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公开(公告)号：US09828877B2
公开(公告)日：2017-11-28
申请号：US14116597
申请日：2012-05-07
CPC分类号： F01D25/243 , F01D25/162 , F02C7/20 , Y02T50/672
摘要： A bypass turbojet engine including a cylindrical cold stream flow path supported by link rods which are attached to a cylindrical outer shell ring of an exhaust case at attachment points. The attachment points for the exhaust case are crevice mounts including lugs that extend radially from the outer shell ring, a bore of the crevice mounts being directed in a direction of generatrices of the outer shell ring.
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公开(公告)号：US09169743B2
公开(公告)日：2015-10-27
申请号：US13505942
申请日：2010-11-10
CPC分类号： F01D25/28 , F01D25/162 , F02K1/80 , F05D2260/30 , Y02T50/672
摘要： A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.
摘要翻译： 用于飞行器涡轮机的两个部件之间的金属环形连接结构，具有包括两个主分支的任意半部分和形成从纵向轴线沿径向方向开口的第一U形状的基部以及形成第二U的两个次级分支 两个主要分支之一在纵向方向上开放。 第一个U的主要和次要分支和基础是单件制成的。
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3.发明申请TURBOSHAFT ENGINE ATTACHED TO A PYLON OF THE FUSELAGE OF AN AIRCRAFT BY A FAILSAFE SUSPENSION SYSTEM 有权涡轮发动机连接到由FAILSAFE悬挂系统组成的飞机的FYLON OF PYLON公开(公告)号：US20130099051A1
公开(公告)日：2013-04-25
申请号：US13703969
申请日：2011-06-09
申请人： Francois Bellabal , Guilhem Seize , Thomas Vincent
发明人： Francois Bellabal , Guilhem Seize , Thomas Vincent
IPC分类号： B64D27/26
摘要： A suspension system including a front suspension plane located at an intermediate turboshaft engine casing and connecting same to a pylon, a rear suspension plane located at an exhaust casing of the turboshaft engine and connecting same to the pylon, and a failsafe intermediate suspension plane located between the front and rear planes and including at least one connecting rod connecting the turboshaft engine having a structural outer casing to the pylon, the connecting rod mounted on the turboshaft engine with a predetermined clearance that renders the connecting rod inoperable while the suspension system of the rear plane is operating. The connecting rod is advantageously arranged between the outer casing and the pylon, and an element made of a flexible material is combined with the connecting rod to create the predetermined clearance by an elastically deformable nature thereof.
摘要翻译： 一种悬架系统，包括位于中间涡轮轴发动机壳体并连接到塔架的前悬架平面，位于所述涡轮轴发动机的排气外壳处并连接到所述塔架的后悬架平面，以及位于 前后平面并且包括将具有结构外壳的涡轮轴发动机连接到塔架的至少一个连杆，连接杆以预定间隙安装在涡轮轴发动机上，使得连杆在后部的悬架系统上不可操作 飞机正在运行。 连接杆有利地布置在外壳和塔之间，并且由柔性材料制成的元件与连接杆组合以通过其可弹性变形的特性产生预定的间隙。
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4.发明申请SYSTEM AND METHOD FOR MEASURING FATIGUE FOR MECHANICAL COMPONENTS OF AN AIRCRAFT AND AIRCRAFT MAINTENANCE METHOD 有权用于测量飞机和飞机维护方法的机械部件的疲劳的系统和方法公开(公告)号：US20120226409A1
公开(公告)日：2012-09-06
申请号：US13509874
申请日：2010-11-15
申请人： Guilhem Seize
发明人： Guilhem Seize
IPC分类号： G01B7/16
CPC分类号： G01N3/32 , G01M5/0033 , G01N2203/0073 , G01N2203/0286 , G07C5/006 , G07C5/0841
摘要： A system for measuring fatigue of a component of an aircraft subject to mechanical stresses includes: a plurality of stress sensors mounted on the component, each sensor being configured to detect a predetermined mechanical stress threshold and to deliver a data signal representative of exceeding of the threshold; and a mechanism for recording the data and the sensors configured to detect different stress thresholds so as to make it possible to calculate, on the basis of the data recorded by the system, an estimation of fatigue of the component due to the mechanical stresses. It is thus possible to optimize overhaul of the components.
摘要翻译： 用于测量经受机械应力的飞行器部件的疲劳的系统包括：安装在部件上的多个应力传感器，每个传感器被配置为检测预定的机械应力阈值，并传递代表超过阈值的数据信号 ; 以及用于记录数据和传感器的机构，其被配置为检测不同的应力阈值，以便能够根据系统记录的数据计算由于机械应力引起的部件疲劳的估计。 因此可以优化组件的大修。
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公开(公告)号：US20120219415A1
公开(公告)日：2012-08-30
申请号：US13505942
申请日：2010-11-10
CPC分类号： F01D25/28 , F01D25/162 , F02K1/80 , F05D2260/30 , Y02T50/672
摘要： A metallic annular connection structure between two parts for an aircraft turbomachine, with an arbitrary half-section including two primary branches and a base forming a first U opening up in the radial direction from a longitudinal axis, and two secondary branches forming a second U with one of the two primary branches opening up in the longitudinal direction. The primary and secondary branches and the base of the first U are made in a single piece.
