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    Gas turbine engine cooling hole with circular exit geometry
    101.
    发明授权
    Gas turbine engine cooling hole with circular exit geometry 有权
    具有圆形出口几何形状的燃气轮机发动机冷却孔

    公开(公告)号：US09376920B2

    公开(公告)日：2016-06-28

    申请号：US13629705

    申请日：2012-09-28

    Applicant: United Technologies Corporation

    Inventor： John McBrien ,  Brandon W. Spangler ,  Matthew A. Devore

    IPC: F01D5/18 ,  F23R3/00 ,  F23R3/06

    CPC classification number: F01D5/186 ,  F05D2250/14 ,  F05D2250/141 ,  F05D2250/314 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00018 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.

    Abstract translation: 燃气涡轮发动机部件包括具有外表面的结构。 冷却孔从冷却通道延伸到外表面，以在外表面上形成大致圆形形状的出口区域。 燃气涡轮发动机包括压缩机部和涡轮部。 在压缩机和涡轮机部分之间提供燃烧器。 压缩机和涡轮机部分中的至少一个中的部件具有外表面。 薄膜冷却孔从冷却通道延伸到外表面以提供基本上圆形的出口区域。 一种加工薄膜冷却孔的方法包括提供具有内部冷却通道和外部表面的部件，从外表面到内部冷却通道加工薄膜冷却孔，以在外部表面上提供基本上圆形的出口区域。

    FLAPPER SEAL APPARATUS AND SYSTEM
    103.
    发明申请
    FLAPPER SEAL APPARATUS AND SYSTEM 审中-公开
    闪光密封装置和系统

    公开(公告)号：US20150354385A1

    公开(公告)日：2015-12-10

    申请号：US14660585

    申请日：2015-03-17

    Applicant: United Technologies Corporation

    Inventor： Richard N. Allen ,  Brandon W. Spangler

    IPC: F01D11/00 ,  F01D9/02

    CPC classification number: F01D9/065 ,  F01D5/189 ,  F05D2240/55 ,  Y02T50/672 ,  Y02T50/676

    Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.

    Abstract translation: 提供了用于隔离第一压力和/或第一流量和第二压力和/或第二流量的发动机部件。 发动机部件可以包括主体部分，第一密封元件和第二密封元件。 主体部分可以包括第一支架和第二支架。 第一密封元件容纳在主体部分内。 第二密封元件也可以容纳在主体部分内。 第二密封元件可以联接到第一密封元件。

    Turbomachine blade
    104.
    发明授权
    Turbomachine blade 有权

    公开(公告)号：US11261737B1

    公开(公告)日：2022-03-01

    申请号：US15871260

    申请日：2018-01-15

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Snyder ,  Edwin Otero ,  Di Wu ,  Timothy Charles Nash ,  Brandon W. Spangler

    IPC: F01D5/28 ,  F01D5/16 ,  F01D5/14 ,  F01D5/18

    Abstract: A turbomachine airfoil element comprises an airfoil having: an inboard end; an outboard end; a leading edge; a trailing edge; a pressure side; and a suction side. A span between the inboard end and the outboard end is 1.35-1.65 inches. A chord length at 50% span is 1.20-1.60 inches. At least two of: a first mode resonance frequency is 2858±10% Hz; a second mode resonance frequency is 4916±10% Hz; a third mode resonance frequency is 7160±10% Hz; a fourth mode resonance frequency is 10268±10% Hz; a fifth mode resonance frequency is 14235±10% Hz; and a sixth mode resonance frequency is 15088±10% Hz.

    Hourglass airfoil cooling configuration
    105.
    发明授权
    Hourglass airfoil cooling configuration 有权

    公开(公告)号：US11111857B2

    公开(公告)日：2021-09-07

    申请号：US16515528

    申请日：2019-07-18

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler

    IPC: F02C7/18 ,  F01D5/18 ,  F01D25/12 ,  B22C7/00

    Abstract: In one exemplary embodiment, an airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls also extend in a radial direction to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction walls. The cooling passage has a first width in the chord-wise direction near the suction side wall. A second width is in the chord-wise direction near the pressure side wall. A third width is between the pressure and suction side walls. The third width is smaller than the first and second widths.

