公开(公告)号：US20180222101A1

公开(公告)日：2018-08-09

申请号：US15891888

申请日：2018-02-08

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN

发明人： Marc-Emmanuel Jean François TECHER ,  Nicolas Cambyse ASHTARI ,  Raoul JAUSSAUD ,  Benoit BAZIN ,  Thierry CHAUVIN ,  Olivier FOUSSARD ,  Nate GRAVELLE ,  Adrien TOUZE

IPC分类号： B29C45/77 ,  B29C70/48 ,  B29C45/82 ,  B29C45/02

CPC分类号： B29C45/77 ,  B29C45/02 ,  B29C45/82 ,  B29C70/48 ,  B29C70/546 ,  B29C2045/465 ,  B29C2945/7604 ,  B29C2945/76498 ,  B29L2031/082

摘要： The invention relates to a resin injection regulator for a resin injection circuit in a mould for producing a composite part, in particular a turbine engine composite part, characterised in that it comprises at least one vessel which is connected to said circuit and inside of which a movable wall means can be moved in a sealed manner, said movable wall means defining in said vessel a first cavity which forms a container for accumulation of resin and is designed to be connected to at least one part of said circuit, and a second cavity which is designed to be connected to a source of pressurised fluid, said movable wall means being designed to be urged by the pressurised fluid with which the second cavity is supplied in order to exert a pressure on the resin contained in the first cavity by isolating said resin from said fluid.

公开(公告)号：US20210323250A1

公开(公告)日：2021-10-21

申请号：US17271456

申请日：2019-08-27

申请人： SAFRAN

发明人： Christophe RAVEY ,  Olivier FOUSSARD ,  Nicolas Pierre LANFANT ,  Didier PAYEN ,  Adrien TOUZE ,  Romain VENAT

IPC分类号： B29C70/48 ,  B29B11/16 ,  B29C70/24 ,  B29C70/54 ,  F01D5/28

摘要： A process for shaping, by compaction, a fibrous structure obtained by three-dimensional or multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns. The yarns of each plurality of layers of warp yarns and layers of weft yarns are coated with a sizing composition. The shaping includes a pre-compaction stage followed by a stage of final compaction of the fibrous structure. During pre-compaction and final compaction, the fibrous structure is at a temperature greater than or equal to the softening temperature of the sizing composition. The process further includes the cooling of the fibrous preform obtained after final compaction of the fibrous structure.

公开(公告)号：US20240102390A1

公开(公告)日：2024-03-28

申请号：US17753579

申请日：2020-09-11

申请人： SAFRAN

发明人： Enrico Giovanni OBERT ,  Adrien TOUZE

IPC分类号： F01D5/18 ,  B29C37/00 ,  B29C70/24 ,  B29C70/48

CPC分类号： F01D5/18 ,  B29C37/0017 ,  B29C70/24 ,  B29C70/48 ,  B29K2105/0845 ,  F05D2230/30 ,  F05D2240/12 ,  F05D2300/6034

摘要： The invention relates to a method for manufacturing a hollow part made of composite material for an aircraft turbomachine, wherein: a) a preform is produced by the three-dimensional weaving of threads; b) the preform is cut so as to provide a separation; c) the cut preform is deformed so as to provide an orifice then comprising a first and a second open end (27a, 27b); d) the deformed preform is placed into an injection mould; e) a resin is injected in order to impregnate the whole of the deformed preform; f) the resin is polymerised; and g) a composite part is extracted from the mould; characterised in that: h) a flexible mandrel (31) with a predetermined shape is positioned in the orifice before the injection step e); i) the flexible mandrel (31) is removed after step f) or the demoulding step g), the composite part then having a hollow core (25).