摘要翻译： 用于飞行器涡轮机的两个部件之间的金属环形连接结构，具有包括两个主分支的任意半部分和形成从纵向轴线沿径向方向开口的第一U形状的基部以及形成第二U的两个次级分支 两个主要分支之一在纵向方向上开放。 第一个U的主要和次要分支和基础是单件制成的。
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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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7.发明授权Dual-flow turbomachine for aircraft, including structural means of rigidifying the central casing 有权用于飞机的双流涡轮机，包括硬化中央壳体的结构手段公开(公告)号：US09157334B2
公开(公告)日：2015-10-13
申请号：US13504009
申请日：2010-11-02
CPC分类号： F01D25/24 , F01D25/28 , F02C7/00 , F02K3/06 , F04D29/403 , F05D2240/14 , F05D2250/30
摘要： A turbomachine for an aircraft including a mechanism forming a case fitted in a rear extension of an inner ferrule of an intermediate casing, and positioned around a central casing. The mechanism includes a structural upstream ferrule assembled on the inner ferrule and defining a front portion of a surface internally delimiting a secondary vein, and a main case extending on the upstream ferrule towards the rear. The turbomachine further includes a structural mechanism rigidifying the central casing, surrounded by the case, and extending towards the rear between the upstream ferrule and the central casing on which these mechanisms are assembled.
摘要翻译： 一种用于飞行器的涡轮机，其包括形成安装在中间壳体的内套圈的后延伸部中并围绕中心壳体定位的壳体的机构。 该机构包括组装在内套圈上的结构上游套圈，并且限定内部限定副静脉的表面的前部，以及在上游套圈上向后延伸的主壳体。 涡轮机还包括结构机构，该结构机构硬化中央壳体，被壳体包围，并且在上游套圈和中心壳体之间向后延伸，在这些组件上组装有这些机构。
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8.发明申请LINK BETWEEN THE EXHAUST CASING AND A STRUCTURAL RING OF THE FAN DUCT OF A JET ENGINE 有权喷气发动机风扇结构与结构环之间的联系公开(公告)号：US20130014515A1
公开(公告)日：2013-01-17
申请号：US13577550
申请日：2011-02-09
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D21/045 , F01D25/24 , F01D25/28 , F02K3/06 , F05D2240/14 , Y02T50/671
摘要： An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken.
摘要翻译： 一种组件，包括排气壳体的外圈，风扇通道的外部管道的结构环和相对于排气壳体的外圈同心的双流喷气式发动机，以及至少一个第一和第二 连接臂或杆通过一端附接到排气套的外圈并且另一端附接到结构环而形成超静力连杆。 由第一连接臂或杆形成的连杆被构造成当超过预定负载时断裂，并且第二连接臂或杆构造成在连杆断裂时在环之间形成力传递路径。
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9.发明授权Link between the exhaust casing and a structural ring of the fan duct of a jet engine 有权排气套管与喷气发动机的风扇管道的结构环之间的连接公开(公告)号：US09121347B2
公开(公告)日：2015-09-01
申请号：US13577550
申请日：2011-02-09
CPC分类号： F02C7/20 , F01D21/045 , F01D25/24 , F01D25/28 , F02K3/06 , F05D2240/14 , Y02T50/671
摘要： An assembly including an outer ring of an exhaust casing, a structural ring of an external duct of a fan channel and of a two-flow jet engine that is concentric relative to the outer ring of the exhaust casing, and at least one first and second linking arm or rod forming a hyperstatic link by being attached by one end to the outer ring of the exhaust casing and, by the other end, to the structural ring. The link formed by the first linking arm or rod is configured to break when a predetermined load is exceeded, and the second linking arm or rod is configured to form a force-transmission path between the rings when the link is broken.
摘要翻译： 一种组件，包括排气壳体的外圈，风扇通道的外部管道的结构环和相对于排气壳体的外圈同心的双流喷气式发动机，以及至少一个第一和第二 连接臂或杆通过一端附接到排气套的外圈并且另一端附接到结构环而形成超静力连杆。 由第一连接臂或杆形成的连杆被构造成当超过预定负载时断裂，并且第二连接臂或杆构造成在连杆断裂时在环之间形成力传递路径。
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10.发明授权Turboshaft engine attached to a pylon of the fuselage of an aircraft by a failsafe suspension system 有权涡轮轴发动机通过故障安全悬挂系统连接到飞机机身的塔架上公开(公告)号：US09067688B2
公开(公告)日：2015-06-30
申请号：US13703969
申请日：2011-06-09
申请人： Francois Bellabal , Guilhem Seize , Thomas Vincent
发明人： Francois Bellabal , Guilhem Seize , Thomas Vincent
摘要： A suspension system including a front suspension plane located at an intermediate turboshaft engine casing and connecting same to a pylon, a rear suspension plane located at an exhaust casing of the turboshaft engine and connecting same to the pylon, and a failsafe intermediate suspension plane located between the front and rear planes and including at least one connecting rod connecting the turboshaft engine having a structural outer casing to the pylon, the connecting rod mounted on the turboshaft engine with a predetermined clearance that renders the connecting rod inoperable while the suspension system of the rear plane is operating. The connecting rod is advantageously arranged between the outer casing and the pylon, and an element made of a flexible material is combined with the connecting rod to create the predetermined clearance by an elastically deformable nature thereof.
摘要翻译： 一种悬架系统，包括位于中间涡轮轴发动机壳体并连接到塔架的前悬架平面，位于所述涡轮轴发动机的排气外壳处并连接到所述塔架的后悬架平面，以及位于 前后平面并且包括将具有结构外壳的涡轮轴发动机连接到塔架的至少一个连杆，连接杆以预定间隙安装在涡轮轴发动机上，使得连杆在后部的悬架系统上不可操作 飞机正在运行。 连接杆有利地布置在外壳和塔之间，并且由柔性材料制成的元件与连接杆组合以通过其可弹性变形的特性产生预定的间隙。
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