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    AXIAL NON-LINEAR INTERFACE FOR COMBUSTOR LINER PANELS IN A GAS TURBINE COMBUSTOR
    52.
    发明申请
    AXIAL NON-LINEAR INTERFACE FOR COMBUSTOR LINER PANELS IN A GAS TURBINE COMBUSTOR 审中-公开

    公开(公告)号：US20180128486A1

    公开(公告)日：2018-05-10

    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.

    COATED COOLING PASSAGE
    54.
    发明申请
    COATED COOLING PASSAGE 审中-公开
    涂层冷却通道

    公开(公告)号：US20160273391A1

    公开(公告)日：2016-09-22

    申请号：US15029525

    申请日：2014-09-04

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Steven W. Burd ,  Christopher R. Brdar ,  Derk S. Philippona

    IPC: F01D25/30 ,  F01D25/14

    Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.

    Abstract translation: 用于燃气涡轮发动机的部件包括具有基板孔的基板和在基板上延伸一定长度的基板孔的涂层。 用于燃气涡轮发动机的衬套组件包括具有多个孔的热板和在热片上的涂层，其延伸多个孔的每一个的长度。 一种形成用于在燃气涡轮发动机的部件中提供膜冷却的孔的方法包括在基板中形成多个基板孔。 多个基板孔中的每一个限定基板内周边。 在形成多个基板孔之后，在基板上施加涂层以至少部分地在多个基板孔内的每一个中限定涂层内周边。 涂层内周面小于基板内周。

    COMBUSTOR WALL WITH METALLIC COATING ON COLD SIDE
    55.
    发明申请
    COMBUSTOR WALL WITH METALLIC COATING ON COLD SIDE 审中-公开
    COMBUSTOR墙与金属涂层在冷边

    公开(公告)号：US20160195273A1

    公开(公告)日：2016-07-07

    申请号：US14972208

    申请日：2015-12-17

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd ,  John S. Tu

    IPC: F23R3/00 ,  F23R3/06

    Abstract: A combustor includes a combustion chamber and a combustor wall that at least partially bounds the combustion chamber. The combustor wall includes a first side that faces the combustion chamber and a second side that faces away from the combustion chamber. The second side includes an array of geometric surface features for thermal transfer. A metallic coating is disposed on at least a portion of the second side of the combustor wall.

    Abstract translation: 燃烧器包括至少部分地限定燃烧室的燃烧室和燃烧器壁。 燃烧器壁包括面向燃烧室的第一侧和面向燃烧室的第二侧。 第二面包括用于热转印的几何表面特征阵列。 金属涂层设置在燃烧器壁的第二侧的至少一部分上。

    Pressure Seal With Non-Metallic Wear Surfaces
    56.
    发明申请
    Pressure Seal With Non-Metallic Wear Surfaces 审中-公开
    非金属磨损表面的压力密封

    公开(公告)号：US20160146032A1

    公开(公告)日：2016-05-26

    申请号：US15011720

    申请日：2016-02-01

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F01D11/02 ,  F16J15/447

    CPC classification number: F01D11/02 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2300/432 ,  F16J15/447 ,  F16J15/54 ,  Y02T50/672

    Abstract: A gas turbine engine has a first component and a second component. The first and second components have a high-pressure chamber on one side and a low pressure chamber on an opposed side. A three sided seal has one side facing each of the first and second components, and a third side facing a third component. At least one non-metallic wear surface is between one of the three sides of the seal and the facing component.

    Abstract translation: 燃气涡轮发动机具有第一部件和第二部件。 第一和第二部件在一侧具有高压室，在相对侧具有低压室。 三面密封件具有面对第一和第二部件中的每一个的一侧和面向第三部件的第三侧。 至少一个非金属磨损表面位于密封件的三个侧面之一和面对部件之间。

    Pressure seal with non-metallic wear surfaces
    57.
    发明授权
    Pressure seal with non-metallic wear surfaces 有权
    带非金属磨损表面的压力密封

    公开(公告)号：US09322288B2

    公开(公告)日：2016-04-26

    申请号：US13688340

    申请日：2012-11-29

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F01D11/00 ,  F16J15/54

    CPC classification number: F01D11/02 ,  F01D11/005 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2300/432 ,  F16J15/447 ,  F16J15/54 ,  Y02T50/672

    Abstract: A gas turbine engine has a pair of components having a high-pressure chamber on one side, and a low pressure chamber on an opposed side. A three-sided seal has one side in sealing contact with each of said components. A third side is associated with a third component. At least one non-metallic wear surface is positioned between one of the three sides of the seal and its respective component.

    Abstract translation: 一种燃气涡轮发动机具有一对在一侧具有高压室的部件和在相对侧的低压室。 三面密封件具有与每个所述部件密封接触的一侧。 第三侧与第三组件相关联。 至少一个非金属磨损表面位于密封件的三个侧面之一和其相应的部件之间。

    FILM COOLING CIRCUIT FOR A COMBUSTOR LINER
    58.
    发明申请
    FILM COOLING CIRCUIT FOR A COMBUSTOR LINER 审中-公开
    电磁线圈电缆冷却电路

    公开(公告)号：US20160069569A1

    公开(公告)日：2016-03-10

    申请号：US14843578

    申请日：2015-09-02

    Applicant: United Technologies Corporation

    Inventor： Steven W. Burd

    IPC: F23R3/06

    CPC classification number: F23R3/06 ,  F05D2230/13 ,  F05D2230/30 ,  F05D2230/90 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03042 ,  F23R2900/03043 ,  Y02T50/675 ,  Y02T50/6765

    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.

    Abstract translation: 燃烧器壁组件的衬套通常限定燃烧室，并且包括膜冷却回路，其具有通过衬套的衬底的热面连通的通道。 电路的孔径由衬底限定，延伸穿过冷面并与通道流体连通。 衬底的热面覆盖有延伸并且因此限定通道的涂层。 薄膜冷却孔延伸穿过涂层并与通道流体连通。 一种制造该电路的方法包括用该孔和孔浇注该基板; 然后在将涂层涂覆在衬底上并插入之前将插入物放入通道中。 然后移除插入物，并通过涂层形成膜冷却孔。

    COATING FOR COOLING AIR HOLES
    59.
    发明申请
    COATING FOR COOLING AIR HOLES 有权
    用于冷却空气的涂层

    公开(公告)号：US20140349029A1

    公开(公告)日：2014-11-27

    申请号：US14455965

    申请日：2014-08-11

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Steven W. Burd

    IPC: B05D5/00

    CPC classification number: B05D5/005 ,  F01D5/005 ,  F01D5/186 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2250/52 ,  F05D2300/2282 ,  Y10T428/24273

    Abstract: A method of repairing a component removes a prior coating from an underlying metal substrate. Small cooling air holes extend through the substrate and the coating that is to be removed. A new coating layer is placed on the metal substrate, and over the existing cooling air holes. The location of the cooling air holes is identified by inspecting the coated component for the location of indicators of the coating passing over the cooling air holes. The identified location of the indicators is used to control a cutting tool to remove any new coating from the cooling air holes. The basic method may also benefit new manufacture.

    Abstract translation: 修复组分的方法从下面的金属基底去除先前的涂层。 小的冷却空气孔延伸穿过基底和待除去的涂层。 新的涂层被放置在金属基底上，并且在现有的冷却空气孔上。 冷却空气孔的位置通过检查涂覆部件来识别通过冷却空气孔的涂层的指示器的位置。 指示器的识别位置用于控制切割工具以从冷却空气孔中移除任何新的涂层。 基本方法也可能有利于新制造。

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