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    CONNECTION FOR A FAIRING IN A MID-TURBINE FRAME OF A GAS TURBINE ENGINE
    81.
    发明申请
    CONNECTION FOR A FAIRING IN A MID-TURBINE FRAME OF A GAS TURBINE ENGINE 审中-公开
    在燃气涡轮发动机的中涡轮机中的接合连接

    公开(公告)号：US20160201515A1

    公开(公告)日：2016-07-14

    申请号：US14912995

    申请日：2014-08-12

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Hoyt Y. Chang

    IPC: F01D25/24 ,  F02C3/04 ,  F01D9/04

    CPC classification number: F01D25/246 ,  F01D9/041 ,  F01D25/28 ,  F02C3/04 ,  F02C7/20 ,  F05D2220/32 ,  F05D2240/14 ,  F05D2240/35 ,  F05D2300/6033 ,  Y02T50/672

    Abstract: A fairing assembly for a gas turbine engine includes an inner fairing platform; an outer fairing platform located radially outward of the inner fairing platform; a plurality of vanes radially outward from the inner fairing platform between the inner fairing platform and outer fairing platform; a mount located on a radially outer side of the outer fairing platform, the mount attached to the outer fairing platform on the radially outer side; and a link that includes an elongated member with a first end and an opposite second end, the first end configured to fit within the mount and define a pivot axis of the link with respect to the mount.

    Abstract translation: 用于燃气涡轮发动机的整流罩组件包括内部整流罩平台; 位于内部整流平台径向外侧的外部整流罩平台; 在所述内侧整流罩平台和所述外部整流罩平台之间从所述内部整流平台径向向外的多个叶片; 位于所述外整流平台的径向外侧上的安装件，所述安装件在所述径向外侧附接到所述外整流平台; 以及包括具有第一端和相对的第二端的细长构件的连杆，所述第一端构造成配合在所述安装件内并且限定所述连杆相对于所述安装件的枢转轴线。

    AUXILIARY COMPONENT MOUNTS
    82.
    发明申请
    AUXILIARY COMPONENT MOUNTS 有权
    辅助组件安装

    公开(公告)号：US20160177840A1

    公开(公告)日：2016-06-23

    申请号：US14410487

    申请日：2013-09-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Thomas J. Robertson ,  Steven Clarkson ,  Mark W. Costa

    IPC: F02C7/32 ,  F02C7/20

    CPC classification number: F02C7/32 ,  F01D21/045 ,  F02C7/20 ,  F05D2220/32 ,  F05D2240/90 ,  F05D2260/30 ,  F05D2260/311

    Abstract: A mount for mounting a component to a gas turbine engine is disclosed. The mount may include a central portion that attaches to the component, and a flange circumscribing the central portion and extending to the gas turbine engine, the flange including a fusible region that breaks at a predetermined load. A method for protecting a component mounted to a gas turbine engine is also disclosed. The method may include attaching a mount to a casing of the gas turbine engine, the mount including a fusible region that breaks at a predetermined load. The method may further include attaching the component to the mount. The method may further include the fusible region breaking when the mount experiences the predetermined load, detaching the component from the casing of the gas turbine engine.

    Abstract translation: 公开了一种用于将部件安装到燃气轮机的安装座。 安装件可以包括附接到部件的中心部分和围绕中心部分并延伸到燃气涡轮发动机的凸缘，凸缘包括以预定负载断裂的可熔区域。 还公开了一种保护安装在燃气涡轮发动机上的部件的方法。 该方法可以包括将安装件附接到燃气涡轮发动机的壳体，该安装件包括以预定负载断裂的可熔区域。 该方法还可以包括将部件附接到安装件。 该方法还可以包括当安装座经受预定负载时的易熔区域断裂，将部件从燃气涡轮发动机的壳体上拆下。

    STIFFENING RIB
    83.
    发明申请
    STIFFENING RIB 审中-公开
    加强RIB

    公开(公告)号：US20160169046A1

    公开(公告)日：2016-06-16

    申请号：US14962448

    申请日：2015-12-08

    Applicant: Rolls-Royce Corporation

    Inventor： Aric Acius ,  Robert Biel

    IPC: F01D25/24

    CPC classification number: F01D25/243 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2300/502 ,  Y02T50/672

    Abstract: A fan casing for a gas turbine includes an improved clipping member for attaching various fan case externals and units. The clipping member may include I-Shaped or C-shaped cross sectional stiffened rib sections that afford enhanced load carrying capabilities while providing mounting surfaces for being connected to structures of the fan case. The I-Shaped or C-Shaped cross sectional stiffened rib also affords an enhanced natural frequency tuning characteristic. Hardware may be formed within the clipping member and become an integral part of the structure which may be tuned to specific design preferences.

