公开(公告)号：US09545762B2

公开(公告)日：2017-01-17

申请号：US13850169

申请日：2013-03-25

Applicant: SNECMA

Inventor： Francois Marie Paul Marlin ,  Philippe Verseux

IPC: B29C70/32 ,  B29C70/54 ,  B29C70/34 ,  F16L47/14 ,  B29C70/08 ,  B29K707/04 ,  B29K709/08 ,  B29L31/24 ,  B29C70/00

CPC classification number: B29C70/545 ,  B29C70/00 ,  B29C70/08 ,  B29C70/32 ,  B29C70/34 ,  B29C70/342 ,  B29C70/345 ,  B29C2793/009 ,  B29K2277/10 ,  B29K2707/04 ,  B29K2709/08 ,  B29L2031/24 ,  F16L47/14

Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface. There is no intersection between the first machining surface and the fibers of the main fiber structure.

Abstract translation: 公开了一种由包括由纤维结构增强的聚合物基体的复合材料制成的联接器。 联接器包括由主纤维结构增强的结构部分和由与主纤维结构不同的第一纤维结构增强的第一加工部分。 结构部分和第一加工部分的矩阵是相同的。 第一加工部分位于结构部分的主面的至少一部分上，并且在第一加工表面中加工。 第一加工面与主纤维结构的纤维之间没有交叉。

公开(公告)号：US20150159554A1

公开(公告)日：2015-06-11

申请号：US14272911

申请日：2014-05-08

Applicant: SNECMA

Inventor： Fabrice Cretin ,  Yvan Guezel ,  Francois Marie Paul Marlin ,  Thierry Georges Paul Papin ,  Alain Marc Lucien Bromann ,  Damien Lourit

IPC: F02C7/04

CPC classification number: F02C7/04 ,  F01D25/243 ,  F02K3/06 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2260/30 ,  F05D2260/31 ,  Y02T50/672 ,  Y10T137/0402 ,  Y10T137/0536

Abstract: This invention relates to an assembly (100) for an aircraft turbofan comprising a flowpath splitter (40) downstream from which there is firstly a fan flowpath (31) inner delimitation ring (44) and secondly a compressor case (42), the assembly comprising a plurality of outlet guide vanes (34) provided with an inner platform (50) located in the downstream continuity of the delimitation ring.According to the invention, the assembly comprises at least one part (52) to support the delimitation ring (44), comprising a radially outer end (52b) fixed to a downstream part of this ring (44) and a radially inner end (52a) fixed to the compressor case (42).

Abstract translation: 本发明涉及一种用于飞行器涡扇风扇的组件（100），其包括在下游的流路分流器（40），其中首先具有风扇流路（31）内定界环（44），其次是压缩机壳体（42），该组件包括 多个出口导叶（34）设置有位于定界环的下游连续性的内平台（50）。 根据本发明，组件包括支撑定界环（44）的至少一个部分（52），包括固定到该环（44）的下游部分的径向外端（52b）和径向内端（52a） ）固定到压缩机壳体（42）。

公开(公告)号：US09528441B2

公开(公告)日：2016-12-27

申请号：US14272911

申请日：2014-05-08

Applicant: SNECMA

Inventor： Fabrice Cretin ,  Yvan Guezel ,  Francois Marie Paul Marlin ,  Thierry Georges Paul Papin ,  Alain Marc Lucien Bromann ,  Damien Lourit

IPC: F01B25/00 ,  F02C7/04 ,  F01D25/24 ,  F02K3/06

CPC classification number: F02C7/04 ,  F01D25/243 ,  F02K3/06 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2260/30 ,  F05D2260/31 ,  Y02T50/672 ,  Y10T137/0402 ,  Y10T137/0536

Abstract: This invention relates to an assembly (100) for an aircraft turbofan comprising a flowpath splitter (40) downstream from which there is firstly a fan flowpath (31) inner delimitation ring (44) and secondly a compressor case (42), the assembly comprising a plurality of outlet guide vanes (34) provided with an inner platform (50) located in the downstream continuity of the delimitation ring.According to the invention, the assembly comprises at least one part (52) to support the delimitation ring (44), comprising a radially outer end (52b) fixed to a downstream part of this ring (44) and a radially inner end (52a) fixed to the compressor case (42).

Abstract translation: 根据本发明，组件包括支撑定界环（44）的至少一个部分（52），包括固定到该环（44）的下游部分的径向外端（52b）和径向内端（52a） ）固定到压缩机壳体（42）。