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    BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT
    1.
    发明申请
    BLADE OUTER AIR SEAL ASSEMBLY AND SUPPORT 审中-公开
    叶片外部空气密封组件和支撑

    公开(公告)号：US20150016954A1

    公开(公告)日：2015-01-15

    申请号：US14504719

    申请日：2014-10-02

    Applicant: United Technologies Corporation

    Inventor： Anne-Marie B. Thibodeau ,  Bruce E. Chick ,  Thurman Carlo Dabbs ,  James N. Knapp ,  Dmitriy A. Romanov ,  Russell E. Keene ,  Jeffrey Vincent Anastas

    IPC: F01D25/24 ,  F01D11/08

    CPC classification number: F01D25/246 ,  F01D11/08 ,  F01D11/125 ,  F05D2240/11 ,  F05D2260/202

    Abstract: An blade outer air seal support assembly includes a main support member configured to support a blade outer air seal. The main support member extends generally axially between a leading edge portion and a trailing edge portion. The leading edge portion is configured to be slidably received within a groove established by the blade outer air seal. A support tab extends radially inward from the main support member toward the blade outer air seal. The support tab configured to contact an extension of the blade outer air seal to limit relative axial movement of the blade outer air seal. A gusset spans between the support tab and the main support member.

    Abstract translation: 叶片外部空气密封支撑组件包括构造成支撑叶片外部空气密封件的主支撑构件。 主支撑构件在前缘部分和后缘部分之间大致轴向地延伸。 前缘部分构造成可滑动地容纳在由叶片外部空气密封件建立的凹槽内。 支撑翼片从主支撑构件朝向叶片外部空气密封件径向向内延伸。 所述支撑突出部构造成接触所述叶片外部空气密封件的延伸部以限制所述叶片外部空气密封件的相对轴向运动。 角撑板跨越支撑片和主支撑件之间。

    BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE
    5.
    发明申请
    BLADE OUTER AIR SEAL FOR GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20190218928A1

    公开(公告)日：2019-07-18

    申请号：US15873496

    申请日：2018-01-17

    Applicant: United Technologies Corporation

    Inventor： Christina G. Ciamarra ,  Brian Barainca ,  Thurman Carlo Dabbs

    IPC: F01D11/10

    CPC classification number: F01D11/10 ,  F01D9/042 ,  F01D11/005 ,  F01D11/08 ,  F01D11/22 ,  F01D25/246 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2260/96

    Abstract: An assembly for use in a turbine section of a gas turbine engine, the assembly including: a blade outer air seal having a forward end and opposite aft end and a pair of opposing sides extending between the forward end and the opposite aft end; a blade outer air seal support, the blade outer air seal support having a rail with at least one scalloped opening, the rail engaging a hook located at the forward end of the blade outer air seal when the blade outer air seal is secured to the blade outer air seal support, wherein two points of contact are made between the hook and the rail of the blade outer air seal support when the blade outer air seal is secured to the blade outer air seal support; and a vane platform, that receives and supports a rail of the blade outer air seal, the rail being located at the aft end of the blade outer air seal and the rail extends continuously between the pair of opposing sides of the blade outer air seal, wherein a single point of contact is made between the rail of the blade outer air seal and the vane platform when the blade outer air seal is secured to the vane platform.

    BOAS HAVING RADIALLY EXTENDED PROTRUSIONS
    6.
    发明申请
    BOAS HAVING RADIALLY EXTENDED PROTRUSIONS 审中-公开

    公开(公告)号：US20190211701A1

    公开(公告)日：2019-07-11

    申请号：US15863152

    申请日：2018-01-05

    Applicant: United Technologies Corporation

    Inventor： Christina G. Ciamarra ,  Brian Barainca ,  Thurman Carlo Dabbs

    IPC: F01D11/08 ,  F16J15/44

    Abstract: A blade outer air seal may comprise an arcuate segment. The arcuate segment may comprise an aft wall having a first radially extending protrusion at a circumferential end of the aft wall. A first hook may extend aft from the aft wall. A first gusset may extend from the first radially extending protrusion. A radial height of the first radially extending protrusion may be greater than a radial height of a second radially extending protrusion of the aft wall.

    GAS TURBINE ENGINE BLADE OUTER AIR SEAL COOLING HOLE CONFIGURATION
    8.
    发明申请
    GAS TURBINE ENGINE BLADE OUTER AIR SEAL COOLING HOLE CONFIGURATION 审中-公开

    公开(公告)号：US20190128134A1

    公开(公告)日：2019-05-02

    申请号：US15798763

    申请日：2017-10-31

    Applicant: United Technologies Corporation

    Inventor： Terence P. Tyler ,  Thurman Carlo Dabbs ,  Kevin J. Ryan ,  Nathan K. Galle

    IPC: F01D11/08 ,  F01D25/12

    Abstract: A blade outer air seal includes a body that extends axially between forward and aft rails and circumferentially between lateral faces. The body has an inner arcuate surface that is configured to seal relative to a blade tip. The body includes a plurality of cooling holes that extend through an exterior surface of the body. Each of the plurality of cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Tables 1, 2 and 3. Each of the geometric coordinates is measured from a reference point on the body.

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