公开(公告)号：US09032740B2

公开(公告)日：2015-05-19

申请号：US12918500

申请日：2009-02-27

Applicant: Frédéric Journade ,  Laurent Lafont ,  Delphine Jalbert

Inventor： Frédéric Journade ,  Laurent Lafont ,  Delphine Jalbert

IPC: F02C7/20 ,  B64D27/26 ,  F01D25/28

CPC classification number: B64D27/26 ,  B64D2027/264 ,  F01D25/28 ,  F02C7/20 ,  Y02T50/672

Abstract: An aircraft engine assembly including an attachment mechanism of a turbojet onto a rigid structure of a mounting strut, including a first, second, and third forward engine attachment for taking up thrust loads brought onto the fan frame, and arranged such that the third attachment passes through a first diametrical plane of the turbojet, the first and second attachments being disposed on one side and another of the first plane. The first and second forward engine attachments are respectively brought to the fan frame at two points, situated beyond the second diametrical plane of the turbojet, orthogonal to the first diametrical plane, with respect to the third attachment.

Abstract translation: 一种飞机发动机组件，其包括涡轮喷气发动机的附接机构到安装支柱的刚性结构上，包括第一，第二和第三前进发动机附件，用于承受带到风扇框架上的推力载荷，并且布置成使得第三附件通过 通过涡轮喷气发动机的第一直径平面，第一和第二附件被设置在第一平面的一侧和另一侧上。 第一和第二前向发动机附件分别相对于第三附件在两个点处被引导到风扇框架，该点位于涡轮喷气发动机的与第一直径平面正交的第二直径平面之外。

公开(公告)号：US08973885B2

公开(公告)日：2015-03-10

申请号：US12915736

申请日：2010-10-29

Applicant: Mathieu Bonnet ,  Frederic Journade ,  Laurent Lafont ,  Benoit Valery

Inventor： Mathieu Bonnet ,  Frederic Journade ,  Laurent Lafont ,  Benoit Valery

IPC: F16M13/00 ,  B64D27/00 ,  F16C7/04

CPC classification number: F16C7/04 ,  Y10T403/11

Abstract: A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.

Abstract translation: 结构杆具有在轴向空腔内具有轴向空腔和次级杆的主杆，使得副杆能够沿着杆的纵向轴线的方向在轴向腔内移动。 主杆具有用于以刚性方式在第一端处紧固结构杆的轴承，并且在第二端处不刚性地紧固到结构。 相反，副杆具有用于以刚性方式在第二端处紧固结构杆的轴承，并且在第一端处不刚性地紧固到结构。 主杆和副杆通过由可变形和弹性材料制成的一个或多个中间连杆元件连接。

公开(公告)号：US08651416B2

公开(公告)日：2014-02-18

申请号：US13496033

申请日：2010-09-20

Applicant: Frederic Journade ,  Laurent Lafont ,  Laurent Agostini ,  Eric Renaud ,  Delphine Jalbert

Inventor： Frederic Journade ,  Laurent Lafont ,  Laurent Agostini ,  Eric Renaud ,  Delphine Jalbert

IPC: B64D27/00

CPC classification number: B64D27/18 ,  B64D2027/005 ,  B64D2027/264 ,  Y02T50/44 ,  Y02T50/66

Abstract: An engine is mounted on a structure by an intermediate structure assembled by flanges, to the structure and to the engine, where a rigid structure connects the flanges. This arrangement enables design of the structure to be simplified while allowing a substantial overhang when it is sought to mount the engine by the plane of its center of gravity, while being obliged to move the mounting structure away from it. The intermediate structure is resistant to forces resulting from the overhang, and also allows assemblies that are favorable to a balanced transmission of forces to the structure and a satisfactory ability to filter vibrations.

Abstract translation: 发动机通过由法兰组装的中间结构安装在结构上，结构和发动机，其中刚性结构连接凸缘。 这种布置使得能够简化结构的设计，同时在寻求通过其重心的平面安装发动机的同时允许大的悬垂，同时不得不使安装结构远离其移动。 中间结构抵抗由突出部产生的力，并且还允许有利于平衡地传递结构的力的组件和令人满意的过滤振动的能力。

公开(公告)号：US08613405B2

公开(公告)日：2013-12-24

申请号：US13384650

申请日：2010-07-29

Applicant: Laurent Lafont

Inventor： Laurent Lafont

IPC: B64D27/26

CPC classification number: B64D27/18 ,  B64D27/26

Abstract: An assembly for an aircraft including: a mechanism attaching a primary structure of an attachment strut to a wing, forming an isostatic system; an attachment housed in a leading edge of the wing and configured to only take up forces exerted along the transverse and longitudinal directions; and an attachment including a connecting rod extending rearwardly, of which one end is connected to the primary structure and the other end is connected to the wing element, the connecting rod being offset along the vertical direction of the attachment.