    Abstract translation: 用于燃气轮机的风扇壳体包括用于附接各种风扇外壳和单元的改进的夹持构件。 夹持构件可以包括I形或C形横截面的加强肋部分，其提供增强的承载能力，同时提供用于连接到风扇壳体的结构的安装表面。 I形或C形横截面加强筋还提供增强的固有频率调谐特性。 硬件可以形成在夹持构件内并且成为结构的整体部分，其可以被调谐到特定的设计偏好。

    In-line removable heat shield for a turbomachine suspension yoke
    84.
    发明授权
    In-line removable heat shield for a turbomachine suspension yoke 有权
    用于涡轮机悬架轭的可插拔式热屏蔽

    公开(公告)号：US09359954B2

    公开(公告)日：2016-06-07

    申请号：US14053862

    申请日：2013-10-15

    Applicant: SNECMA

    Inventor： Lambert Olivier Marie Demoulin ,  Julien Pavillet ,  Guilhem Seize

    IPC: F02C7/24 ,  F02C7/20 ,  B64D27/26

    CPC classification number: F02C7/20 ,  B64D27/26 ,  B64D2027/266 ,  F02C7/24

    Abstract: A heat shield device for a yoke suspending an engine from an aircraft is provided. The device includes panels able to be fixed to the yoke, at least one of the panels extending radially in the direction of the axis of the engine, and a component configured to be fixed to the engine and including a groove shaped in such a way that the lower end of the panel can be inserted into it.

    Abstract translation: 提供一种用于从飞行器悬挂发动机的轭的隔热装置。 该装置包括能够固定到轭架的​​面板，至少一个面板沿着发动机的轴线的方向径向地延伸，以及构造成固定到发动机的部件，并且包括一个凹槽， 面板的下端可以插入其中。

    TURBINE ENGINE CASING HAVING A CUT-OUT FLANGE
    85.
    发明申请
    TURBINE ENGINE CASING HAVING A CUT-OUT FLANGE 有权
    具有切口法兰的涡轮发动机壳体

    公开(公告)号：US20160146051A1

    公开(公告)日：2016-05-26

    申请号：US14903266

    申请日：2014-07-07

    Applicant: SNECMA

    Inventor： Benoit DEBRAY ,  Gregory GHOSAROSSIAN-PRILLIEUX ,  Mario DE SOUSA ,  Nicolas POMMIER ,  Frederic Noel

    IPC: F01D25/24 ,  F01D25/30 ,  F01D9/02

    CPC classification number: F01D25/243 ,  F01D9/02 ,  F01D25/162 ,  F01D25/30 ,  F02C7/20 ,  F02K1/04 ,  F05D2220/323 ,  F05D2230/10

    Abstract: The present invention relates to a turbine engine casing (1), in particular a turbojet exhaust casing, including at least one hoop (2) and at least one flange (3, 4) at least partially defining one end of said hoop (2), and at least one cap (5) positioned at least partially on the outer surface of the hoop (2), said cap (5) including a bore (6) capable of receiving an element for fastening the casing (1) to a bracket, the flange including an access cut-out (7a) substantially coaxial with the bore (6) of said at least one cap (5), said access cut-out (7a) enabling access to the bore (6), the access cut-out (7a) being provided at a release cut-out (7b) which is wider than the flange (3, 4) and constitutes a recess on said release cut-out (7b). The invention also relates to a turbine engine including a casing (1) and to a method for machining the latter according to the present invention.

    Abstract translation: 本发明涉及一种涡轮发动机外壳（尤其是涡轮喷气发动机排气罩），其包括至少部分地限定所述环箍（2）的一端的至少一个箍（2）和至少一个凸缘（3,4） ，以及至少一个至少部分地定位在所述箍（2）的外表面上的帽（5），所述帽（5）包括孔（6），所述孔能够容纳用于将所述壳体（1）紧固到支架 所述凸缘包括与所述至少一个盖（5）的所述孔（6）基本上同轴的进入切口（7a），所述进入切口（7a）能够进入所述孔（6），所述进入切口 （7a）设置在比凸缘（3,4）更宽的释放切口（7b）处，并且构成在所述释放切口（7b）上的凹部。 本发明还涉及一种包括壳体（1）和根据本发明的用于加工后者的方法的涡轮发动机。

    Modular power plant and an aircraft provided with a lift rotor
    86.
    发明授权
    Modular power plant and an aircraft provided with a lift rotor 有权
    模块化发电厂和一架配有电梯转子的飞机

