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    SECONDARY-AIR NOZZLE OF A TWO-FLOW JET ENGINE HAVING SEPARATED FLOWS INCLUDING A GRID THRUST REVERSER
    2.
    发明申请
    SECONDARY-AIR NOZZLE OF A TWO-FLOW JET ENGINE HAVING SEPARATED FLOWS INCLUDING A GRID THRUST REVERSER 审中-公开
    具有分离流量的双流喷射发动机的二次空气喷嘴，包括一个反向扭矩

    公开(公告)号：US20130032642A1

    公开(公告)日：2013-02-07

    申请号：US13577554

    申请日：2011-02-04

    申请人： Stephane Bensilum ,  Jean Bertucchi

    发明人： Stephane Bensilum ,  Jean Bertucchi

    IPC分类号： B64D33/04

    CPC分类号： F02K1/72

    摘要： A secondary-air nozzle of a two-flow jet engine having separated flows including an annular cowl element translatably mobile in an axial direction between an upstream retracted position allowing the engine to operate under direct thrust and a downstream extended position, and a grid thrust reverser including cylindrical ring sectors coaxial with the cowl element, including blades with a radial setting, and axially separated to provide radial guide passages therebetween, the cowl element opening the radial guide passages in the downstream extended position through the thrust reverser grids. The radius of the ring sectors forming the grids is not constant around the circumference of the cowl element, the radius of transverse cuts of at least one of the walls not being constant, when moving around the circumference of the cowl element, the cuts being made between the upstream edge of the cowl element and the downstream edge thereof.

    摘要翻译： 双流喷气发动机的二次空气喷嘴具有分离的流动，其包括环形整流罩元件，该环形整流罩元件可在允许发动机在直接推力和下游延伸位置下操作的上游缩回位置之间沿轴向方向可移动地移动;以及网格推力反向器 包括与整流罩元件同轴的圆柱形环段，包括具有径向设置的叶片，并且轴向分离以在其间提供径向引导通道，整流罩元件通过推力反向器网格在下游延伸位置打开径向引导通道。 形成网格的环形部分的半径在整流罩元件的圆周周围不是恒定的，当围绕整流罩元件的圆周移动时，至少一个壁的横向切口的半径不恒定，切割被制成 在整流罩元件的上游边缘和其下游边缘之间。

    Pipe having an upstream core having a sharp curvature
    3.
    发明授权
    Pipe having an upstream core having a sharp curvature 有权
    具有上游芯的管具有尖锐的曲率

    公开(公告)号：US09341082B2

    公开(公告)日：2016-05-17

    申请号：US14003180

    申请日：2012-03-02

    申请人： Stephane Emmanuel Daniel Bensilum ,  Jean Bertucchi ,  Mathieu Gaillot

    发明人： Stephane Emmanuel Daniel Bensilum ,  Jean Bertucchi ,  Mathieu Gaillot

    IPC分类号： F01D1/00 ,  F01D25/24 ,  B64D33/04 ,  F02K1/00 ,  F02K1/82

    CPC分类号： F01D25/24 ,  B64D33/04 ,  F02K1/00 ,  F02K1/82 ,  F05D2250/71 ,  F05D2250/711 ,  Y02T50/671

    摘要： A turbine engine pipe having a longitudinal axis, which, at an upstream end thereof, includes an outer wall and a core, only an upstream portion of which is surrounded by the outer wall. The boundary between the upstream portion and a downstream portion is defined by the intersection between the core and the surface formed by bisectors of acute angles formed by straight lines perpendicular to the outer wall and straight lines perpendicular to an outer surface of the core passing through the downstream end of the outer wall. The outer surface of the downstream portion of the core has a sharply curved convex region close to the boundary, the region having a radius of curvature in a radial plane of less than 30 times the radius of the core at the boundary, and a first slightly curved region between the boundary and the sharply curved convex region.

    摘要翻译： 一种具有纵向轴线的涡轮发动机管道，其在其上游端包括外壁和芯部，只有其上游部分被外壁包围。 上游部分和下游部分之间的边界由芯和由垂直于外壁的直线形成的锐角的平分线形成的表面和垂直于芯的外表面的直线形成的表面之间的交点限定， 外壁的下游端。 芯的下游部分的外表面具有接近边界的急剧弯曲的凸起区域，该区域在径向平面中的曲率半径小于边界处的芯的半径的30倍，并且第一稍微 边界与锐曲的凸区域之间的弯曲区域。

    Assembly formed by a turbine engine and a system for attaching it to an aircraft structure
    4.
    发明授权
    Assembly formed by a turbine engine and a system for attaching it to an aircraft structure 有权
    由涡轮发动机和用于将其附接到飞行器结构的系统形成的组件

    公开(公告)号：US09488106B2

    公开(公告)日：2016-11-08

    申请号：US14241246

    申请日：2012-08-24

    申请人： Mathieu Gaillot ,  Jean Bertucchi ,  Matthieu Leyko

    发明人： Mathieu Gaillot ,  Jean Bertucchi ,  Matthieu Leyko

    IPC分类号： F02C7/20 ,  B64C7/02 ,  B64D27/26

    CPC分类号： F02C7/20 ,  B64C7/02 ,  B64D27/26 ,  B64D2027/266

    摘要： In an assembly including a bypass turbine engine and an attachment system attaching the turbine engine to an aircraft structure, the attachment system includes a mast, at least two rear attachments connecting the mast to two rear attachment points of the turbine engine, and a rear covering covering the rear attachments and providing a streamlined fairing. The rear covering includes two side walls, each including a first portion extending along and in proximity of the mast and extending rearwards, and a second portion projecting sideways relative to the first portion towards its outside, to cover the rear attachments. Each second portion is substantially a bulge and is connected to the first portion along a curved connection line extending between front and rear points situated substantially level with an inner longitudinal edge of the first portion to minimize the impact on a flow of bypass stream leaving the bypass passage.