    Gas turbine engine airfoil having serpentine fed platform cooling passage
    106.
    发明授权
    Gas turbine engine airfoil having serpentine fed platform cooling passage 有权

    公开(公告)号：US11047241B2

    公开(公告)日：2021-06-29

    申请号：US15022622

    申请日：2014-09-12

    Applicant: United Technologies Corporation

    Inventor： Scott W. Gayman ,  Brandon W. Spangler

    IPC: F01D5/18

    Abstract: A gas turbine engine airfoil includes a platform, and spaced apart walls that provide an exterior airfoil surface that extends radially from the platform to an end opposite the platform. A serpentine cooling passage is arranged between the walls and has a first passageway that extends from the platform toward the end and a second passageway fluidly connecting to the first passageway and extending from the end toward the platform to an end. A platform cooling passageway is fluidly connected to the end and extends transversely into the platform. A cooling hole fluidly connects the platform cooling passageway to an exterior surface.

    AIRFOIL TURN CHANNEL WITH SPLIT AND FLOW-THROUGH
    107.
    发明申请
    AIRFOIL TURN CHANNEL WITH SPLIT AND FLOW-THROUGH 有权

    公开(公告)号：US20210148237A1

    公开(公告)日：2021-05-20

    申请号：US16686696

    申请日：2019-11-18

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler

    IPC: F01D5/18 ,  F02C7/12

    Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a first side, and a second side. Radially-extending ribs partition the interior cavity of the airfoil into first and second cooling channels and a radial cooling passage that is situated between the first and second cooling channels. The cooling channels extend to respective first and second channel ends. A turn channel connects the first and second channel ends. The turn channel splits at the first channel end into first and second channel legs such that there is a region between the first and second channel legs. The channels legs merge at the second channel end. The radial cooling passage extends through the region between the first and second channel legs.

    AIRFOIL WITH RIBS HAVING CONNECTOR ARMS AND APERTURES DEFINING A COOLING CIRCUIT
    108.
    发明申请
    AIRFOIL WITH RIBS HAVING CONNECTOR ARMS AND APERTURES DEFINING A COOLING CIRCUIT 有权

    公开(公告)号：US20210054746A1

    公开(公告)日：2021-02-25

    申请号：US16545451

    申请日：2019-08-20

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  David R. Pack

    IPC: F01D5/18 ,  F01D5/14

    Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and first and second sides joining the leading end and the trailing end. First and second ribs each connect the first and second sides of the airfoil wall. Each of the first and second ribs define a tube portion that circumscribes a rib passage and includes cooling apertures, and first and second connector arms that solely join the tube portion to, respectively, the first and second sides of the airfoil wall. The airfoil wall and the first and second ribs bound a cooling channel there between. The cooling apertures of the first and second ribs open at the cooling channel such that there is a cooling circuit in which the rib passages of the first and second ribs are fluidly connected through the cooling apertures and the cooling channel

    HOURGLASS AIRFOIL COOLING CONFIGURATION
    109.
    发明申请
    HOURGLASS AIRFOIL COOLING CONFIGURATION 有权

    公开(公告)号：US20210017906A1

    公开(公告)日：2021-01-21

    申请号：US16515528

    申请日：2019-07-18

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler

    IPC: F02C7/18 ,  F01D5/18 ,  F01D25/12

    Abstract: In one exemplary embodiment, an airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls also extend in a radial direction to provide an exterior airfoil surface. A cooling passage is arranged between the pressure and suction walls. The cooling passage has a first width in the chord-wise direction near the suction side wall. A second width is in the chord-wise direction near the pressure side wall. A third width is between the pressure and suction side walls. The third width is smaller than the first and second widths.

    Cooling hole for a gas turbine engine component
    110.
    发明授权
    Cooling hole for a gas turbine engine component 有权

    公开(公告)号：US10822971B2

    公开(公告)日：2020-11-03

    申请号：US16283279

    申请日：2019-02-22

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler ,  Dominic J. Mongillo

    IPC: F01D9/02 ,  F01D5/18 ,  F01D9/06 ,  F23R3/00 ,  F01D11/20 ,  F01D5/28

    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall having an internal surface and an outer skin, a cooling hole having an inlet extending from the internal surface and merging into a metering section, and a diffusion section downstream of the metering section that extends to an outlet located at the outer skin. The diffusion section of the cooling hole includes a first side diffusion angle, a second side diffusion angle and a downstream diffusion angle at a downstream surface of the diffusion section, the downstream diffusion angle being less than the first side diffusion angle and the second side diffusion angle.

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