technology of Remelting Layer via Cooling Film Holes Processing of Aero Engine Turbine Blade

In order to improve the cooling effect of blade, blade film hole design becomes more and more complex. Film cooling hole machining in turbine blade as an important technology is the key. Un- der current circumstances, this paper makes further research on the processing of film hole, based on the theory of extrusion of abrasive flow machining, using extrusion abrasive flow test method for machi- ning process, making an experiment of controlling abrasive flow aperture increase in order to remove the remelting layer on blade film cooling holes. It has achieved the result that when the abrasive flow aper- ture diameter 0.3 increase is 0.04, and pore size ~P 0.5 increase is 0.02, the remelting layer results can be eliminated. The paper illustrates that removal effect is very satisfactory by removing remehing layer and micro crack with abrasive flow.