Abstract translation: 一种用于飞行器的组件，包括：将附接支柱的一次结构附接到机翼的机构，形成等静压系统; 容纳在翼的前缘中并被构造成仅沿着横向和纵向方向施加的力的附件; 以及附件，其包括向后延伸的连杆，其一端连接到主结构，另一端连接到翼元件，连杆沿附件的垂直方向偏移。

公开(公告)号：US08496438B2

公开(公告)日：2013-07-30

申请号：US12709793

申请日：2010-02-22

Applicant: Laurent Lafont

Inventor： Laurent Lafont

IPC: F01D5/30

CPC classification number: F02K3/025 ,  B64C11/06 ,  F01D5/147 ,  F01D5/30 ,  F01D7/00 ,  F01D21/045 ,  F02K3/062 ,  F04D29/34 ,  F05D2260/30 ,  F05D2260/74 ,  F05D2260/79 ,  Y02T50/66 ,  Y02T50/673

Abstract: The invention concerns an aircraft turbomachine propeller comprising a plurality of blades (1) each comprising a root (20) mounted on a hub (2) rotating about the rotation axis of the propeller (I-I), and its purpose is to reduce the risks of loss of the entire blade (1) following an impact by a foreign body.To achieve this, at least one blade (1) comprises a means (30) of retaining the blade in an outwards radial direction, said retaining means (30) being engaged in a housing (5) of said blade (1) opening radially inwards at the root of the blade (20), and fixed in translation in said outwards radial direction.

Abstract translation: 本发明涉及一种包括多个叶片（1）的飞机涡轮机推进器，每个叶片包括安装在围绕螺旋桨（II）的旋转轴线旋转的轮毂（2）上的根部（20），并且其目的是降低 整个叶片（1）在异物撞击后的损失。 为了实现这一点，至少一个叶片（1）包括将叶片保持在向外径向的装置（30），所述保持装置（30）接合在所述叶片（1）的径向向内开口的壳体（5）中 在叶片（20）的根部处，并且以所述向外的径向方向固定成平移。

公开(公告)号：US08083176B2

公开(公告)日：2011-12-27

申请号：US12067190

申请日：2006-09-22

Applicant: Laurent Lafont ,  Frederic Journade ,  Eric Renaud

Inventor： Laurent Lafont ,  Frederic Journade ,  Eric Renaud

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/266

Abstract: A method to mount an aircraft engine on a rigid structure of an engine mount, includes securing, on the structure, an attachment body for an engine attachment, the attachment body configured to lie against a contact surface of the rigid structure oriented forwardly, and secured to the structure by at least one shear pin passing through a first and a second primary orifice. The securing of the body includes: pre-positioning the engine relative to the engine mount to place the first orifice opposite the second orifice, and inserting a pin fitted with a convex centering head through the two orifices, so that the pin forms the shear pin.

Abstract translation: 一种将飞机发动机安装在发动机支架的刚性结构上的方法，包括在所述结构上固定用于发动机附件的附接体，所述附接体构造成抵靠所述刚性结构向前定向的接触表面并且被固定 通过穿过第一和第二主孔的至少一个剪切销到结构。 主体的固定包括：相对于发动机支架预先定位发动机，以将第一孔与第二孔相对，并且通过这两个孔插入装配有凸起定心头的销，使得销形成剪切销 。

公开(公告)号：US08070093B2

公开(公告)日：2011-12-06

申请号：US12089058

申请日：2006-06-29

Applicant: Lionel Diochon ,  Jean-Michel Cetout ,  Laurent Lafont ,  David Chartier

Inventor： Lionel Diochon ,  Jean-Michel Cetout ,  Laurent Lafont ,  David Chartier

IPC: B64D27/26

CPC classification number: B64D27/18 ,  B64D27/26 ,  B64D2027/264 ,  Y02T50/44

Abstract: A mount for an aircraft turbojet engine. The mount includes a central box formed by an assembly of two side panels joined via transverse ribs and two side boxes secured to a forward part of the box and arranged either side thereof, each side box including an aft closure frame. One of the ribs forming the box includes two side extensions made in a single piece with the rib and respectively projecting from the two side panels outwardly from the box, the two extensions being fixedly mounted on the frame of each of the two side boxes, respectively.

