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据一线维修人员反馈,涡轮叶片烧蚀日趋严峻,给机务维修和航空公司运营带来很大压力。叶片烧蚀的根本原因在于传统冷却结构不能满足燃气温度升高的需要,针对该问题研究一种新型的缝型冷却结构,并通过数值计算从冷却效率与气动损失两方面验证该结构的冷却效果。结果显示:在工作吹风比适当范围内,缝型结构在展向与延伸方向都有明显均匀冷却性,显著降低了叶片表面由冷却不均产生的热应力,起到减缓叶片烧蚀、延长使用寿命的目的,同时在压力损失及加工清理维护方面也明显优于传统结构。
According to feedback from front-line maintenance personnel, turbine blade erosion has become increasingly severe, putting a lot of pressure on maintenance and airline operations. The basic reason of the blade ablation is that the traditional cooling structure can not meet the need of gas temperature rise. A new type of slot cooling structure is studied in this paper. The cooling effect of the structure is verified by numerical calculation from both cooling efficiency and aerodynamic loss . The results show that in the proper range of working blow ratio, the seam structure has obvious uniform cooling in the span direction and extending direction, significantly reducing the thermal stress caused by the uneven cooling on the blade surface, reducing the ablation of the blade and prolonging the use of the blade The purpose of life expectancy is also significantly better than traditional structures in terms of pressure loss and process cleanup and maintenance.