    公开(公告)号：US09346541B2

    公开(公告)日：2016-05-24

    申请号：US14330170

    申请日：2014-07-14

    Applicant: AIRBUS HELICOPTERS

    Inventor： Olivier Honnorat

    IPC: B64D27/00 ,  B64C27/12 ,  B64D27/14 ,  F02C7/36 ,  B64C27/473 ,  F02C7/12 ,  F02C7/20 ,  F16H57/025

    CPC classification number: B64C27/12 ,  B64C27/473 ,  B64D27/14 ,  F02C7/12 ,  F02C7/20 ,  F02C7/36 ,  F05D2220/328 ,  F05D2220/329 ,  F05D2240/90 ,  F05D2260/40311 ,  F16H57/025

    Abstract: A power plant (10) having a main gearbox (20), a turbine engine (40), and a heat exchanger (60), the main gearbox (20) including a substantially vertical rotor mast (21). The main gearbox (20) comprises at least a rotary speed reduction stage arranged in a flat casing (22), and a pylon (23). The turbine engine (40) has an engine casing (42) with an outlet shaft projecting from said engine casing (42) and penetrating into said flat casing (22), said outlet shaft (41) being substantially parallel to the rotor mast (21), said engine casing (42) being offset longitudinally from the pylon (23) and not being in contact with the pylon (23). The heat exchanger (60) extends longitudinally behind said turbine engine (40), while, on the contrary, said rotor mast (21) is situated longitudinally in front of said turbine engine (40).

    Abstract translation: 具有主变速箱（20），涡轮发动机（40）和热交换器（60）的动力装置（10），所述主变速箱（20）包括基本垂直的转子桅杆（21）。 主变速箱（20）至少包括设置在平坦壳体（22）中的旋转减速台和塔架（23）。 涡轮发动机（40）具有发动机壳体（42），其具有从所述发动机壳体（42）突出并且穿透到所述平坦壳体（22）中的出口轴，所述出口轴（41）基本上平行于所述转子桅杆 ），所述发动机壳体（42）从所述塔架（23）纵向偏移并且不与所述塔架（23）接触。 所述热交换器（60）纵向延伸到所述涡轮发动机（40）之后，而相反地，所述转子桅杆（21）纵向位于所述涡轮发动机（40）的前方。

    Transition support system for combustion transition ducts for turbine engines
    88.
    发明授权
    Transition support system for combustion transition ducts for turbine engines 有权
    用于涡轮发动机燃烧过渡管道的过渡支撑系统

    公开(公告)号：US09328664B2

    公开(公告)日：2016-05-03

    申请号：US14074911

    申请日：2013-11-08

    Applicant: Keith W. Piersall ,  Yevgeniy Shteyman ,  Robert Angel ,  Ashley N. Girdich ,  Robert T. Brooks ,  James Alfonso ,  James Marshall

    Inventor： Keith W. Piersall ,  Yevgeniy Shteyman ,  Robert Angel ,  Ashley N. Girdich ,  Robert T. Brooks ,  James Alfonso ,  James Marshall

    IPC: F02C7/20 ,  F02C9/16 ,  F23R3/60 ,  F01D9/02 ,  F01D25/04 ,  F23R3/46

    CPC classification number: F02C7/20 ,  F01D9/023 ,  F01D25/04 ,  F02C9/16 ,  F05D2260/30 ,  F05D2260/96 ,  F23R3/46 ,  F23R3/60 ,  F23R2900/00014

    Abstract: An adjustable transition duct support system for a transition duct that channels hot gases from a combustor exit to a gas turbine inlet of a turbine engine. The adjustable transition duct support system includes an adjustable forward transition flexible support assembly in contact with a transition duct body, whereby the forward transition flexible support assembly may be formed from a base extending toward the transition duct body and first and second side support arms extending from the base to the transition duct body. The first and second side support arms may be formed from a plurality of flex plates spaced from each other with spacers that provide rigidity in circumferential and radial directions and flexibility in an axial direction. The number of flex plates used may be varied to accommodate different turbine engines. The adjustable transition duct support system may have natural frequencies for circumferential and radial modes above two engine orders.

    Abstract translation: 用于过渡管道的可调节的过渡管道支撑系统，其将来自燃烧器出口的热气体引导到涡轮发动机的燃气涡轮机入口。 可调节的过渡管道支撑系统包括与过渡管道本体接触的可调节的向前过渡的柔性支撑组件，由此前向过渡的柔性支撑组件可由朝向过渡管道本体延伸的基部形成，并且第一和第二侧支撑臂从 基座到过渡管体。 第一侧支撑臂和第二侧支撑臂可以由多个彼此间隔开的柔性板形成，间隔件在周向和径向方向上提供刚性并且在轴向方向上具有柔性。 所使用的柔性板的数量可以变化以适应不同的涡轮发动机。 可调节的过渡管道支撑系统可以具有高于两个发动机顺序的周向和径向模式的固有频率。

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