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    GAS TURBINE ENGINE SYSTEMS WITH FAIRING
    1.
    发明申请
    GAS TURBINE ENGINE SYSTEMS WITH FAIRING 审中-公开
    燃气涡轮发动机系统

    公开(公告)号：WO2009151701A3

    公开(公告)日：2010-11-18

    申请号：PCT/US2009037531

    申请日：2009-03-18

    Applicant: UNITED TECHNOLOGIES CORP ,  LYDERS DAVID ,  KLINETOB CARL BRIAN ,  ALEXANDER PHILLIP

    Inventor： LYDERS DAVID ,  KLINETOB CARL BRIAN ,  ALEXANDER PHILLIP

    IPC: F01D25/28 ,  F02C7/20

    CPC classification number: F01D25/28 ,  F01D9/041 ,  F02C7/20 ,  F05D2240/12 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/36

    Abstract: Gas turbine engine systems involving fairings with locating data are provided. In this regard, a representative a fairing assembly for a gas turbine engine includes: a first locating component having a leading edge, first and second sides extending from the leading edge, and a recess oriented parallel to the leading edge, the recess having a first datum surface, the first locating component being operative to be positioned between a portion of a strut and a portion of an interior surface of a fairing sheath such that the first datum surface establishes a desired orientation of the fairing sheath relative to the strut.

    Abstract translation: 提供了涉及具有定位数据的整流罩的燃气涡轮发动机系统。 在这方面，用于燃气涡轮发动机的代表性整流罩组件包括：第一定位部件，其具有前缘，从前缘延伸的第一和第二侧以及平行于前缘定向的凹部，所述凹部具有第一 基准表面，第一定位部件可操作地定位在支柱的一部分和整流罩的内表面的一部分之间，使得第一基准表面相对于支柱建立整流罩的期望取向。

    COMPOSITE AIRFOIL WITH LOCAL TAILORING OF MATERIAL PROPERTIES
    2.
    发明申请
    COMPOSITE AIRFOIL WITH LOCAL TAILORING OF MATERIAL PROPERTIES 审中-公开
    具有材料特性的局部定制的复合空气管

    公开(公告)号：WO2013172893A3

    公开(公告)日：2014-02-27

    申请号：PCT/US2013026661

    申请日：2013-02-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALEXANDER PHILLIP ,  SALISBURY GEORGE ALAN ,  FOSTER LARRY

    IPC: F01D5/28 ,  F01D5/14 ,  F02C7/00 ,  F02K3/00

    CPC classification number: F01D5/282 ,  B29C70/22 ,  B29C70/48 ,  B29D99/0025 ,  B29L2031/08 ,  F05D2220/36

    Abstract: A composite airfoil includes a woven preform with warp yarns of a first material, the preform with a tip, root, leading edge, trailing edge and an intermediate region positioned between the root and the tip; and a first matrix made of a first resin maintaining the relative positions of the preform yarns. The composite blade further includes at least one of: fill yarns of a second material in the woven preform; and a second matrix made of a second resin maintaining the relative positions of the preform yarns in a portion of the airfoil.

    Abstract translation: 复合翼型件包括具有第一材料的经纱的编织预制件，所述预制件具有尖端，根部，前缘，后缘和位于根部与尖端之间的中间区域; 以及由保持预成型纱线的相对位置的第一树脂制成的第一基体。 复合刀片还包括以下中的至少一个：编织预制件中的第二材料的填充纱线; 以及由第二树脂制成的第二基体，其保持预成型纱线在翼型的一部分中的相对位置。

    METHOD FOR LOADING AND LOCKING TANGENTIAL ROTOR BLADES AND BLADE DESIGN
    4.
    发明专利
    METHOD FOR LOADING AND LOCKING TANGENTIAL ROTOR BLADES AND BLADE DESIGN 未知

    公开(公告)号：CA2551774A1

    公开(公告)日：2007-01-14

    申请号：CA2551774

    申请日：2006-07-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BARNES ROLAND ,  PICKENS JOHN ,  ALEXANDER PHILLIP

    IPC: F01D5/30 ,  F01D5/02 ,  F01D5/32

    Abstract: A method of loading and locking a plurality of tangential rotor blades is provided. The method includes the steps of providing a disk having a slot and a pair of rails adjacent the slot, positioning a first snap seal in a desired location over the slot and the rails, radially loading a first blade having a platform into the slot and rotating the blade, and positioning the first blade adjacent the snap seal so that a portion of the snap seal slides under the platform. The rotor blades preferably have an attachment part which comprises a circular neck and a dovetail portion having two ends and upper and lower chamfered edges at each of the ends.

    COMPOSITE LEADING EDGE SHEATH AND DOVETAIL ROOT UNDERCUT
    6.
    发明专利
    COMPOSITE LEADING EDGE SHEATH AND DOVETAIL ROOT UNDERCUT 未知

    公开(公告)号：SG174697A1

    公开(公告)日：2011-10-28

    申请号：SG2011018728

    申请日：2011-03-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALEXANDER PHILLIP

    Abstract: An airfoil having a composite blade formed from a plurality of plies and having a leading edge and a root for attachment to an engine. The blade has a decreased number of plies at the junction of the blade leading edge and the root. A metallic sheath is attached to the leading edge, wherein the sheath has a portion proximate the junction of sufficient thickness to restore at least a portion of the decreased number of plies.(Figure 1)

    SHIM LOCK/PIN ANTI-ROTATION BUMPER DESIGN
    8.
    发明专利
    SHIM LOCK/PIN ANTI-ROTATION BUMPER DESIGN 未知

    公开(公告)号：CA2442358A1

    公开(公告)日：2004-03-30

    申请号：CA2442358

    申请日：2003-09-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUMMINGS KEVIN J ,  BIFULCO ANTHONY R ,  ALEXANDER PHILLIP ,  PICKENS JOHN T

    IPC: F04D29/56 ,  B60R19/24 ,  F01B25/02 ,  F01D17/16 ,  F01D9/02

    Abstract: The present invention relates to a bumper system for use with a compressor variable vane system. The bumper system broadly comprises a synchronizing ring, a bumper, a shim for defining a gap between a bumper pad and the bumper, a pin for preventing rotation of the bumper relative to the synchronizing ring, and a device for fully trapping t he shim. In a first embodiment, the device for fully trapping the shim comprises a sleeve passin g through the synchronizing ring. In a second embodiment, the device for fully trapping th e shim comprises a pin which passes through the synchronizing body. In a third embodiment, the device for fully trapping the shim comprises a fastener with a shoulder.

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