公开(公告)号：US10655250B2

公开(公告)日：2020-05-19

申请号：US15262029

申请日：2016-09-12

Applicant: AIRCELLE

Inventor： Julien Lorrillard ,  Bertrand Desjoyeaux ,  Michel Rognant ,  Benjamin Provost

IPC: D03D25/00 ,  D03D1/00 ,  D03D11/02 ,  D03D13/00 ,  D03D49/20 ,  B29B11/16

Abstract: The disclosure relates to a shape-woven preform which has an omega-shaped cross-section including a core and a sole. At least one part of the core and at least one part of the sole have weft yarns in common with one another.

公开(公告)号：US08845287B2

公开(公告)日：2014-09-30

申请号：US13731150

申请日：2012-12-31

Applicant: Aircelle ,  SNECMA

Inventor： Hervé Hurlin ,  Nicolas Dezeustre ,  Olivier Kerbler ,  François Gallet ,  Bertrand Desjoyeaux

IPC: F01D25/28 ,  B64D29/08 ,  F01D25/24 ,  B64D29/06

CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D29/08

Abstract: A nacelle for a turbojet engine is provided that includes an air intake upstream from the turbojet engine, a middle section intended to surround a fan of the turbojet engine and its case, and a downstream section. The middle section is made from at least one aerostructure capable of ensuring external aerodynamic continuity of the nacelle, and the aerostructure is rigidly bound, so as to be able to be taken apart, to at least one surrounding fixed structure.

Abstract translation: 提供了一种用于涡轮喷气发动机的机舱，其包括涡轮喷气发动机上游的进气口，旨在围绕涡轮喷气发动机及其壳体的风扇的中间部分和下游部分。 中间部分由能够确保机舱的外部空气动力连续性的至少一个航空结构制成，并且航空结构刚性地结合，以便能够被分离到至少一个周围的固定结构。

公开(公告)号：US09518509B2

公开(公告)日：2016-12-13

申请号：US14635667

申请日：2015-03-02

Applicant: AIRCELLE

Inventor： Bertrand Desjoyeaux ,  Thierry Deschamps ,  John Moutier

IPC: F02C7/04 ,  B32B3/12 ,  B32B3/18 ,  F02K1/82 ,  G10K11/172 ,  B32B37/12 ,  B32B38/00 ,  B32B5/14 ,  B32B5/24 ,  B32B7/12 ,  B32B15/04 ,  B32B15/14 ,  B32B15/20 ,  B32B3/26

CPC classification number: F02C7/04 ,  B32B3/12 ,  B32B3/18 ,  B32B3/266 ,  B32B5/142 ,  B32B5/24 ,  B32B7/12 ,  B32B15/04 ,  B32B15/14 ,  B32B15/20 ,  B32B37/12 ,  B32B38/0012 ,  B32B2038/0052 ,  B32B2307/102 ,  B32B2307/50 ,  B32B2307/546 ,  B32B2307/724 ,  B32B2307/7242 ,  B32B2605/18 ,  F02K1/827 ,  G10K11/172 ,  Y02T50/672 ,  Y10T137/0536 ,  Y10T156/1003 ,  Y10T428/192 ,  Y10T428/24149

Abstract: The present disclosure related to a method for manufacturing a structure with cellular cores that can be used in a structural panel of a turbojet nacelle, including at least one block of cellular cores. The at least one block of cellular cores includes a central portion with core honeycomb cells, and two side portions each including side honeycomb cells. The side honeycomb cells have edge honeycomb cells situated on edges of a side part of a block, and adjacent honeycomb cells. In particular, the method includes: A) forming junction walls on the side honeycomb cells by opening the edge honeycomb cells, the junction walls being capable of interacting for forming a junction area; B) unfolding the junction walls thus formed in step A; and C) joining the junction walls thus unfolded in step B and belonging to two different side portions end-to-end.

