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    Airfoil with ribs defining shaped cooling channel
    34.
    发明授权
    Airfoil with ribs defining shaped cooling channel 有权

    公开(公告)号：US12000305B2

    公开(公告)日：2024-06-04

    申请号：US16682453

    申请日：2019-11-13

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  David R. Pack

    IPC: F01D5/18

    CPC classification number: F01D5/189 ,  F05D2220/32 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/22141

    Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.

    Airfoil turn channel with split and flow-through
    35.
    发明授权
    Airfoil turn channel with split and flow-through 有权

    公开(公告)号：US11454124B2

    公开(公告)日：2022-09-27

    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.

    Gas turbine engine component with flow separating rib
    38.
    发明授权
    Gas turbine engine component with flow separating rib 有权

    公开(公告)号：US10774655B2

    公开(公告)日：2020-09-15

    申请号：US15919253

    申请日：2018-03-13

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Gina Cavallo

    IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F01D9/06

    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a wall that extends about a cooling cavity. The cooling cavity is a dual-fed cavity that is fed from at least two different locations. A rib separates the cooling cavity into a first portion and a second portion that is fluidly isolated from the first portion. The component is an airfoil. The first portion is fed with a first cooling fluid from a first coolant source, and the second portion is fed with a second, different cooling fluid from a second coolant source. The first and second coolant sources are separate and distinct from the component.

    TRAILING EDGE PRESSURE AND FLOW REGULATOR
    39.
    发明申请
    TRAILING EDGE PRESSURE AND FLOW REGULATOR 审中-公开

    公开(公告)号：US20200277861A1

    公开(公告)日：2020-09-03

    申请号：US16739254

    申请日：2020-01-10

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Carey Clum ,  Matthew A. Devore

    IPC: F01D5/18 ,  F01D9/06 ,  F02C7/18

    Abstract: A gas turbine engine component comprises a body having a leading edge, a trailing edge, and a radial span. One internal channel in the body provides an upstream supply pressure. Another internal channel in body receives the upstream supply pressure and provides a downstream supply pressure. At least one axial rib separates an internal area adjacent to the trailing edge into a plurality of individual cavities. At least one pressure regulating feature is located at an entrance to at least one individual cavity entrance to control downstream supply pressure to the trailing edge. Exits formed in the trailing edge communicate with an exit pressure. The rib and pressure regulating features cooperate such that the downstream supply pressure mimics the exit pressure along the radial span. A method of manufacturing a gas turbine engine component and a method of controlling flow in a gas turbine engine component are also disclosed.

    BLADE/VANE COOLING PASSAGES
    40.
    发明申请
    BLADE/VANE COOLING PASSAGES 审中-公开

    公开(公告)号：US20200277858A1

    公开(公告)日：2020-09-03

    申请号：US16289341

    申请日：2019-02-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Brandon W. Spangler ,  David R. Pack

    IPC: F01D5/18 ,  F01D5/14 ,  F01D25/12

    Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall and a suction side wall. The suction side wall is configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The blade also includes a plurality of ribs forming a plurality of trapezoidal shaped cavities to receive a cooling airflow. The plurality of ribs being shaped in a way to allow for thermal growth of the airfoil, while minimizing stress in the airfoil.

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