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    Turbine wheel for a turbine engine
    3.
    发明授权
    Turbine wheel for a turbine engine 有权

    公开(公告)号：US09951625B2

    公开(公告)日：2018-04-24

    申请号：US14931474

    申请日：2015-11-03

    Applicant: SNECMA

    Inventor： Sébastien Serge Francis Congratel ,  Maurice Guy Judet

    IPC: F01D5/10 ,  F01D5/22 ,  F01D11/00 ,  F01D5/30

    CPC classification number: F01D5/10 ,  F01D5/22 ,  F01D5/3023 ,  F01D11/006 ,  F05D2260/30 ,  F05D2260/96 ,  Y02T50/671

    Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades each having a platform, carrying an impeller connected by a stilt to a root. Each blade comprises an upstream radial wall and a downstream radial wall extending inwards from the platform of the blade. The roots of the blades are engaged into slots on the periphery of the disk, so that the radial walls of the blades and the platforms of the blades are circumferentially arranged end-to-end, and define inter-blade cavities radially inside the platforms, each accommodating an inter-blade sealing and vibration damping member. At least one member comprises an elastically deformable element configured so as to be elastically prestressed against the walls of a cavity in the member mounting position.

    COMPOSITE DISK
    5.
    发明申请
    COMPOSITE DISK 有权
    复合盘

    公开(公告)号：US20160362990A1

    公开(公告)日：2016-12-15

    申请号：US14734091

    申请日：2015-06-09

    Applicant: General Electric Company

    Inventor： Nicholas Joseph KRAY ,  Baskaran BHUVARAGHAN ,  Nitesh JAIN

    IPC: F01D5/30

    CPC classification number: F01D5/3023 ,  B29C70/345 ,  B29C70/48 ,  B29D99/0025 ,  F01D5/028 ,  F01D5/282 ,  F01D5/3007 ,  F05D2220/36

    Abstract: A gas turbine engine composite disk includes dovetail slots between disk posts extending radially inwardly from a periphery, a hub ring of composite plies circumscribed about a centerline axis, and radial plies extending radially away from hub ring into disk posts. A segmented intermediate ring concentric with and located radially outwardly of hub ring includes intermediate ring segments having nested plies with annular bases circumscribed about centerline axis and substantially radially extending clockwise and counter-clockwise radial ply arms. An outer segmented ring may be concentric with and located radially outwardly of intermediate ring, include annular outer ring segments with circumferentially stacked composite plies disposed within intermediate ring segments between clockwise and counter-clockwise radial ply arms and radially outwardly of annular bases. An outer skin of outermost composite covering plies may extend circumferentially around composite disk. Circumferential and radial composite plies may include circumferentially and radially oriented fibers.

    Abstract translation: 燃气涡轮发动机复合盘包括在从周边径向向内延伸的盘柱之间的燕尾槽，围绕中心线轴线包围的复合帘布层的轮毂圈，以及从轮毂环径向延伸到盘柱的径向帘布层。 与轮毂环径向向外同心并且位于毂环径向向外的分段中间环包括具有嵌套层的中间环段，环状基部围绕中心线轴线以及基本径向延伸的顺时针和逆时针径向层叠臂。 外部分段环可以与中间环同心并位于中间环的径向向外，包括环形外环段，其具有周向堆叠的复合层，设置在顺时针和逆时针径向层叠臂之间的中间环段内，并且环形基底的径向向外。 最外面的复合材料覆盖层的外皮可围绕复合盘周向延伸。 周向和径向复合层可以包括周向和径向取向的纤维。

    Catcher ring arrangement
    6.
    发明授权
    Catcher ring arrangement 有权
    捕手环安排

    公开(公告)号：US09434467B2

    公开(公告)日：2016-09-06

    申请号：US13914961

    申请日：2013-06-11

    Applicant: ROLLS-ROYCE PLC

    Inventor： Kenneth John Mackie ,  Kenneth Franklin Udall

    IPC: B64C11/08 ,  B64C11/06 ,  F01D5/30 ,  B64D27/00

    CPC classification number: B64C11/08 ,  B64C11/06 ,  B64D2027/005 ,  F01D5/3023 ,  Y02T50/66

    Abstract: This invention relates to a blade assembly comprising: a hub which is rotatable about an axis; at least one blade having an aerofoil portion and a root, wherein the root is coupled to the hub using a primary retention device which prevents radial separation of the root and hub in normal use; and, a secondary retention device which comprises an annular catcher having a restriction through which the root portion cannot radially pass, the restriction being located radially outwardly and radially spaced from the root part during use.

    Abstract translation: 本发明涉及一种叶片组件，其包括：可围绕轴线旋转的轮毂; 至少一个叶片具有机翼部分和根部，其中所述根部使用主保持装置联接到所述轮毂，所述主保持装置在正常使用中防止所述根部和轮毂的径向分离; 以及第二保持装置，其包括环形捕集器，所述环形捕集器具有根部不能径向通过的限制，所述限制件在使用期间径向向外定位并与根部部分径向间隔开。

    HYBRID METAL AND COMPOSITE SPOOL FOR ROTATING MACHINERY
    7.
    发明申请
    HYBRID METAL AND COMPOSITE SPOOL FOR ROTATING MACHINERY 有权
    混合金属和复合材料旋转机械

    公开(公告)号：US20160245086A1

    公开(公告)日：2016-08-25

    申请号：US14628311

    申请日：2015-02-23

    Applicant: General Electric Company

    Inventor： Bowden Kirkpatrick ,  Nicholas Joseph Kray ,  Todd Alan Anderson ,  Stefaan Guido Van Nieuwenhove ,  Po-Ching Yeh

