公开(公告)号：US20180010462A1

公开(公告)日：2018-01-11

申请号：US15201979

申请日：2016-07-05

申请人： Safran Aircraft Engines

发明人： Jeremy GUIVARC'H ,  Francois Charleux

IPC分类号： F01D5/14 ,  F01D5/28 ,  B29B11/16 ,  B29C45/02 ,  B29C45/14 ,  B29L31/08

CPC分类号： F01D5/143 ,  B29B11/16 ,  B29C45/02 ,  B29C45/14631 ,  B29K2713/00 ,  B29L2031/082 ,  D03D1/00 ,  D03D13/004 ,  D03D25/005 ,  D10B2505/02 ,  F01D5/282 ,  F01D11/008 ,  F05D2220/36 ,  F05D2240/80 ,  F05D2300/6012 ,  F05D2300/6034

摘要： The invention provides a fitted platform (1) for positioning between two adjacent blades of an aviation turbine engine fan, said platform comprising a flow passage wall (10) made of composite material having a central portion (16) and first and second margins (18) each extending in a longitudinal direction of said wall, each margin extending over a determined distance (D) from the central portion (16) in a transverse direction of said wall, said flow passage wall comprising fiber reinforcement densified by a matrix, the platform being characterized in that the fiber reinforcement present in the central portion (16) presents three-dimensional weaving, and in that the fiber reinforcement present in the first and second margins (18) presents two-dimensional weaving, at least in part. The invention also provides a fan module, a turbine engine, and a method of fabricating such a platform.

公开(公告)号：US20180274375A1

公开(公告)日：2018-09-27

申请号：US15763703

申请日：2016-09-27

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Gilles Pierre-Marie NOTARIANNI ,  Jeremy GUIVARC'H ,  Frederic Jean-Bernard POUZADOUX ,  Dominique RAULIN ,  Thibault RUF

IPC分类号： F01D5/28 ,  F01D5/14

CPC分类号： F01D5/282 ,  F01D5/147 ,  F04D29/324 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2240/303 ,  F05D2260/36 ,  F05D2300/133 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

摘要： A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.

公开(公告)号：US20220127965A1

公开(公告)日：2022-04-28

申请号：US17441619

申请日：2020-03-19

申请人： SAFRAN ,  SAFRAN AIRCRAFT ENGINES

发明人： Jeremy Philippe Pierre EDYNAK ,  Jeremy GUIVARC'H ,  Lola AULIAC ,  Thibaut Dominique Augustin GIRARD ,  Pierre Jean FAIVRE D'ARCIER

IPC分类号： F01D5/30 ,  F01D11/00

摘要： The invention relates to a fan rotor for a turbomachine, comprising including a fan disk, fan blades with a leading edge and a trailing edge, platforms inserted between the blades and fixed to the periphery of the disk, each including an aerodynamic surface extending from the leading edges to the trailing edges of the blades. The aerodynamic surface includes an upstream longitudinal portion on the side of the leading edges and a downstream longitudinal portion on the side of the trailing edges, the upstream longitudinal portion being supported by a first member of the platform fixed to the disk in a pivotable manner, and the downstream longitudinal portion being independent of the upstream longitudinal portion and supported by a second member of the platform which is independent of the first member and fixed to the disk in a pivotable manner.

公开(公告)号：US20200217217A1

公开(公告)日：2020-07-09

申请号：US16733620

申请日：2020-01-03

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN

发明人： Thibaut Dominique Augustin GIRARD ,  Lola AULIAC ,  Jeremy GUIVARC'H ,  Jeremy Philippe Pierre EDYNAK ,  Pierre Jean FAIVRE D'ARCIER

IPC分类号： F01D11/00 ,  F01D5/02

摘要： Seal (10) for an inter-blade platform intended to extend circumferentially about an axis and to be mounted between two axial ends of the inter-blade platform, including a first part (10a) in contact with a first blade adjacent to a first circumferential end of the platform, and a second part (10b) in contact with a second blade adjacent to a second circumferential end of the platform, the first part (10a) and the second part (10b) of the seal (10) being fixed to each other such that a displacement in the circumferential direction of one of the two parts (10a, 10b) of the seal (10) causes a displacement of the other part (10a, 10b) of the seal (10) in the same direction, when the two parts (10a, 10b) of the seal (10) are fixed to each other.

公开(公告)号：US20190390559A1

公开(公告)日：2019-12-26

申请号：US16446669

申请日：2019-06-20

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Jeremy GUIVARC'H ,  Fabrice Michel Francois Rene AUBERT ,  Pierre Martin MICHELSEN

IPC分类号： F01D11/00 ,  F01D5/32 ,  F04D19/00

摘要： A fan includes: a fan disc; an inter-blade platform including a base and a radial tab, a second orifice being formed in the tab of the platform; and a lock having a downstream edge configured to bear against the tab of the platform. The one among the downstream edge and the yoke of the fan disc includes a pin, the other includes a first orifice, the pin being configured to enter the first orifice and the second orifice so as to block the platform relative to the fan disc.