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    THERMALLY PROTECTED SEAL ASSEMBLY
    2.
    发明申请
    THERMALLY PROTECTED SEAL ASSEMBLY 审中-公开
    热保护密封组件

    公开(公告)号：US20160084099A1

    公开(公告)日：2016-03-24

    申请号：US14704634

    申请日：2015-05-05

    Applicant: United Technologies Corporation

    Inventor： Timothy M. Davis ,  Michael S. Stevens

    IPC: F01D11/00 ,  F01D11/10 ,  F01D25/24 ,  F16J15/08

    CPC classification number: F16J15/0887 ,  F01D11/003 ,  F05D2240/11 ,  F05D2240/15 ,  F05D2250/75 ,  Y02T50/672

    Abstract: A seal assembly that may be for turbine engine includes first and second rings with a convoluted seal resiliently compressed there-between. The seal may define a gap for receipt of a thermally resistant shield that may also reduce wear of the seal. The seal may include a hole for the flow of cooling air and the shield may be porous so as not to obstruct the cooling air flow for cooling of the seal.

    Abstract translation: 可用于涡轮发动机的密封组件包括具有弹性压缩在其之间的卷积密封件的第一和第二环。 密封件可以限定用于接收耐热屏蔽的间隙，其还可以减少密封件的磨损。 密封件可以包括用于冷却空气流动的孔，并且屏蔽件可以是多孔的，以便不妨碍用于冷却密封件的冷却空气流。

    LOW THERMAL MASS JOINT
    3.
    发明申请
    LOW THERMAL MASS JOINT 审中-公开
    低热量接头

    公开(公告)号：US20150068214A1

    公开(公告)日：2015-03-12

    申请号：US14477964

    申请日：2014-09-05

    Applicant: United Technologies Corporation

    Inventor： Michael S. Stevens ,  Ken F. Blaney

    IPC: F01D25/24

    CPC classification number: F01D25/243 ,  F01D9/041 ,  F01D25/08 ,  F01D25/246 ,  Y02T50/671

    Abstract: A gas turbine engine includes a tangential on-board injector (TOBI) fluidly connected to a compressor section. A diffuser case structurally supports a combustor section and the tangential on-board injector via at least one low thermal mass joint.

    Abstract translation: 燃气涡轮发动机包括流体连接到压缩机部分的切向车载喷射器（TOBI）。 扩散器壳体通过至少一个低热质量接头在结构上支撑燃烧器部分和切向车载喷射器。

    Support ring with thermal heat shield for case flange
    4.
    发明授权
    Support ring with thermal heat shield for case flange 有权

    公开(公告)号：US10808558B2

    公开(公告)日：2020-10-20

    申请号：US15982714

    申请日：2018-05-17

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Michael S. Stevens ,  Christine F. McGinnis ,  Major D. Jones ,  Judith F. Brooks ,  Brian Duguay ,  Tomasz Pelic

    IPC: F01D9/04 ,  F01D9/02 ,  F02K3/06

    Abstract: A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.

    GASKET WITH THERMAL AND WEAR PROTECTIVE FABRIC
    6.
    发明申请
    GASKET WITH THERMAL AND WEAR PROTECTIVE FABRIC 审中-公开
    垫子与热和磨损保护织物

    公开(公告)号：US20160003078A1

    公开(公告)日：2016-01-07

    申请号：US14742788

    申请日：2015-06-18

    Applicant: United Technologies Corporation

    Inventor： Michael S. Stevens ,  Timothy M. Davis

    IPC: F01D11/00 ,  F01D11/08

    CPC classification number: F01D11/005 ,  F05D2240/55 ,  F05D2250/75 ,  F16J15/0887 ,  F16J15/121

    Abstract: The present disclosure relates generally to a gasket assembly for use in a gas turbine engine, the gasket assembly including a gasket component including an outer surface and end portions, and a seal component operably coupled to the outer surface of the gasket component for providing sealing contact.

    Abstract translation: 本公开总体上涉及一种用于燃气涡轮发动机的垫圈组件，所述垫圈组件包括包括外表面和端部的垫圈部件以及可操作地联接到所述垫圈部件的外表面的密封部件，用于提供密封接触 。

    TANGENTIAL ON-BOARD INJECTORS FOR GAS TURBINE ENGINES
    10.
    发明申请
    TANGENTIAL ON-BOARD INJECTORS FOR GAS TURBINE ENGINES 审中-公开

    公开(公告)号：US20170292393A1

    公开(公告)日：2017-10-12

    申请号：US15094603

    申请日：2016-04-08

    Applicant: United Technologies Corporation

    Inventor： Jeffrey Vincent Anastas ,  Michael S. Stevens

    IPC: F01D9/04 ,  F01D5/08

    CPC classification number: F01D9/048 ,  F01D5/082 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2240/126 ,  F05D2240/128 ,  F05D2260/20

    Abstract: A TOBI for a gas turbine engine having a TOBI body, a first TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge, and a second TOBI airfoil circumferentially adjacent to the first TOBI airfoil, the second TOBI airfoil having a radially extending portion extending from a leading edge and an axially extending portion extending toward a trailing edge. An entrance is defined between the leading edges of the adjacent TOBI airfoils and an exit is defined between the trailing edges of the TOBI airfoils, wherein airflow entering the entrance enters in a radial direction relative to the TOBI body and airflow exiting the exit exits in a circumferential direction relative to the TOBI body.

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