Lukyanenko O. Improving the carrying capacity of the ГТД compressor blades through finishing-strengthening treatment

The subject of research: the first stage blades of the compressor of the engine ТВЗ-117 made of the titanium alloy BT8M; the aim of research: increasing the carrying capacity of compressor blades made from titanium alloys through the formation of rational combination of characteristics of the surface layer by a surface hardening and subsequent applying the ion-plasma coating that assures high characteristics of durability, impact strength and wear resistance; methods of research are: radiometallographic methods - to determine structural crystallography in a surface layer of a blade foil and structural phase changes; metallographic methods - to research the microstructure of blades surface layer and fatigue fracture; mechanical engineering methods - to research residual stresses, adhesive strength of coating, durability parameters, impact strength and wear resistance of blades; methods of mathematical statistics - to process the results of testings and obtain correlative relationships; methods of theoryof elasticity - to compute the stress in a blade at collision with a foreign body; results: developed were the technological recommendations on applying the methods of finish - hardening machining and techniques to increase the carrying capacity of compressor blades; novelty: scientific substantiation of technological provision of carrying capacity of a compressor blades of the engine ТВЗ-117 has been given on basis of obtained results when researching the characteristics of surface foil layer of blade made of titanium alloy BT8M in relationship to machining regime and their influence on fatigue resistance and impact strength. It was found that preliminary ultrasound shot peening favours for beneficial development of TiN crystals with the most advantageous planes orientation in the process of coat formation that improve wear resistance of blades; strain concentration level produced by the damage on incoming edge of a blade foil has been determined. It was ascertained that in case of the damage on the incomingedge the zone of maximum strain shifts to the damaged area and the level of strain is doubled. Promoted - at "Motor Sich" Field of applying: aircraft engines and mechanical engineering.