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    GAS TURBINE ENGINE ROTOR SEAL
    1.
    发明申请
    GAS TURBINE ENGINE ROTOR SEAL 审中-公开
    气体涡轮发动机转子密封

    公开(公告)号：WO2014116330A2

    公开(公告)日：2014-07-31

    申请号：PCT/US2013/068923

    申请日：2013-11-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AIELLO, Nicholas ,  ANDERSON, Carney R.

    IPC: F01D11/00 ,  F01D9/02 ,  F04D29/08 ,  F02C7/28

    CPC classification number: F01D11/001

    Abstract: A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.

    Abstract translation: 用于将燃气涡轮发动机的叶片转子密封到其定子的旋转密封件包括密封元件和密封元件支撑件，所述密封元件和密封元件支撑件包括固定密封元件的径向外边缘部分，适于附接到 支撑的转子轮毂和在径向外边缘部分和径向内部安装部分之间延伸的柔性内侧腹板部分。

    COMPRESSOR ROTOR FOR GAS TURBINE ENGINE WITH DEEP BLADE GROOVE
    2.
    发明申请
    COMPRESSOR ROTOR FOR GAS TURBINE ENGINE WITH DEEP BLADE GROOVE 审中-公开
    用于具有深度叶片的气体涡轮发动机的压缩机转子

    公开(公告)号：WO2014105593A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/076351

    申请日：2013-12-19

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AIELLO, Nicholas ,  PHAN, Uyen

    IPC: F01D5/02 ,  F04D29/26

    CPC classification number: F04D29/322 ,  F01D5/3038 ,  F05D2250/292 ,  F05D2250/294 ,  F05D2260/941

    Abstract: A compressor rotor has a rotor centered on an axis, and a groove with opposed side edges. The groove receives a plurality of removable compressor blades, and has tangential sides. The tangential side surfaces are in contact with said tangential sides of the groove, and at least one slot is cut into the side edges. A first radial distance is measured from a radially outer edge of the side edge to a radially outer beginning point of the tangential sides of the groove. A second radial distance is radially between the radially outer beginning point of the tangential sides to a radially inner end of the tangential sides of the groove. A ratio of the first and second radial distance is between 1.1 and 5.0.

    Abstract translation: 压缩机转子具有以轴为中心的转子和具有相对侧边缘的槽。 凹槽接收多个可移除的压缩机叶片，并具有切向侧。 切向侧表面与凹槽的所述切向侧面接触，并且至少一个狭槽被切入侧边缘。 第一径向距离是从侧边缘的径向外边缘到凹槽的切向边的径向外开始点测量的。 第二径向距离在切线侧的径向外部起始点与槽的切向侧的径向内端之间径向地形成。 第一和第二径向距离的比率在1.1和5.0之间。

    SHIELD SLOT ON SIDE OF LOAD SLOT IN GAS TURBINE ENGINE ROTOR
    3.
    发明申请
    SHIELD SLOT ON SIDE OF LOAD SLOT IN GAS TURBINE ENGINE ROTOR 审中-公开
    燃气涡轮发动机转子负载槽侧的屏蔽槽

    公开(公告)号：WO2014028082A2

    公开(公告)日：2014-02-20

    申请号：PCT/US2013/041066

    申请日：2013-05-15

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AIELLO, Nicholas ,  COSBY, James ,  CORCORAN, Kevin L.

    CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/32 ,  F05D2260/30

    Abstract: A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge, load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

    Abstract translation: 转子体围绕旋转轴线旋转。 壁架提供了用于保持叶片的保持结构。 多个叶片定位在壁架下方，负载槽的尺寸被设计成允许叶片的安装部分在壁架的径向内部移动。 叶片沿周向移动以使凸缘的径向向内具有安装结构。 锁槽位于装载槽的一个圆周侧。 锁槽形成为接收锁，并且锁部分地容纳在至少一个叶片的一部分内，以将叶片锁定在转子内，以​​及在装载槽的第二周向侧上的屏蔽槽。 屏蔽槽的尺寸与锁定槽的尺寸不同，使得锁不能无意中定位在屏蔽槽内。

    SEGMENTED SEAL WITH SHIP LAP ENDS
    6.
    发明申请
    SEGMENTED SEAL WITH SHIP LAP ENDS 审中-公开
    SEGMENTED密封与船尾拉链

    公开(公告)号：WO2013180899A1

    公开(公告)日：2013-12-05

    申请号：PCT/US2013/039643

    申请日：2013-05-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AIELLO, Nicholas ,  LEE, Conor

    IPC: F02C7/28 ,  F01D5/20 ,  F02C7/00 ,  F01D5/00

    CPC classification number: F01D11/001 ,  F01D11/005 ,  F04D29/083 ,  F04D29/164 ,  Y10T29/49321

    Abstract: A segment for a knife edge seal includes an arcuate segment with a first end with a first end surface and a second end with a second end surface. The first end surface and the second end surface are complementary and overlapping when the first end surface and the second end surface interface with ends of adjacent segments.

