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公开(公告)号：US20120119056A1
公开(公告)日：2012-05-17
申请号：US13387534
申请日：2010-07-27
IPC分类号： B64D27/26
摘要： A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibres. In one embodiment, the beam takes a form of a circle arc.
摘要翻译： 一种用于将涡轮轴发动机悬挂在飞行器结构上的梁，包括构造成固定到飞机结构的第一连接机构和构造成固定到发动机的至少一个第二连接机构。 梁至少部分由包括增强纤维的金属基复合材料制成。 在一个实施例中，光束采取圆弧的形式。
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公开(公告)号：US09321537B2
公开(公告)日：2016-04-26
申请号：US13387534
申请日：2010-07-27
摘要： A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibers. In one embodiment, the beam takes a form of a circle arc.
摘要翻译： 一种用于将涡轮轴发动机悬挂在飞行器结构上的梁，包括构造成固定到飞机结构的第一连接机构和构造成固定到发动机的至少一个第二连接机构。 梁至少部分由包括增强纤维的金属基复合材料制成。 在一个实施例中，光束采取圆弧的形式。
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3.发明授权公开(公告)号：US08707669B2
公开(公告)日：2014-04-29
申请号：US13395219
申请日：2010-09-13
CPC分类号： F16C7/02 , Y10T74/2142 , Y10T74/2144 , Y10T156/1052
摘要： The present invention relates to a method of fabricating a metal link rod (6) that is longitudinally reinforced in its thickness by fiber reinforcement (2), the method comprising the following steps: making a metal blank including at least one longitudinal housing (11, 12) leading into an edge face of the blank; inserting fiber reinforcement (2) in the housing; connecting the fiber reinforcement to the blank by metal diffusion around the fibers of the fiber reinforcement (2); and finishing the blank in order to obtain a link rod (6). The invention also provides a link rod having a metal matrix in which reinforcing fibers are embedded that extend on either side of a longitudinal axis (X) of the link rod, the fibers leading into an edge face of the link rod.
摘要翻译： 本发明涉及一种制造金属连杆（6）的方法，该金属连杆通过纤维增强件（2）在其厚度上纵向增强，该方法包括以下步骤：制造金属坯料，其包括至少一个纵向壳体（11， 12）进入坯料的边缘面; 将纤维增强件（2）插入壳体中; 通过在纤维增强件（2）的纤维周围的金属扩散将纤维增强材料连接到坯料上; 并整理坯料以获得连杆（6）。 本发明还提供一种具有金属基体的连杆，其中嵌入增强纤维，其在连杆的纵向轴线（X）的两侧延伸，纤维通向连杆的边缘面。
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公开(公告)号：US20130251519A1
公开(公告)日：2013-09-26
申请号：US13820545
申请日：2011-09-05
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D9/042 , F04D29/023 , F04D29/522 , F04D29/542 , F04D29/644 , F05D2300/43 , F05D2300/603 , Y02T50/672
摘要： A turbojet casing adapted to receive a plurality of vanes, the casing including attachment means (21, 30) for attaching one end of each vane to the casing, the casing being characterized in that the attachment means extend on a face of the casing facing away from the vanes, the casing including orifices (26) for passing the ends of the vanes so that they can co-operate with the attachment means of the casing. A turbojet including such a casing.
摘要翻译： 适于接收多个叶片的涡轮喷气发动机壳体，所述壳体包括用于将每个叶片的一端附接到所述壳体的附接装置（21,30），所述壳体的特征在于，所述附接装置在所述壳体的面向外延伸 来自叶片的壳体包括用于使叶片的端部通过的孔口（26），使得它们可以与壳体的附接装置协同操作。 包括这种壳体的涡轮喷气发动机。
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5.发明申请METHOD FOR MAKING AN ARM FOR A HINGED STRUCTURE SUCH AS A ROCKER ARM FOR AN AIRCRAFT LANDING-GEAR STRUCTURE 审中-公开用于制造用于铰链结构的ARM的方法，例如作为用于飞机起落架结构的摇臂臂公开(公告)号：US20130062012A1
公开(公告)日：2013-03-14
申请号：US13574327
申请日：2011-01-19
申请人： Richard Masson , Patrick Dunleavy
发明人： Richard Masson , Patrick Dunleavy
IPC分类号： B32B37/14
CPC分类号： B29C70/72 , B29C70/48 , B29L2031/75 , B64C25/02 , F16C7/026 , F16C2326/43
摘要： The invention relates to a method for making an arm for a hinged structure such as an aircraft landing gear structure, this arm comprising a main body (30; 130; 230) extending in a longitudinal direction (AP; BP; CP), and including an interface (13; 113; 213) such as a yoke radially protruding from the main body, this method including the steps of: making an insert (11; 211) including a base (12; 212) carrying the interface; making a mandrel (10; 110) integrating the base of the insert so that a portion of the external surface of this mandrel is delimited by a portion of the external face (17; 217) of the base of the insert; applying one or more layers of reinforcing fibers (31; 131; 231) around the mandrel and over all its length, so that each layer has the interface (13; 113; 213) passing through it without covering the interface; injecting resin into the layer or layers of reinforcing fibers (31; 131; 231) and at the level of the area of contact (32) of these layers (31) with the external face (17; 217) of the base; and polymerizing the resin to bind rigidly the layers of reinforcing fibers and the base of the insert.
