公开(公告)号：US09643341B2

公开(公告)日：2017-05-09

申请号：US14765614

申请日：2014-02-04

Applicant: SNECMA ,  SAFRAN

Inventor： Franck Bernard Leon Varin ,  Thierry Chauvin

IPC: B29C33/00 ,  B29C33/30 ,  B29C33/44 ,  B29C37/00 ,  B29C45/33

CPC classification number: B29C33/0044 ,  B29C33/30 ,  B29C33/44 ,  B29C37/005 ,  B29C45/33

Abstract: A mold includes a first shell and a second shell that are suitable, in the closed position, for imparting a shape to a part that is to be molded in the mold, a main axis being perpendicular to the main plane in which the first shell and the second shell extend. The mold further includes a slide that is situated between the first shell and the second shell and that is in contact with the first shell and the second shell when the mold is in the closed position, and that is to come into contact with the molded part, the slide presenting a first face that constitutes its interface with the first shell, the first face presenting a primary direction along which the slide is suitable for sliding along the first face when the mold is in the open position.

公开(公告)号：US09457435B2

公开(公告)日：2016-10-04

申请号：US14374670

申请日：2013-01-24

Applicant: SNECMA ,  SAFRAN

Inventor： Richard Mathon ,  Olivier Foussard ,  Yann Marchal ,  Franck Bernard Leon Varin

IPC: B23P15/04 ,  B29C70/48 ,  B29C70/54 ,  B29C70/86 ,  B29D99/00 ,  B29C70/08 ,  B64C11/26 ,  B64F5/00 ,  B29C31/08 ,  B29C70/24 ,  B29L31/08 ,  B64D27/00

CPC classification number: B23P15/04 ,  B29C31/08 ,  B29C31/085 ,  B29C70/086 ,  B29C70/24 ,  B29C70/48 ,  B29C70/541 ,  B29C70/86 ,  B29D99/0025 ,  B29L2031/08 ,  B64C11/26 ,  B64D2027/005 ,  B64F5/10 ,  Y02T50/66 ,  Y10T29/49332 ,  Y10T29/49336 ,  Y10T29/49337

Abstract: A propeller blade, which can belong to a fan without covering by an external casing, includes two portions fitted into one another and of different materials, generally composite, to resist various stresses, heating coming from a rotor or impacts of solid bodies. An internal portion includes a blade core, a blade shank and possibly a foam lining, and a preform of an outside portion is assembled to it by surrounding it closely before being completely formed by receiving its resin, which is placed into polymerization. A method for producing the propeller blade guarantees good assembly of the portions without defects of form, damage or deformation of a fiber weave.

Abstract translation: 可以属于风扇而不被外部壳体覆盖的螺旋桨叶片包括彼此并且通常复合的不同材料的两个部分，以抵抗各种应力，来自转子的加热或固体的冲击。 内部部分包括刀片芯，刀片柄和可能的泡沫衬里，并且外部部分的预成型件通过在通过接收其被聚合的树脂完全形成之前紧密地围绕在其上而形成。 用于制造螺旋桨叶片的方法保证了这些部分的良好组装，而没有纤维编织的形式，损坏或变形的缺陷。

公开(公告)号：US10180070B2

公开(公告)日：2019-01-15

申请号：US14889710

申请日：2014-04-28

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Thierry Chauvin ,  Franck Bernard Leon Varin

IPC: B29C65/00 ,  B32B37/00 ,  C08J5/00 ,  B31F5/00 ,  B65H29/00 ,  B29C65/08 ,  B30B5/02 ,  B30B5/04 ,  B30B15/34 ,  B21K25/00 ,  B23P15/04 ,  B21D53/78 ,  B21K3/04 ,  B23P15/02 ,  F01D5/28 ,  B29C65/78 ,  F04D29/02 ,  F04D29/32 ,  F01D25/28 ,  F01D5/14 ,  B29C65/48 ,  B23Q3/06 ,  B29L31/08 ,  B29K101/00 ,  B29K105/00 ,  B29C65/18

Abstract: A tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, the tooling including a blade support for receiving a blade while leaving surfaces of the leading edge of the blade disengaged; and a leading edge reinforcement support on which the blade support is designed to be mounted, and including two lateral wedges between which the metal reinforcement for the leading edge of the blade is positioned, the wedges being suitable for being capable of moving towards each other and apart from each other and each of them being provided with a suction grid for gripping the metal reinforcement, the leading edge reinforcement support further including heater elements for polymerizing an adhesive film applied on the leading edge surfaces of the blade.

