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    BLADE OUTER AIR SEAL INCLUDING COOLING TRENCH
    74.
    发明申请
    BLADE OUTER AIR SEAL INCLUDING COOLING TRENCH 有权

    公开(公告)号：US20210148247A1

    公开(公告)日：2021-05-20

    申请号：US16686609

    申请日：2019-11-18

    Applicant: United Technologies Corporation

    Inventor： Winston Gregory Smiddy ,  San Quach ,  Matthew D. Parekh ,  Jeffrey T. Morton

    IPC: F01D25/12 ,  F01D11/00

    Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a core flowpath, and a turbine fluidly connected to the combustor via the core flowpath. The turbine includes at least one stage having a plurality of rotors and a plurality of vanes. An outer diameter of the core flowpath at at least one stage is at least partially defined by a set of circumferentially arranged blade outer air seals. Each blade outer air seal includes a platform. An internal cooling cavity is defined within the platform. At least one mateface of the platform includes a cooling trench, and a first set of cooling holes connecting the internal cavity to the cooling trench.

    DEFLECTOR FOR COMBUSTOR OF GAS TURBINE ENGINE
    76.
    发明申请
    DEFLECTOR FOR COMBUSTOR OF GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20190368735A1

    公开(公告)日：2019-12-05

    申请号：US15995508

    申请日：2018-06-01

    Applicant: United Technologies Corporation

    Inventor： Kristy Rose Riley ,  John R. Battye ,  Joanne V. Rampersad ,  San Quach

    IPC: F23R3/00 ,  F23R3/28 ,  F02C3/04

    Abstract: A deflector panel for a combustor of a gas turbine engine includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge including a panel scallop at least partially defining a deflector opening receptive of a fuel nozzle of the combustor. A combustor of a gas turbine engine includes a combustor shell at least partially defining a combustion zone therein, and a deflector assembly operably connected to the combustor shell. The deflector assembly includes a plurality of circumferentially abutted deflector panels. Each deflector panel includes an outer radial edge, an inner radial edge, and two circumferential edges extending between the outer radial edge and the inner radial edge. Each circumferential edge includes a panel scallop at least partially defining a deflector opening. A fuel nozzle extends through the deflector opening.

    Combustor panel endrail interface
    77.
    发明授权
    Combustor panel endrail interface 有权

    公开(公告)号：US10473331B2

    公开(公告)日：2019-11-12

    申请号：US15599159

    申请日：2017-05-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： San Quach ,  Jeffrey T. Morton ,  Matthew D. Parekh

    IPC: F23R3/00 ,  F23R3/06

    Abstract: A combustor of a gas turbine engine may include a combustor shell, a first combustor panel coupled to the combustor shell, and a second combustor panel coupled to the combustor shell. The first combustor panel may have a first endrail and the second combustor panel may have a second endrail. An annular cooling cavity may be defined between the combustor shell and the first and second combustor panels and a channel may be defined between the first endrail and the second endrail, wherein direct line-of-sight through the channel from the annular cooling cavity to a combustor chamber is obstructed. Said differently, the interface between the adjacent endrails may be non-linear, in a direction from the annular cooling cavity to the combustor chamber.

    FLOAT WALL COMBUSTOR PANELS HAVING AIRFLOW DISTRIBUTION FEATURES
    78.
    发明申请
    FLOAT WALL COMBUSTOR PANELS HAVING AIRFLOW DISTRIBUTION FEATURES 审中-公开

    公开(公告)号：US20190128187A1

    公开(公告)日：2019-05-02

    申请号：US15795301

    申请日：2017-10-27

    Applicant: United Technologies Corporation

    Inventor： Jason Shenny ,  John J. Rup, JR. ,  Robert M. Sonntag ,  James B. Hoke ,  San Quach ,  Richard G. Ullrich

    IPC: F02C7/18 ,  F23R3/00 ,  F23R3/04

    Abstract: Combustor panels including panel bodies with first and second sides, a pin array extending from the first side, wherein each pin extends a first height, has a pin diameter, and is separated from adjacent pins by a pin array separation distance. A structural protrusion extends from the first side. No pins of the pin array are located within a flashing distance that is equal to a protrusion separation distance plus half of the pin diameter, wherein a location of the pin is measured from a center point of the pin to a closest point on the exterior surface of the structural protrusion. At least one pin array extension is integrally formed with the structural protrusion, the pin array extension extending along the first side to a position that replaces a pin of the pin array that would be within the flashing distance.

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