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    Oscillating tube having a segmented coating for damping the tube
    44.
    发明授权
    Oscillating tube having a segmented coating for damping the tube 有权
    振荡管具有用于阻尼管的分段涂层

    公开(公告)号：US08727069B1

    公开(公告)日：2014-05-20

    申请号：US13705942

    申请日：2012-12-05

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F16L11/26

    CPC classification number: F16L55/0336 ,  F16L55/0335 ,  Y10T29/49885

    Abstract: The oscillating tube (10) includes a first end (12), an opposed second end (16), and a fluid conduit (18) defined by the tube extending between the opposed ends (12, 16). A segmented damping coating (20) covers in intimate contact a covered or coated portion (22) of the tube (10) so that the coated portion (22) of the tube includes at least about ten percent of an axial length of the tube and an uncoated portion (34, 36) that is not covered by the segmented damping coating (22) includes greater than about ten percent of an axial length of the tube (10). The segmented damping coating (20) may include polymers, polytetrafluoroethylene, single composition polymers, ceramic fibers, polymer fibers, reinforced polymer fibers including a polytetrafluoroethylene, ceramics, including monolithic and matrix ceramics, thermoplastics, carbon/graphic materials, silicon materials, metal rings or clamps, and combinations thereof.

    Abstract translation: 振荡管（10）包括第一端（12），相对的第二端（16）和由在相对端（12,16）之间延伸的管限定的流体导管（18）。 分段阻尼涂层（20）紧密地覆盖管（10）的覆盖或涂覆部分（22），使得管的涂覆部分（22）包括管的轴向长度的至少约百分之十， 未被分段阻尼涂层（22）覆盖的未涂覆部分（34,36）包括大于管（10）的轴向长度的约百分之十。 分段阻尼涂层（20）可以包括聚合物，聚四氟乙烯，单一组合物聚合物，陶瓷纤维，聚合物纤维，包括聚四氟乙烯的增强聚合物纤维，包括整体和基体陶瓷的陶瓷，热塑性塑料，碳/图形材料，硅材料，金属环 或夹具，及其组合。

    Axial non-linear interface for combustor liner panels in a gas turbine combustor
    45.
    发明授权
    Axial non-linear interface for combustor liner panels in a gas turbine combustor 有权

    公开(公告)号：US10830433B2

    公开(公告)日：2020-11-10

    申请号：US15348679

    申请日：2016-11-10

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F23R3/00 ,  F23R3/60

    Abstract: A combustor for a gas turbine engine including a non-linear axial edge between the forward edge and the aft edge. A combustor for a gas turbine engine including a multiple of forward liner panels circumferentially mounted within the support shell via a multiple of studs, each of the multiple of forward liner panels having a non-linear axial edge therebetween to define a forward non-linear interface between each adjacent pair of the multiple of forward liner panels and a multiple of aft liner panels circumferentially mounted within the support shell via a multiple of studs aft of the multiple of forward liner panels, each of the multiple of aft liner panels having an aft non-linear axial edge therebetween to define a non-linear interface between each adjacent pair of the multiple of aft liner panels.

    Single-walled combustor for a gas turbine engine and method of manufacture
    46.
    发明授权
    Single-walled combustor for a gas turbine engine and method of manufacture 有权

    公开(公告)号：US10788210B2

    公开(公告)日：2020-09-29

    申请号：US14849017

    申请日：2015-09-09

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F23R3/00 ,  F23R3/06 ,  F23M5/08 ,  F02C7/18 ,  F23R3/50

    Abstract: A single-walled combustor includes a multi-layered wall having a first face defining a cooling plenum and an opposite second face. A thermal barrier coating of the wall may be secured to the second face and defines at least in-part a combustion chamber. A plurality of cooling circuits each extend through the base layer and the thermal barrier coating for flowing cooling air from the plenum and into the combustion chamber. Each circuit includes a first surface recessed from the second face and spaced from the thermal barrier coating with a channel defined in-part by the first surface and covered by the thermal barrier coating. A hole in the thermal barrier coating is in fluid communication between the channel and the combustion chamber. A method of manufacturing the circuit includes fabricating the base layer with the aperture and hole; then placing an insert into the channel prior to application of the coating over the base layer and insert. The insert is then removed and the film cooling hole is formed through the coating.

    Film cooling circuit for a combustor liner
    47.
    发明授权
    Film cooling circuit for a combustor liner 有权

    公开(公告)号：US10731857B2

    公开(公告)日：2020-08-04

    申请号：US14843578

    申请日：2015-09-02

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F23R3/06 ,  F23R3/00

    Abstract: A liner of a combustor wall assembly generally defines a combustion chamber and includes a film cooling circuit having a channel communicating through a hot face of a substrate of the liner. An aperture of the circuit is defined by the substrate, extends through the cold face and is in fluid communication with the channel. The hot face of the substrate is covered with a coating that extends over and thus defines in-part the channel. A film cooling hole extends through the coating and is in fluid communication with the channel. A method of manufacturing the circuit includes casting the substrate with the aperture and hole; then placing an insert into the channel prior to application of the coating over the substrate and insert. The insert is then removed and the film cooling hole is formed through the coating.

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