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12 条记录 (耗时 0.188 秒)

    MONOBLOC FLAMEHOLDER ARM FOR AN AFTERBURNER DEVICE OF A BYPASS TURBOJET
    5.
    发明申请
    MONOBLOC FLAMEHOLDER ARM FOR AN AFTERBURNER DEVICE OF A BYPASS TURBOJET 有权
    用于旁路涡轮机燃烧器装置的MONOBLOC FLAMEHOLDER ARM

    公开(公告)号：US20070039327A1

    公开(公告)日：2007-02-22

    申请号：US11024732

    申请日：2004-12-30

    申请人： Stephane Blanchard ,  Stephane Touchaud ,  Thierry Pancou ,  Eric Conete ,  Pierre Camy ,  Georges Habarou

    发明人： Stephane Blanchard ,  Stephane Touchaud ,  Thierry Pancou ,  Eric Conete ,  Pierre Camy ,  Georges Habarou

    IPC分类号： F02K3/10

    CPC分类号： F02K3/10 ,  F23R3/18

    摘要： A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

    摘要翻译： 支撑臂（13）旨在安装在旁路涡轮喷气发动机的后燃器装置中的径向位置。 该装置包括限定用于主流的通道的第一和第二内部环形壳体以及与第一内部环形壳体一起限定用于二次流动的通道的外部环形壳体。 臂（13）包括由复合材料制成的整体结构，其包括两个整体壁（14,15），一方面设计成限定具有大致V形轮廓的凹槽（16），另一方面， 包括连接在一起并适于限定足部（18）的第一端部部分（17）和适于各自限定至少一个凸缘（20,21）的第二端部（19），所述至少一个凸缘（20,21）被确定地连接到所述外部环形壳体。

    TURBINE ENGINE ROTOR WHEEL WITH BLADES MADE OF A COMPOSITE MATERIAL PROVIDED WITH A SPRING RING
    6.
    发明申请
    TURBINE ENGINE ROTOR WHEEL WITH BLADES MADE OF A COMPOSITE MATERIAL PROVIDED WITH A SPRING RING 有权
    具有弹簧圈的复合材料的叶片的涡轮发动机转子轮

    公开(公告)号：US20110268561A1

    公开(公告)日：2011-11-03

    申请号：US13141857

    申请日：2009-12-22

    申请人： Stephane Blanchard ,  Alain Gendraud

    发明人： Stephane Blanchard ,  Alain Gendraud

    IPC分类号： F01D11/02 ,  F01D11/12

    CPC分类号： F01D11/18 ,  F01D5/282 ,  F01D5/303 ,  F01D5/3069 ,  F01D5/32 ,  Y02T50/672

    摘要： A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate.

    摘要翻译： 包括由复合材料制成的叶片的涡轮机转子轮; 环形安装板; 安装在安装板上的多个复合材料叶片，每个叶片还包括顶部平台，顶端承载径向迷宫齿; 定位盘同轴地固定在安装板周围并且在其外周包括在一端开口的多个轴向槽，每个槽具有与叶片根部的横截面相匹配的横截面，以便将其保持成角度 在形状合作的位置; 以及可变直径的弹簧环，其部分地容纳在形成在每个叶片根部中并且相对于其相对地突出的轴向凹口中，弹簧环在叶片相对于叶片的径向向外运动期间径向抵靠定向盘的内表面 安装板。

    Monobloc flameholder arm for an afterburner device of a bypass turbojet
    8.
    发明授权
    Monobloc flameholder arm for an afterburner device of a bypass turbojet 有权
    用于旁路涡轮喷气发动机的燃烧器装置的单体火焰稳定器臂

    公开(公告)号：US07168253B1

    公开(公告)日：2007-01-30

    申请号：US11024732

    申请日：2004-12-30

    申请人： Stephane Blanchard ,  Stephane Touchaud ,  Thierry Pancou ,  Eric Conete ,  Pierre Camy ,  Georges Habarou

    发明人： Stephane Blanchard ,  Stephane Touchaud ,  Thierry Pancou ,  Eric Conete ,  Pierre Camy ,  Georges Habarou

    IPC分类号： F02K3/10

    CPC分类号： F02K3/10 ,  F23R3/18

    摘要： A support arm (13) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm (13) comprises a monobloc structure made of composite material including two integral walls (14, 15), on the one hand, designed to define a groove (16) having a substantially V-shaped profile and, on the other hand, including first end parts (17) joined together and adapted to define a foot (18) and second end parts (19) adapted each to define at least one flange (20, 21) intended to be positively connected to the outer annular casing.

    摘要翻译： 支撑臂（13）旨在安装在旁路涡轮喷气发动机的后燃器装置中的径向位置。 该装置包括限定用于主流的通道的第一和第二内部环形壳体以及与第一内部环形壳体一起限定用于二次流动的通道的外部环形壳体。 臂（13）包括由复合材料制成的整体结构，其包括两个整体壁（14,15），一方面设计成限定具有大致V形轮廓的凹槽（16），另一方面， 包括连接在一起并适于限定足部（18）的第一端部部分（17）和适于各自限定至少一个凸缘（20,21）的第二端部（19），所述至少一个凸缘（20,21）被确定地连接到所述外部环形壳体。

    Long life nozzle flap for aircraft turbojets
    10.
    发明申请
    Long life nozzle flap for aircraft turbojets 有权
    飞机涡轮喷气机寿命长的喷嘴挡板

    公开(公告)号：US20050005608A1

    公开(公告)日：2005-01-13

    申请号：US10849019

    申请日：2004-05-20

    申请人： Thierry Pancou ,  Herve Barret ,  Claude Corbin ,  Stephane Blanchard

    发明人： Thierry Pancou ,  Herve Barret ,  Claude Corbin ,  Stephane Blanchard

    IPC分类号： B64D33/04 ,  F02C7/00 ,  F02K1/00 ,  F02K1/06 ,  F02K1/12 ,  F02K99/00

    CPC分类号： F02K1/1207 ,  F02K1/002 ,  F05D2300/603 ,  F05D2300/614 ,  Y02T50/67 ,  Y02T50/672

    摘要： The invention proposes a long life nozzle flap for aircraft turbojets. This flap is remarkable in that it is composed of a hollow tapered body (10) flattened in the transverse direction along straight geometric generating lines (11), the body (10) forming a thin wall (12) with an approximately constant thickness E, this wall (12) comprising a continuous inner surface with a radius of curvature equal to at least 2×E, the wall (12) being made of a refractory composite material composed of reinforcing fibres (18) embedded in a matrix also made from a refractory material, the reinforcing fibres (18) being arranged in a plurality of continuous layers of fibres (18) stacked on each other, the fibres (18a) of a layer crossing the fibres (18b) of any adjacent layer.

    摘要翻译： 本发明提出了一种用于飞机涡轮喷气发动机的长寿命喷嘴挡板。 该翼片是显着的，它由沿着直线几何生成线（11）在横向方向平坦化的中空锥形体（10）组成，主体（10）形成具有近似恒定厚度E的薄壁（12） 该壁（12）包括曲率半径等于至少2xE的连续内表面，壁（12）由耐火材料复合材料制成，该耐火复合材料由嵌入基体中的增强纤维（18）组成，该基体也由耐火材料制成 ，所述增强纤维（18）布置在彼此堆叠的多个连续的纤维层（18）中，所述纤维（18a）与任何相邻层的纤维（18b）交叉。