公开(公告)号：US20190143396A1

公开(公告)日：2019-05-16

申请号：US16092922

申请日：2017-04-10

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN ,  Centre National De La Recherche Scientifique

发明人： Gilles Charles Casimir KLEIN ,  Jean-Michel Patrick Maurice FRANCHET ,  Yann LEPETITCORPS ,  Jerome ROGER ,  Benoit SERGENT

IPC分类号： B21D53/78 ,  B21D37/01 ,  B21D35/00 ,  C23C8/30 ,  C23C8/02 ,  F01D5/14

摘要： A metal core for hot-shaping a metal part made out of titanium-based alloy. The metal core presents on an outside surface that is to come into contact with the metal part, a layer of material enriched in metallic carbonitride. The metal core includes an alloy based on nickel or on cobalt, and the nickel- or cobalt-based alloy includes chromium, molybdenum, and/or titanium. A method of fabricating and regenerating the metal core, and also a method of fabricating a metal part using the metal core, are disclosed.

公开(公告)号：US20170342524A1

公开(公告)日：2017-11-30

申请号：US15538119

申请日：2015-12-14

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Jean-Yves GUEDOU ,  Jean-Michel Patrick Maurice FRANCHET ,  Jean-Loup Bernard Victor STRUDEL ,  Laurent GERMANN ,  Dipankar BANERJEE ,  Vikas KUMAR ,  Tapash NANDY

IPC分类号： C22C14/00 ,  C22C1/04

CPC分类号： C22C14/00 ,  C22C1/0458 ,  C22C1/0491 ,  C22F1/183

摘要： A titanium-based intermetallic alloy includes, in atomic percent, 16% to 26% Al, 18% to 28% Nb, 0% to 3% of a metal M selected from Mo, W, Hf, and V, 0.1% to 2% of Si, 0% to 2% of Ta, 1% to 4% of Zr, with the condition Fe+Ni≦400 ppm, the balance being Ti, the alloy also presenting an Al/Nb ratio in atomic percent lying in the range 1.05 to 1.15.

公开(公告)号：US20170274470A1

公开(公告)日：2017-09-28

申请号：US15512140

申请日：2015-09-18

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Gilles Charles Casimir KLEIN ,  Jean-Michel Patrick Maurice FRANCHET ,  Dominique Michel Serge MAGNAUDEIX

IPC分类号： B23K20/02 ,  F04D29/32 ,  F01D5/28 ,  F04D29/02 ,  B23P15/04 ,  F01D5/14

摘要： A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.