公开(公告)号：US20150151485A1

公开(公告)日：2015-06-04

申请号：US14412532

申请日：2013-07-03

Applicant: SNECMA

Inventor： Thierry Godon ,  Bruno Jacques Gerard Dambrine ,  Franck Bernard Leon Varin

IPC: B29C65/54 ,  B29C45/26 ,  B32B38/18 ,  B32B37/12 ,  B32B37/16 ,  B29C45/14 ,  B29C45/16

CPC classification number: B29C65/542 ,  B23P15/04 ,  B29C45/14008 ,  B29C45/14065 ,  B29C45/1657 ,  B29C45/1671 ,  B29C45/2602 ,  B29C65/483 ,  B29C65/4835 ,  B29C65/7847 ,  B29C66/12461 ,  B29C66/301 ,  B29C66/532 ,  B29C66/721 ,  B29C66/72141 ,  B29C66/742 ,  B29C66/81423 ,  B29C66/8221 ,  B29C66/83241 ,  B29C2045/14155 ,  B29C2045/1664 ,  B29K2305/00 ,  B29L2009/003 ,  B29L2031/08 ,  B29L2031/082 ,  B32B37/1284 ,  B32B37/16 ,  B32B38/1858 ,  B32B2038/0076 ,  B32B2305/08 ,  B32B2311/18 ,  B32B2603/00 ,  F01D5/282 ,  F01D5/288 ,  F04D29/324 ,  F05D2240/303 ,  Y02T50/672 ,  Y02T50/673

Abstract: A method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material and an injection mold for performing the method, the method including positioning the structural metal reinforcement in an injection mold, positioning the portion of the blade onto which the structural metal reinforcement is to be fastened in the injection mold, the portion of the blade and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them a gap, injecting adhesive into the gap between the structural metal reinforcement and the portion of the blade onto which the structural metal reinforcement is to be fastened, and polymerizing the adhesive.

Abstract translation: 一种将由复合材料制成的燃气轮机叶片的一部分上的结构金属加强件紧固的方法，以及用于执行该方法的注射模具的方法，该方法包括将结构金属加强件定位在注射模具中， 结构金属加强件应紧固在注射模具中，刀片和结构金属加强件的部分在其最终相对位置相对于彼此定位，同时在它们之间留有间隙，将粘合剂注入到结构金属加强件 以及将结构金属加强件固定在其上的刀片部分，并使粘合剂聚合。

公开(公告)号：US10137640B2

公开(公告)日：2018-11-27

申请号：US15101754

申请日：2014-11-28

Applicant: SNECMA

Inventor： Thierry Godon ,  Julien Schneider ,  Franck Bernard Leon Varin

IPC: B29C65/00 ,  B29C65/48 ,  F16B11/00 ,  F04D29/32 ,  F04D29/02 ,  B29C70/84 ,  B29C70/72 ,  B29C65/70 ,  B29C65/02 ,  B29C65/18 ,  B29C65/26 ,  B29L31/08 ,  F01D5/14 ,  F01D5/28

Abstract: A method is provided of bonding together at least two parts. The method includes assembling together at least two parts and at least one adhesive layer, the adhesive being configured so that its adhesive power increases on heating as a result of it polymerizing, at least one of the parts being made of composite material or of metal, the adhesive layer being present, after assembly, between the parts, the assembled together parts and the adhesive being present in a chamber defined by a wall, the wall having an inside face situated facing a first part present between the adhesive layer and the wall, the first part being intended to be bonded to a second part and only a fraction of the second part being present inside the chamber; and applying a liquid against the wall on its side opposite from the chamber.

公开(公告)号：US10259169B2

公开(公告)日：2019-04-16

申请号：US14412532

申请日：2013-07-03

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thierry Godon ,  Bruno Jacques Gerard Dambrine ,  Franck Bernard Leon Varin

IPC: B29C65/54 ,  B23P15/04 ,  B29C65/78 ,  B29C65/00 ,  F01D5/28 ,  B29C65/48 ,  B29C45/14 ,  B29C45/16 ,  B29C45/26 ,  B32B37/12 ,  B32B37/16 ,  B32B38/18 ,  F04D29/32 ,  B29L31/08 ,  B29K305/00 ,  B29L9/00 ,  B32B38/00

Abstract: A method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material and an injection mold for performing the method, the method including positioning the structural metal reinforcement in an injection mold, positioning the portion of the blade onto which the structural metal reinforcement is to be fastened in the injection mold, the portion of the blade and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them a gap, injecting adhesive into the gap between the structural metal reinforcement and the portion of the blade onto which the structural metal reinforcement is to be fastened, and polymerizing the adhesive.