Abstract translation: 本公开涉及一种用于制造具有蜂窝芯的结构的方法，所述结构可以用于包括至少一个蜂窝芯的块的涡轮喷气发动机舱的结构面板中。 所述至少一个蜂窝芯块包括具有核心蜂窝单元的中心部分，以及包括侧蜂窝单元的两个侧部分。 侧蜂窝单元具有位于块的侧部的边缘上的边缘蜂窝单元和相邻的蜂窝单元。 特别地，该方法包括：A）通过打开边缘蜂窝单元在侧蜂窝单元上形成接合壁，所述接合壁能够相互作用以形成接合区域; B）在步骤A中展开由此形成的接合壁; 并且C）在步骤B中连接如此展开的接合壁并且属于端对端的两个不同的侧部。

公开(公告)号：US20130133977A1

公开(公告)日：2013-05-30

申请号：US13749215

申请日：2013-01-24

Applicant: Aircelle

Inventor： Herve Hurlin ,  Nicolas Dezeustre ,  Wouter Balk ,  Bertrand Desjoyeaux

IPC: B32B3/10

CPC classification number: B32B3/10 ,  B64D33/02 ,  B64D33/06 ,  B64D2033/0206 ,  B64D2033/0286 ,  F01D25/243 ,  F01D25/28 ,  F02C7/045 ,  F02K1/44 ,  F02K1/827 ,  F05B2260/301 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2300/603 ,  G10K11/172 ,  Y02T50/672

Abstract: An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached.

Abstract translation: 提供一种声学面板，其包括布置在至少内部皮肤和外部皮肤之间的至少一个细胞芯，其中所述外部皮肤包括至少一个紧固件，所述至少一个紧固件能够以可断开的方式与与其结构相关联的互补的紧固件协作 它是附加的。

公开(公告)号：US09481054B2

公开(公告)日：2016-11-01

申请号：US13958246

申请日：2013-08-02

Applicant: AIRCELLE

Inventor： Bertrand Desjoyeaux ,  Olivier Hubier

IPC: B64D33/00 ,  B23P15/00 ,  B29C70/84 ,  B64D33/02 ,  B29C70/44 ,  B29C70/48

CPC classification number: B23P15/008 ,  B29C70/44 ,  B29C70/48 ,  B29C70/84 ,  B64D33/02 ,  B64D2033/0286 ,  Y10T29/49346

Abstract: A method for manufacturing an air-intake structure for a turbojet-engine nacelle includes two component parts, i.e. one air-intake lip structure and one outer cowl for the air-intake structure. In particular, the method includes the following steps: separately manufacturing the component parts such that each integrates one overlapping portion with a part to which is to be attached. The overlapping portion is configured such that an outer surface of the outer overlapping portion provides continuity with an outer surface of the outer cowl associated with the inner overlapping portion. To secure the overlapping portions, glue or a fastener may be used.

Abstract translation: 用于制造涡轮喷气发动机机舱的进气结构的方法包括两个部件，即一个进气口结构和一个用于进气结构的外罩。 特别地，该方法包括以下步骤：分开制造组成部件，使得每个部件将一个重叠部分与要附接的部分集成。 重叠部分构造成使得外部重叠部分的外表面与外部整流罩的与内部重叠部分相关联的外表面提供连续性。 为了固定重叠部分，可以使用胶水或紧固件。

公开(公告)号：US08579078B2

公开(公告)日：2013-11-12

申请号：US13749215

申请日：2013-01-24

Applicant: Aircelle

Inventor： Herve Hurlin ,  Nicolas Dezeustre ,  Wouter Balk ,  Bertrand Desjoyeaux

IPC: E04B1/82

CPC classification number: B32B3/10 ,  B64D33/02 ,  B64D33/06 ,  B64D2033/0206 ,  B64D2033/0286 ,  F01D25/243 ,  F01D25/28 ,  F02C7/045 ,  F02K1/44 ,  F02K1/827 ,  F05B2260/301 ,  F05D2220/36 ,  F05D2250/283 ,  F05D2300/603 ,  G10K11/172 ,  Y02T50/672

Abstract: An acoustic panel is provided that includes at least one cellular core arranged between at least an internal skin and an external skin, wherein the external skin incorporates at least one fastener able to collaborate in a disconnectable fashion with a complementary fastener associated with a structure to which it is to be attached.

Abstract translation: 提供一种声学面板，其包括布置在至少内部皮肤和外部皮肤之间的至少一个细胞芯，其中所述外部皮肤包括至少一个紧固件，所述至少一个紧固件能够以可断开的方式与与其结构相关联的互补的紧固件协作 它是附加的。

公开(公告)号：US20130280031A1

公开(公告)日：2013-10-24

申请号：US13855947

申请日：2013-04-03

Applicant: AIRCELLE

Inventor： Herve Hurlin ,  Nicolas Dezeustre ,  Wouter Balk ,  Bertrand Desjoyeaux

IPC: F01D25/24

CPC classification number: F01D25/24 ,  F01D5/005 ,  F02K1/605 ,  F02K1/625 ,  F02K1/72 ,  F02K1/766 ,  F05D2230/80 ,  F05D2240/14 ,  Y02T50/672 ,  Y02T50/673

Abstract: A thrust reverser for the nacelle of a turboreactor includes at least one fixed front frame that can be mounted downstream of a fan casing of the turboreactor and directly or indirectly supports at least one flow deviation vanes, in which at least part of the flow deviation vanes can be detached from the front frame and moved in translation independently therefrom when a maintenance operation is being carried out on the reverser.

