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    COMPOSITE ROTOR AND VANE ASSEMBLIES WITH INTEGRAL AIRFOILS
    1.
    发明申请
    COMPOSITE ROTOR AND VANE ASSEMBLIES WITH INTEGRAL AIRFOILS 审中-公开
    复合转子和带集成空气的风扇组件

    公开(公告)号：WO2013133875A3

    公开(公告)日：2013-11-07

    申请号：PCT/US2012068368

    申请日：2012-12-07

    Applicant: GEN ELECTRIC

    Inventor： KRAY NICHOLAS JOSEPH ,  MCAFEE CHRISTOPHER LEE ,  SHIM DONG-JIN

    IPC: F01D5/34 ,  B29C70/06 ,  F01D5/28

    CPC classification number: F01D5/282 ,  B29B11/16 ,  B29C70/48 ,  B29L2031/08 ,  F01D5/30 ,  F01D5/34 ,  F01D9/042 ,  F05D2300/6034 ,  Y02T50/672

    Abstract: A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies (57), a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise (60) and counter-clockwise (62) airfoil segments at clockwise (64) and counter-clockwise (66) ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell (68) circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots (83) in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled. Circumferentially adjacent ones of clockwise and counter" clockwise airfoil segments may be stitched together.

    Abstract translation: 复合燃气涡轮发动机结构包括具有与保持环安装在一体并与径向远离保持环的翼型的保持环。 保持环包括环形复合层（57），周向分段的翼型环，包括围绕保持环的外周和内周中的一个周围设置的翼型环段。 翼型环段包括环形基座和径向延伸的环形基座的顺时针（64）和逆时针（66）端的顺时针（60）和逆时针（62）翼型段。 复合翼型件包括沿周向相邻的顺时针和逆时针翼型段。 周向设置在分段翼型环周围的流路外壳（68）在流路壳和保持环之间捕获环形基座。 复合翼型件翼型件通过流道外壳中的槽（83）延伸。 层可以包裹在由连续的复合胶带制成的单个螺旋。 槽可以是周向成角度的。 顺时针和反向“顺时针”翼形段的周向相邻可以缝合在一起。

    LOW RADIUS RATIO FAN FOR A GAS TURBINE ENGINE
    3.
    发明申请
    LOW RADIUS RATIO FAN FOR A GAS TURBINE ENGINE 审中-公开
    用于气体涡轮发动机的低半径比风扇

    公开(公告)号：WO2014039974A8

    公开(公告)日：2015-04-16

    申请号：PCT/US2013058771

    申请日：2013-09-09

    Applicant: GEN ELECTRIC

    Inventor： LAMBOY JORGE ORLANDO ,  KRAY NICHOLAS JOSEPH ,  PAULEY GERALD ALEXANDER ,  LI QIANG ,  WILKIN II DANIEL ALLEN ,  DAVIS TOD WINTON

    IPC: F01D5/30 ,  F01D5/14 ,  F01D11/00 ,  F04D29/32

    CPC classification number: F04D29/324 ,  F01D5/147 ,  F01D5/3007 ,  F01D11/008 ,  F04D29/329 ,  F05D2220/3217 ,  F05D2240/80 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

    Abstract: A fan blade (18) for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure (40) and suction sides (42), and further including at least one shoulder (62,64) protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss (66,74) defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.