    摘要翻译： 在包括旁通涡轮发动机和将涡轮发动机附接到飞行器结构的附接系统的组件中，附接系统包括桅杆，将桅杆连接到涡轮发动机的两个后连接点的至少两个后部附件和后盖 覆盖后部附件并提供流线型整流罩。 后盖包括两个侧壁，每个侧壁包括沿着桅杆延伸并且在桅杆附近向后延伸的第一部分，以及相对于第一部分朝向其外部侧向突出的第二部分，以覆盖后部附件。 每个第二部分基本上是凸起的并且沿着弯曲的连接线连接到第一部分，弯曲的连接线在前部和后部点之间延伸，其基本上与第一部分的内部纵向边缘大致水平，以最小化对离开旁路的旁路流的影响 通道。

    ASSEMBLY FORMED BY A TURBINE ENGINE AND A SYSTEM FOR ATTACHING IT TO AN AIRCRAFT STRUCTURE
    5.
    发明申请
    ASSEMBLY FORMED BY A TURBINE ENGINE AND A SYSTEM FOR ATTACHING IT TO AN AIRCRAFT STRUCTURE 有权
    涡轮发动机组装和连接飞机结构的系统

    公开(公告)号：US20140202169A1

    公开(公告)日：2014-07-24

    申请号：US14241246

    申请日：2012-08-24

    申请人： Mathieu Gaillot ,  Jean Bertucchi ,  Matthieu Leyko

    发明人： Mathieu Gaillot ,  Jean Bertucchi ,  Matthieu Leyko

    IPC分类号： F02C7/20

    CPC分类号： F02C7/20 ,  B64C7/02 ,  B64D27/26 ,  B64D2027/266

    摘要： In an assembly including a bypass turbine engine and an attachment system attaching the turbine engine to an aircraft structure, the attachment system includes a mast, at least two rear attachments connecting the mast to two rear attachment points of the turbine engine, and a rear covering covering the rear attachments and providing a streamlined fairing. The rear covering includes two side walls, each including a first portion extending along and in proximity of the mast and extending rearwards, and a second portion projecting sideways relative to the first portion towards its outside, to cover the rear attachments. Each second portion is substantially a bulge and is connected to the first portion along a curved connection line extending between front and rear points situated substantially level with an inner longitudinal edge of the first portion to minimize the impact on a flow of bypass stream leaving the bypass passage.

    摘要翻译： 在包括旁通涡轮发动机和将涡轮发动机附接到飞行器结构的附接系统的组件中，附接系统包括桅杆，将桅杆连接到涡轮发动机的两个后连接点的至少两个后部附件和后盖 覆盖后部附件并提供流线型整流罩。 后盖包括两个侧壁，每个侧壁包括沿着桅杆延伸并且在桅杆附近向后延伸的第一部分，以及相对于第一部分朝向其外部侧向突出的第二部分，以覆盖后部附件。 每个第二部分基本上是凸起的并且沿着弯曲的连接线连接到第一部分，弯曲的连接线在前部和后部点之间延伸，其基本上与第一部分的内部纵向边缘大致水平，以最小化对离开旁路的旁路流的影响 通道。

    PIPE HAVING AN UPSTREAM CORE HAVING A SHARP CURVATURE
    6.
    发明申请
    PIPE HAVING AN UPSTREAM CORE HAVING A SHARP CURVATURE 有权
    具有SHARP曲线的上游核心的管子

    公开(公告)号：US20130336772A1

    公开(公告)日：2013-12-19

    申请号：US14003180

    申请日：2012-03-02

    申请人： Stéphane Emmanuel Daniel Bensilum ,  Jean Bertucchi ,  Mathieu Gaillot

    发明人： Stéphane Emmanuel Daniel Bensilum ,  Jean Bertucchi ,  Mathieu Gaillot

    IPC分类号： F01D25/24

    CPC分类号： F01D25/24 ,  B64D33/04 ,  F02K1/00 ,  F02K1/82 ,  F05D2250/71 ,  F05D2250/711 ,  Y02T50/671

    摘要： A turbine engine pipe having a longitudinal axis, which, at an upstream end thereof, includes an outer wall and a core, only an upstream portion of which is surrounded by the outer wall. The boundary between the upstream portion and a downstream portion is defined by the intersection between the core and the surface formed by bisectors of acute angles formed by straight lines perpendicular to the outer wall and straight lines perpendicular to an outer surface of the core passing through the downstream end of the outer wall. The outer surface of the downstream portion of the core has a sharply curved convex region close to the boundary, the region having a radius of curvature in a radial plane of less than 30 times the radius of the core at the boundary, and a first slightly curved region between the boundary and the sharply curved convex region.

    摘要翻译： 一种具有纵向轴线的涡轮发动机管道，其在其上游端包括外壁和芯部，只有其上游部分被外壁包围。 上游部分和下游部分之间的边界由芯和由垂直于外壁的直线形成的锐角的平分线形成的表面和垂直于芯的外表面的直线形成的表面之间的交点限定， 外壁的下游端。 芯的下游部分的外表面具有接近边界的急剧弯曲的凸起区域，该区域在径向平面中的曲率半径小于边界处的芯的半径的30倍，并且第一稍微 边界与锐曲的凸区域之间的弯曲区域。