Abstract translation: 用于涡轮反应器的机舱的推力反向器包括至少一个固定的前框架，其可以安装在涡轮反应器的风扇壳体的下游，并且直接或间接地支撑至少一个流动偏离叶片，其中至少一部分流动偏离叶片 当在反向器上进行维护操作时，可以从前框架拆下并且独立地移动。

公开(公告)号：US10016912B2

公开(公告)日：2018-07-10

申请号：US14761792

申请日：2014-01-09

Applicant: SAFRAN ,  AIRCELLE

Inventor： Patrick Dunleavy ,  Bertrand Desjoyeaux

IPC: D03D3/02 ,  B60B11/06 ,  B29B11/16 ,  D03D25/00

CPC classification number: B29B11/16 ,  B60B11/06 ,  B60B2310/241 ,  B60B2360/3444 ,  B60Y2200/51 ,  D03D3/02 ,  D03D25/005 ,  D10B2101/06 ,  D10B2101/08 ,  D10B2505/02 ,  Y10T428/1314 ,  Y10T428/1362

Abstract: A single-piece woven fiber structure for fabricating an axisymmetric part of varying diameter made out of composite material, the fiber structure having a portion of frustoconical shape with a large diameter and a small diameter, the ratio between the large diameter and the small diameter being not less than 2. The fiber structure is formed by winding layers of warp and weft yarns that are woven on a mandrel having a profile that is defined as a function of the profile of the part to be fabricated with warp yarn take-up. For each layer of yarns, the weft yarns are angularly distributed on a single diameter in a zone of the large diameter of the portion of frustoconical shape and on at least two different diameters in a zone of the small diameter of the portion of frustoconical shape in order to form at least two superposed plies of weft yarns.

公开(公告)号：US09109509B2

公开(公告)日：2015-08-18

申请号：US13671233

申请日：2012-11-07

Applicant: AIRCELLE

Inventor： Christophe Thorel ,  Bertrand Desjoyeaux ,  Florent Bouillon ,  John Moutier ,  Stéphane Bardin

IPC: B64D33/02 ,  F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/82

CPC classification number: F02C7/04 ,  B64D29/06 ,  F02C7/045 ,  F02K1/80 ,  F02K1/827 ,  Y02T50/672 ,  Y10T29/49826 ,  Y10T403/45

Abstract: A unit for an aircraft thruster is provided that includes a first ferrule configured to be attached to a second ferrule and a first connection flange configured to be secured to a second corresponding connection flange secured to the second ferrule. The connection flange includes a portion forming a plane extending along a radial direction with respect to the first ferrule. A link between the first ferrule and the corresponding connection flange is offset to a distance from said plane corresponding to a length for damping a shear-generating flexural moment, generated by fluxes of forces passing through the first ferrule.

Abstract translation: 提供了一种用于飞机推进器的单元，其包括构造成附接到第二套圈的第一套圈和构造成固定到固定到第二套圈的第二对应连接凸缘的第一连接凸缘。 连接凸缘包括形成相对于第一套圈沿径向方向延伸的平面的部分。 第一套圈和对应的连接凸缘之间的连接偏移到与所述平面相对应的距离，该长度与用于阻尼通过第一套圈的力的通量产生的剪切产生弯曲力矩的长度相对应。

公开(公告)号：US20140255178A1

公开(公告)日：2014-09-11

申请号：US14286666

申请日：2014-05-23

Applicant: AIRCELLE

Inventor： Arnaud OUDIN ,  Bertrand Desjoyeaux ,  Nicolas Dezeustre ,  Olivier Kerbler

IPC: F01D9/02

CPC classification number: F01D9/02 ,  F01D25/28 ,  F04D29/023 ,  F04D29/542 ,  F05C2225/08 ,  F05D2240/12 ,  F05D2300/43 ,  F05D2300/436 ,  F05D2300/44 ,  F05D2300/603 ,  F05D2300/6034 ,  Y02T50/672

Abstract: A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.

Abstract translation: 由复合材料制成的流动矫直叶片包括由三维编织织物棒构成的芯，该芯由纤维覆盖层包围，该芯并且该覆盖物使用热固性树脂固结。