摘要翻译： 本发明涉及一种用于制造诸如飞机起落架结构的铰接结构的臂的方法，该臂包括沿纵向（AP; BP; CP）延伸的主体（30; 130; 230），并且包括 一个诸如从主体径向突出的轭的接口（13; 113; 213），该方法包括以下步骤：制造包括承载界面的基座（12; 212）的插入件（11; 211） 制造将所述插入件的底部整合的心轴（10; 110），使得所述心轴的外表面的一部分由插入件的基部的外表面（17; 217）的一部分限定; 将一层或多层增强纤维（31; 131; 231）围绕所述心轴并且在其所有长度上施加，使得每层具有通过它的界面（13; 113; 213）而不覆盖界面; 将树脂注入到增强纤维（31; 131; 231）的层中，并且在这些层（31）的接触区域（32）的水平处与基底的外表面（17; 217）注入; 并且使树脂聚合以将刚性地粘合增强纤维层和插入物的底部。
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6.发明申请公开(公告)号：US20120124838A1
公开(公告)日：2012-05-24
申请号：US13378815
申请日：2010-06-14
申请人： Patrick Dunleavy , Jean-Michel Patrick Maurice Franchet , Gilles Charles Casimir Klein , Richard Masson
发明人： Patrick Dunleavy , Jean-Michel Patrick Maurice Franchet , Gilles Charles Casimir Klein , Richard Masson
IPC分类号： B23P15/00
CPC分类号： C22C14/00 , C22C47/04 , C22C47/064 , Y10T29/4932 , Y10T29/49336 , Y10T29/49337 , Y10T29/4949 , Y10T29/49801
摘要： A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.
摘要翻译： 通过包括复合材料的绕组来加强轴对称环形金属部件的方法。 制备该部件的金属坯料，其中形成有开口成同轴的内表面的空腔，并且具有从内侧向外侧减小的轴向范围的右侧横截面，增强纱线被卷绕 空腔，空腔关闭，组件经受热等静压处理，坯料加工得到最终部件。
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公开(公告)号：US09726186B2
公开(公告)日：2017-08-08
申请号：US14005471
申请日：2012-03-15
CPC分类号： F04D25/00 , F02C3/113 , F02C7/36 , F02K3/06 , F05D2260/4023 , F05D2260/40311 , F05D2260/902 , Y02T50/671
摘要： A method and system improving energy efficiency of a turbojet engine by optimizing rotating speed of a fan and operability of an engine, by freeing the fan from exclusive control of a low-pressure (LP) shaft by providing combined control with a high-pressure (HP) shaft when cruising power has been reached. The turbojet engine include at least one LP turbine and one HP turbine coupled to coaxial LP shafts and HP shafts, respectively, which can drive LP and HP compressors, respectively. The LP compressors include a fan that forms a first primary air-intake compression stage. The LP and HP shafts are mounted on one of two driving mechanisms, an inner ring gear, and a planet carrier for a planetary gear train for driving the fan, the HP shaft being mounted on a disengagement mechanism and the fan being coupled to the planetary gear train via an outer driven ring gear.
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8.发明授权Process for manufacturing a mechanical member made of a composite having increased mechanical strength 有权用于制造由具有增加的机械强度的复合材料制成的机械构件的方法公开(公告)号：US08850942B2
公开(公告)日：2014-10-07
申请号：US13819258
申请日：2011-08-30
申请人： Richard Masson , Patrick Dunleavy
发明人： Richard Masson , Patrick Dunleavy
CPC分类号： D04C1/06 , B29C70/222 , B29C70/32 , B29C70/48 , D04C1/02 , D04C3/48 , D10B2403/02411 , D10B2505/02 , F16C7/026
摘要： A method of fabricating a mechanical member for aircraft, including a plurality of operations of braiding and depositing layers of braided reinforcing fibers on a mandrel (11) by using braiding machine. Each operation comprises braiding a braided layer and depositing it by moving the mandrel (11) along a central axis of the braiding machine. Each of the various superposed braided layers comprises both longitudinal fibers (12, 12G) that are parallel to a main direction of the mandrel (11), and interlacing fibers that are inclined. At least one operation is configured to form and deposit a braided layer having, in at least one cross-section of the member, a density of longitudinal fibers that differs depending on whether consideration is given to one angular region (S1) or another angular region (S2) of the same extent around the center of gravity (G) of the mandrel (11) in the section under consideration.