Abstract translation: 飞机涡轮喷气发动机的安装座。 安装座包括一个由两个侧板组成的中央箱，该两个侧板通过横向肋条连接，两个侧箱固定在箱体的前部，并设置在其两侧，每个侧箱包括一个后盖框架。 形成盒子的肋条之一包括两个侧边延伸部，分别与肋一体成型并分别从盒子的两个侧面板向外突出，两个延伸部分别固定地安装在两个侧盒中的每一个的框架上 。

公开(公告)号：US20100209254A1

公开(公告)日：2010-08-19

申请号：US12705229

申请日：2010-02-12

Applicant: Laurent LAFONT

Inventor： Laurent LAFONT

IPC: B63H1/20 ,  B63H1/26

CPC classification number: F04D29/324 ,  B64C11/205 ,  B64C11/24 ,  B64C11/26 ,  B64C11/48 ,  B64D2027/026 ,  F01D5/16 ,  F02K3/072 ,  F04D27/0292 ,  F04D29/023 ,  F05D2230/53 ,  F05D2300/603 ,  F05D2300/612 ,  Y02T50/66 ,  Y02T50/672 ,  Y02T50/673

Abstract: The invention relates to a vane (200) for an aircraft turbine engine receiver comprising a blade (14) having an aerodynamic shell (24) enveloping a principal hollow structural core (34) extending in the direction of wingspan of the blade. According to the invention, the vane further comprises a secondary structural assembly (34′) enveloped by the hollow core (34) and extending also in the direction of wingspan, as well as a first coating made of shock-absorbing material (50) arranged between a longeron (44) of the core (34) and the assembly (34′), and a second coating made of shock-absorbing material (52) arranged between another longeron (38) of the core (34), and this same assembly (34′).

Abstract translation: 本发明涉及一种用于飞行器涡轮发动机接收器的叶片（200），其包括具有空气动力学外壳（24）的叶片（14），该空气动力学壳体包围沿叶片的翼展方向延伸的主要中空结构芯（34）。 根据本发明，叶片还包括由中空芯（34）包围并沿翼展方向延伸的第二结构组件（34'），以及由减震材料（50）制成的第一涂层 在芯体（34）的长孔（44）和组件（34'）之间的第二涂层以及设置在芯体（34）的另一长孔（38）之间的由减震材料（52）制成的第二涂层， 组件（34'）。

公开(公告)号：US20100193627A1

公开(公告)日：2010-08-05

申请号：US11525018

申请日：2006-09-22

Applicant: Laurent Lafont

Inventor： Laurent Lafont

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D27/18 ,  B64D2027/264

Abstract: The invention relates to an assembly for an aircraft comprising a wing element (2) and a suspension pylon (4) for an engine (10) under the wing element, the suspension pylon (4) comprising a rigid structure (6) forming a box provided with an aft closing element (28), and the wing element (2) having a forward spar (34) extending substantially parallel to a leading edge (30) of the wing element. According to the invention, the rigid structure is assembled on the wing element such that the aft closing element bears in contact with the forward spar (34).

Abstract translation: 本发明涉及一种用于飞行器的组件，其包括翼元件（2）和用于机翼元件下方的发动机（10）的悬挂塔（4），悬架塔（4）包括刚性结构（6），形成箱 设置有后关闭元件（28），并且翼元件（2）具有基本上平行于翼元件的前缘（30）延伸的前翼梁（34）。 根据本发明，刚性结构组装在翼元件上，使得后关闭元件与前翼梁（34）接触。

公开(公告)号：US20080296430A1

公开(公告)日：2008-12-04

申请号：US12064916

申请日：2006-08-31

Applicant: Stéphane Combes ,  Stephane Levert ,  Laurent Lafont ,  Dominique Moreau

Inventor： Stéphane Combes ,  Stephane Levert ,  Laurent Lafont ,  Dominique Moreau

IPC: B64D27/00

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely.

Abstract translation: 一种被配置为将再生棒连接到飞行器发动机支架的刚性结构上的装置，包括滑动地安装在支架的第一通道中的销系统，以允许其沿着第一纵向轴线从第一方向从正常延伸位置 到缩回位置，其中销系统在该相同的支架内缩回，反之亦然。 该布置还包括由该系统承载的销销延伸构件，并且构造成在从正常缩回位置到延伸位置的第二方向上平行于纵向轴线移动，销延伸构件连接到系统并突出超出 系统，而相反。