    Abstract translation: 用于刀刃密封件的段包括弓形段，其具有带有第一端面的第一端和具有第二端面的第二端。 当第一端面和第二端面与相邻段的端部相接触时，第一端面和第二端表面是互补和重叠的。

    TURBOMACHINE ROTOR GROOVE
    8.
    发明申请
    TURBOMACHINE ROTOR GROOVE 审中-公开
    涡轮转子槽

    公开(公告)号：WO2014052039A1

    公开(公告)日：2014-04-03

    申请号：PCT/US2013/059597

    申请日：2013-09-13

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AIELLO, Nicholas ,  MALI, Raji

    IPC: F01D5/30 ,  F02C7/00 ,  F02K3/00

    CPC classification number: F01D5/3038 ,  Y10T29/49332

    Abstract: An example turbomachine rotor provides a groove that is annular and is configured to receive a root of an airfoil, the groove having a radial cross-sectional area. A ratio of the radial cross-sectional area of the groove to a radial cross-sectional area of the root received within the annular groove is from 2 to 5.

    Abstract translation: 涡轮机转子的一个实例提供了一个环形槽，并被构造为容纳翼型的根部，该槽具有径向横截面积。 槽的径向横截面积与在环形槽内容纳的根部的径向横截面积的比为2〜5。

    FLOATING SEGMENTED SEAL
    9.
    发明申请
    FLOATING SEGMENTED SEAL 审中-公开

    公开(公告)号：WO2014025439A3

    公开(公告)日：2014-02-13

    申请号：PCT/US2013/041496

    申请日：2013-05-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AIELLO, Nicholas ,  LEE, Conor

    IPC: F02C7/28 ,  F01D11/00

    Abstract: A gas turbine engine rotor section includes a rotor body with a ledge extending axially from a location on the rotor body. The ledge defines a radially inner surface radially inwardly of the ledge, and a hub extends axially from the rotor, and beyond the ledge. The hub has a radially outer surface spaced from the ledge radially inner surface. A first distance is defined between the radially inner surface of the ledge and the radially outer surface of the hub. A knife edge seal has at least one pointed knife seal portion at a radially outer end. A radially inwardly extending arm portion extends from the seal, and an axially inwardly extending portion extends axially inwardly from the radially inwardly extending portion. The axially inwardly extending portion has a radially outer face and a radially inner face, which are spaced by a second distance. The second distance is less than the first distance. The axially inwardly extending portion is received between the radially inner face of the rotor and the radially outer face of the hub, such that the knife edge seal is free floating between the ledge and the hub.

    KNIFE EDGE SEAL FOR GAS TURBINE ENGINE
    10.
    发明申请
    KNIFE EDGE SEAL FOR GAS TURBINE ENGINE 审中-公开
    燃气涡轮发动机切割边缘密封

    公开(公告)号：WO2013158168A1

    公开(公告)日：2013-10-24

    申请号：PCT/US2013/021653

    申请日：2013-01-16

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KNAUL, David, A. ,  MAALOUF, Fadi, S. ,  AIELLO, Nicholas ,  MORGAN, Orenthral, T. ,  MALI, Raji

    IPC: F01D11/14

    CPC classification number: F16J15/4472 ,  F01D11/001

    Abstract: A seal for a gas turbine engine and a gas turbine engine employing such a seal are disclosed. More specifically, the engine includes a knife edge seal which is better able to withstand the extremely high temperatures and mechanical loads to which gas turbine engine components are increasingly subjected. By moving the knife edge seal to the aft hub and cantilevering its angle off of vertical, thermal and mechanical loads are balanced and thus thermal mechanical fatigue life is improved while low cycle fatigue is maintained.

    Abstract translation: 公开了一种用于燃气涡轮发动机和采用这种密封件的燃气涡轮发动机的密封件。 更具体地说，发动机包括能够更好地承受燃气涡轮发动机部件越来越多地受到的极高温度和机械负载的刀刃密封。 通过将刀刃密封件移动到后轮毂，并将其角度从垂直方向悬垂，热和机械负载平衡，从而提高热机械疲劳寿命，同时保持低循环疲劳。

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