摘要翻译： 一种制造用于飞机的机械构件的方法，包括通过使用编织机在芯棒（11）上编织和沉积编织增强纤维层的多个操作。 每个操作包括编织编织层并通过沿编织机的中心轴移动心轴（11）来沉积编织层。 各个重叠编织层中的每一个包括平行于心轴（11）的主方向的纵向纤维（12,12G）和倾斜的交织纤维。 至少一个操作被配置成形成和沉积编织层，所述编织层在构件的至少一个横截面中具有根据是否考虑到一个角度区域（S1）或另一个角度区域而不同的纵向纤维的密度 （S2）在所考虑的部分中围绕心轴（11）的重心（G）的相同程度。
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9.发明授权Method for making a composite metal part having inner reinforcements in the form of fibers, blank for implementing same and metal part thus obtained 有权制造复合金属部件的方法，所述复合金属部件具有纤维形式的内部增强件，用于实现其的坯料和由此获得的金属部件公开(公告)号：US08776343B2
公开(公告)日：2014-07-15
申请号：US13509022
申请日：2010-11-24
摘要： During implementing a composite metal part by compaction of an insert having reinforcing fibers in a metal body or container, gas used for compaction may enter the cavity formed in the container for receiving the insert between a lid covering the insert and the container, which can prevent or degrade compaction and diffusion welding of fiber sheaths of the insert therebetween and/or with walls of the cavity. To solve this problem, the present method includes initiating isostatic compaction by a phase including raising and maintaining temperature, followed by a phase including hot-feeding pressurized gas, and machining an assembly to obtain the part. The temperature raising phase includes a diffusion pre-welding of material rigidly connecting the pressure-adjusted walls of the lid and the container. The method can be used for designing parts having a tensile and compression resistance, such as parts for aircraft landing gear.
摘要翻译： 在通过在金属体或容器中压制具有增强纤维的插入件来实现复合金属部件时，用于压实的气体可以进入形成在容器中的空腔中，用于在覆盖插入件的盖子和容器之间接收插入件，这可以防止 或降低其间的插入物的纤维鞘和/或腔的壁的压实和扩散焊接。 为了解决这个问题，本方法包括通过包括升温和保持温度的相进行等静压缩，接着是包括加热加压气体的相，并加工组件以获得部件。 升温阶段包括将盖的压力调节壁和容器刚性连接的材料的扩散预焊接。 该方法可用于设计具有拉伸和抗压缩性的部件，例如用于飞机起落架的部件。
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10.发明申请公开(公告)号：US20110129639A1
公开(公告)日：2011-06-02
申请号：US12997785
申请日：2009-06-12
申请人： Patrick Dunleavy , Richard Masson
发明人： Patrick Dunleavy , Richard Masson
CPC分类号： B29C70/222 , B29C70/48 , B29C70/865 , B29K2077/10 , B29K2707/04 , B29K2709/08 , B29L2031/06 , D04C3/48 , F16C7/026 , Y10T428/24008
摘要： A process for manufacturing a structural part made of an organic matrix composite including: production of a fibrous structure, forming a preform by braiding rovings of a fibrous material on a mandrel that includes a reinforcement in its axial extension, impregnation of the preform with an organic resin; and curing of this resin, the reinforcement, forming the cover, having a bore with an axis perpendicular to the axis for housing a connecting member. Barbs, some of which are projecting, are incorporated into the reinforcement over at least part of the surface of which lying on either side of the bore, the braiding being carried out around the barbs so that the rovings at least partly criss-cross around the barbs.
摘要翻译： 一种用于制造由有机基质复合材料制成的结构件的方法，包括：生产纤维结构体，通过将纤维材料的粗纱编织在包括其轴向延伸的增强材料的心轴上形成预型体，用有机物浸渍预成型体 树脂; 以及固化该树脂，加强件，形成盖子，具有垂直于轴线的轴孔以容纳连接构件。 其中一些突出的倒钩在其位于孔的任一侧的表面的至少一部分上并入加强件中，编织物围绕倒钩进行，使得粗纱至少部分地绕着 倒钩
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