    Abstract translation: 一种用于燃气涡轮发动机的风扇叶片（18）包括：直轴向燕尾，翼型件和设置在燕尾榫和翼型之间的过渡部分，风扇叶片具有相对的压力（40）和吸力侧（42），以及 还包括从所述压力和吸力侧中的所选一个的标称表面突出的至少一个肩部（62,64），其中所述至少一个肩部包括限定侧面的凸台（66,74）和上部 从凸台径向向外延伸并向内渐缩以连接所选侧面的标称表面。

    ATTACHMENT OF COMPOSITE ARTICLE
    5.
    发明申请
    ATTACHMENT OF COMPOSITE ARTICLE 审中-公开
    附件复合文章

    公开(公告)号：WO2014130131A2

    公开(公告)日：2014-08-28

    申请号：PCT/US2013073501

    申请日：2013-12-06

    Applicant: GEN ELECTRIC

    Inventor： KRAY NICHOLAS JOSEPH ,  FINN SCOTT ROGER ,  BAEHMANN PEGGY LYNN ,  WHITE JOEL

    IPC: F01D5/14

    CPC classification number: F01D5/147 ,  B29C70/202 ,  B29C70/38 ,  B29D99/0025 ,  B29L2031/082 ,  F01D5/282 ,  Y02T50/672

    Abstract: A composite article including composite component mounted on a spar including a shank extending heightwise from below component base up into composite component. Tab at an upper end of shank substantially or fully embedded in the composite component and at least one ply surface pattern of the composite component contacting and generally conforming to at least one spar surface pattern on the tab. Spar surface pattern may include spaced apart spar surface protrusions with spar surface spaces therebetween and spar surface protrusions extending outwardly from spar and disposed between tows in ply surface pattern. Tows may be layed up in spar surface spaces. Spar surface pattern may include continuous or segmented spaced spar surface protrusions and spar surface spaces therebetween with tows in ply surface pattern disposed in spar surface spaces. The composite article may be a composite blade or vane including a composite airfoil.

    Abstract translation: 一种复合材料制品，其包括安装在翼梁上的复合构件，所述翼梁包括从下面的构件基部高度地延伸到复合构件中的杆。 在基部或完全嵌入复合部件中的柄部的上端处的翼片以及复合部件的至少一个层片表面图案接触且大致符合在翼片上的至少一个翼梁表面图案。 Spar表面图案可以包括间隔开的翼梁表面突起，其间具有翼梁表面间隔，并且翼梁表面突起从翼梁向外延伸并布置在帘布层表面图案中的丝束之间。 丝束可能放置在晶石表面空间。 Spar表面图案可以包括连续或分段间隔的翼梁表面突起以及它们之间的翼梁表面间隔，其中帘布层表面图案中的束布置在翼梁表面空间中。 复合制品可以是包括复合翼型件的复合叶片或叶片。

    NON-INTEGRAL FAN BLADE PLATFORM
    6.
    发明申请
    NON-INTEGRAL FAN BLADE PLATFORM 审中-公开
    非整体风扇叶片平台

    公开(公告)号：WO2014105701A3

    公开(公告)日：2014-08-28

    申请号：PCT/US2013076935

    申请日：2013-12-20

    Applicant: GEN ELECTRIC

    Inventor： LAMBOY JORGE ORLANDO ,  GANN MATTHEW GLEN ,  KRAY NICHOLAS JOSEPH ,  PAULEY GERALD ALEXANDER ,  WILKIN DANIEL ALLEN ,  XIE MING

    IPC: F01D11/00 ,  F01D5/30 ,  F02K3/06 ,  F04D29/26

    CPC classification number: F01D5/3038 ,  F01D5/3007 ,  F01D11/008 ,  F02K3/06 ,  F04D29/321 ,  F04D29/644 ,  F05D2220/36 ,  F05D2260/30 ,  Y02T50/672 ,  Y10T29/4932

    Abstract: Described are a gas turbine engine fan blade platform, related rotor assembly and gas turbine engine, as well as a method of assembling the same. The platform has a forward portion proximal to an axis of rotation, an aft portion, and a transition portion between the forward and aft portions. The forward portion has a forward interface surface facing axially forward, the aft portion has an aft interface surface facing radially outward, and the transition portion has at least one mounting feature. For the method of assembly, an aft support is installed on a fan disk and booster spool assembly. A plurality of fan blades are installed into a fan disk, followed by installing a fan platform between adjacent blades and securing the mounting features to the disk, thereby filling the annulus of the fan disk. Finally, a forward support is installed on the fan disk.