    IPC: F01D5/02 ,  F01D5/30

    CPC classification number: F01D25/005 ,  F01D5/06 ,  F01D5/282 ,  F01D5/3023 ,  F01D11/02 ,  F05B2240/24 ,  F05D2230/20 ,  F05D2230/23 ,  Y02T50/672

    Abstract: A hybrid metal and composite spool includes metal rings on an outer diameter of a composite spool shell. Metal rings may include features such as annular or axial dovetail slots. Adhesive layers may be between the metal rings and composite shell which may be connected by a shrink bonded joint. The metal rings may include a single seal tooth ring with an annular radially extending seal tooth. A method for fabricating the spool may include fabricating one or more metal rings with the features therein, positioning the metal rings in place on an outer surface of an uncured composite spool shell of the spool before curing the shell, and curing the shell with the one or more metal rings positioned in place. Alternatively, rings may be heated to a temperature at least sufficient to slide rings over a cured composite shell, and allowed to cool and shrink onto shell.

    Abstract translation: 混合金属和复合线轴包括在复合卷轴外壳的外径上的金属环。 金属环可以包括诸如环形或轴向燕尾槽的特征。 粘合剂层可以在金属环和可通过收缩接合连接的复合壳之间。 金属环可以包括具有环形径向延伸的密封齿的单个密封齿环。 制造卷轴的方法可以包括制造具有其特征的一个或多个金属环，在固化壳体之前将金属环定位在卷轴的未固化的复合卷轴外壳的外表面上，并将壳体固化在壳体上 或多个金属环定位就位。 或者，环可以被加热到至少足以将环滑过固化的复合壳体的温度，并允许冷却并收缩到壳体上。

    Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping
    8.
    发明授权
    Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping 有权
    具有通过夹紧获得具有叶片到盘连接的复合材料刀片的燃气轮机发动机转子轮

    公开(公告)号：US09422818B2

    公开(公告)日：2016-08-23

    申请号：US13698208

    申请日：2011-06-21

    Applicant: Stephane Pierre Guillaume Blanchard ,  Laurent Pierre Joseph Ricou

    Inventor： Stephane Pierre Guillaume Blanchard ,  Laurent Pierre Joseph Ricou

    IPC: F01D5/30 ,  F01D5/28

    CPC classification number: F01D5/3023 ,  F01D5/282 ,  F01D5/3046 ,  F01D5/3053 ,  F01D5/3069 ,  F05D2250/25 ,  Y02T50/672

    Abstract: A rotor wheel for a gas turbine engine, the wheel including: a metal holder disk including a plurality of teeth at its periphery, the teeth extending radially outwards from the disk; a plurality of composite material blades, each blade including a root engaged between two adjacent teeth of the holder disk and that is held against the teeth by a pivot connection; a clamp disk including a plurality of teeth at its periphery extending in an axial direction, the clamp disk being fastened against the holder disk and on the same axis, with each of its teeth taking up a circumferential position between a blade root and a tooth of the holder disk; and a mechanism exerting a clamping force in a circumferential direction urging the teeth of the clamp disk against the blade roots.

    Abstract translation: 一种用于燃气涡轮发动机的转子轮，所述转轮包括：在其周边包括多个齿的金属保持盘，所述齿从所述盘径向向外延伸; 多个复合材料叶片，每个叶片包括接合在保持器盘的两个相邻齿之间的根部，并且通过枢转连接而保持抵靠齿; 夹持盘在其周边沿轴向延伸的多个齿，夹紧盘紧固在保持盘上并在相同的轴线上，其每个齿处于叶片根部与牙齿之间的圆周位置 保持盘; 以及在圆周方向上施加夹紧力的机构，其推动夹紧盘的齿抵靠叶片根部。

    TURBINE OR COMPRESSOR STAGE INCLUDING AN INTERFACE PART MADE OF CERAMIC MATERIAL
    10.
    发明申请
    TURBINE OR COMPRESSOR STAGE INCLUDING AN INTERFACE PART MADE OF CERAMIC MATERIAL 有权
    涡轮或压缩机阶段，包括陶瓷材料界面部分

    公开(公告)号：US20150010404A1

    公开(公告)日：2015-01-08

    申请号：US14320911

    申请日：2014-07-01

    Applicant: SNECMA

    Inventor： Son LE HONG ,  Gael EVAIN ,  Didier FABRE ,  Philippe PICOT

    IPC: F01D5/30 ,  F04D29/26

    CPC classification number: F01D5/3084 ,  F01D5/3023 ,  F01D5/3069 ,  F04D29/023 ,  F04D29/26 ,  F04D29/321 ,  F04D29/322 ,  F05D2230/22 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A turbine or compressor stage suitable for being included in airplane turbojets. According to the invention, the stage comprises a disk (30) configured to be coupled to a shaft of the turbine engine, and at least one airfoil (20), the disk (30) comprising a metal material, the airfoil (20) comprising a ceramic matrix composite material, and the stage further including an interface part (40) that is distinct from the airfoil (20) and that is configured to be fastened to the disk (30) and to fasten said at least one airfoil (20), said interface part (40) comprising a ceramic or a ceramic matrix composite material.

    Abstract translation: 适用于飞机涡轮喷气发动机的涡轮或压缩机级。 根据本发明，该台包括构造成联接到涡轮发动机的轴的盘（30）和至少一个翼片（20），盘（30）包括金属材料，所述翼型件（20）包括 陶瓷基体复合材料，并且所述台阶还包括与所述翼型件（20）不同的接口部分（40），并且被构造成紧固到所述盘（30）并且紧固所述至少一个翼型件（20） ，所述界面部分（40）包括陶瓷或陶瓷基复合材料。

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