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一、前言 随着航空事业的不断发展,对喷气发动机涡轮前温度提出了更高的要求,因而对涡轮叶片材料的高温强度性能也要求与之相适应。为了捉高合金的高温性能,一般要调整合金成分。另外,也可采用在合金表面渗铝的办法提高其抗氧化和腐蚀性能。但是,表面全部渗铝的不足之处是直接承受振动力的零件部位如叶片榫齿,若渗有铝层则容易产生渗层裂纹而带来缺口敏感,同时榫齿渗铝也影响滚棒尺寸不利装配。因此,在国外都是采用保护套(金属或陶瓷)或保护涂层法加以解决。当然采用涂层保护方法较好,然而此类涂层的配方,配制和使用方法在国外都属于专利、公开文献中未见报导。为了某发动机Ⅱ级涡轮叶片局部渗铝工艺生产定型的急需,本着自力更生原则,我们研制了适用于国内目前采用的“Al-Fe”粉固体包埋法渗铝工艺的防渗铝涂料,现已取得了实用的效果,正式投入了批生产。
I. INTRODUCTION With the continuous development of the aviation industry, higher requirements are put forward on the temperature of the jet turbine before the turbine. Therefore, the high-temperature strength performance of the turbine blade material is also required to be compatible with it. In order to catch high temperature alloy performance, the general adjustment of alloy composition. In addition, aluminum alloy surface can also be used to improve its anti-oxidation and corrosion resistance. However, the surface of the overall lack of aluminum is directly subjected to vibration parts such as blade tenon teeth, if the infiltration of aluminum layer is prone to cracks in the gap caused by the gap sensitive, while the tooth aluminum teeth also affect the roll size Adverse assembly. Therefore, in foreign countries are used protective cover (metal or ceramic) or protective coating method to be solved. Of course, the coating protection method is better, however, the formulation, formulation and use of such coatings are all patented in foreign countries and have not been reported in open literature. In order to urgently need the localized aluminizing process of a class II turbine blade, and based on the principle of self-reliance, we have developed the anti-seepage aluminum coating suitable for the aluminized process of the currently used Al-Fe powder solid embedding method Has achieved practical results, formally put into batch production.