    Abstract translation: 描述了一种燃气涡轮发动机风扇叶片平台，相关的转子组件和燃气涡轮发动机，以及其组装方法。 平台具有靠近旋转轴线的前部，后部部分和前部和后部之间的过渡部分。 前部具有面向轴向前方的前向接口表面，后部具有面向径向外侧的后界面，并且该过渡部具有至少一个安装特征。 对于组装方法，后部支撑件安装在风扇盘和助力阀芯组件上。 将多个风扇叶片安装到风扇盘中，随后在相邻叶片之间安装风扇平台并将安装特征固定到盘上，从而填充风扇盘的环形空间。 最后，风扇盘上安装了前向支持。

    ROTOR BLADE
    7.
    发明专利
    ROTOR BLADE 失效

    公开(公告)号：JP2001055996A

    公开(公告)日：2001-02-27

    申请号：JP2000226248

    申请日：2000-07-27

    Applicant: GEN ELECTRIC

    Inventor： LAMMAS ANDREW J ,  KRAY NICHOLAS JOSEPH

    IPC: F04D29/38 ,  F01D5/14 ,  F01D21/04 ,  F04D29/32

    Abstract: PROBLEM TO BE SOLVED: To provide a rotor blade and vane for a turbine engine constructed to be easier to bend or buckle than conventional rotor blades and vanes. SOLUTION: A rotor blade 100 for a turbine engine has a blade root portion 104 and an aerofoil portion 102 extending radially outward from the blade root portion 104 along a radial line RAS. The radial line RAS extends slantly at an angle rather than perpendicular or transverse to a plane along the upper face of a platform 106. As a result, over-turning moment occurs at the root of the aerofoil portion 102 during blading-out. The over-turning moment facilitates the bending of the aerofoil portion 102 and reduces damage to a stator.

    APPARATUS AND METHOD FOR FORMING FLANGES ON COMPONENTS
    9.
    发明专利
    APPARATUS AND METHOD FOR FORMING FLANGES ON COMPONENTS 未知

    公开(公告)号：CA2884651A1

    公开(公告)日：2015-09-21

    申请号：CA2884651

    申请日：2015-03-12

    Applicant: GEN ELECTRIC

    Inventor： VERMILYEA MARK ERNEST ,  KRAY NICHOLAS JOSEPH ,  RADEBACH MATTHEW ALLEN ,  VALLEE ALEXANDER JOSEPH JR ,  CARMICHAEL CRAIG DOUGLAS

    IPC: B29C57/02

    Abstract: An apparatus for forming a flange on a component is presented. The apparatus includes a mold disposed for the placement of the component thereon, a forming tool, and a tubular bladder. The forming tool is assembled to hold the component with a first portion extending into a space defined between the mold and the forming tool. The tubular bladder has a non-uniform wall thickness around its cross section along a longitudinal dimension of the bladder. The bladder is disposed in a step defined in the mold, and configured to impart a forming force to the portion extending into the space to form the flange on the component when the bladder is inflated. A method for forming the flange on the component is also provided.

    FLOW SURFACE
    10.
    发明专利
    FLOW SURFACE 未知

    公开(公告)号：CA2915496A1

    公开(公告)日：2014-12-31

    申请号：CA2915496

    申请日：2014-06-17

    Applicant: GEN ELECTRIC

    Inventor： KRAY NICHOLAS JOSEPH ,  BEDEL DAVID L ,  PRENTICE IAN FRANCIS

    IPC: F01D25/02 ,  B64D15/16 ,  F01D5/28 ,  F02C7/047

    Abstract: According to some embodiments, a flow surface comprises a composite material formed of a plurality of layers of said composite, and a piezoelectric actuator located within the layers or on an outer surface of the composite material. The piezoelectric actuator is actuatable to vibrate the composite material and one of inhibit ice build-up or shed ice which has formed.

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