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    Self-leveling container for laser welding
    41.
    发明授权
    Self-leveling container for laser welding 有权

    公开(公告)号：US11192205B2

    公开(公告)日：2021-12-07

    申请号：US16416238

    申请日：2019-05-19

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales

    IPC: B23K26/12 ,  B23K26/21 ,  B23K37/04

    Abstract: A self-leveling container that contains argon gas for laser welding of a work piece includes a base surface, a plurality of pleated sidewalls, each comprising an associated distal sidewall end and an associated proximate sidewall end, where the proximate sidewall end is sealed to the base surface. A frame includes a plurality of frame segments, each secured to an associated one of the distal sidewall ends. A plurality of actuators, each located with one intersection of the plurality of frame segments, linearly move its associated one intersection of the plurality frame segments so a plane formed by the frame segments remains parallel to a planar surface.

    METHOD FOR REMOVING REFRACTORY METAL CORES
    42.
    发明申请
    METHOD FOR REMOVING REFRACTORY METAL CORES 有权

    公开(公告)号：US20210283681A1

    公开(公告)日：2021-09-16

    申请号：US16816865

    申请日：2020-03-12

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Thomas DeMichael

    IPC: B22D29/00 ,  F27B5/14

    Abstract: A furnace for removing a molybdenum-alloy refractory metal core through sublimation comprising a retort furnace having an interior; a sublimation fixture insertable within the interior of the retort furnace, the sublimation fixture configured to receive at least one turbine blade having the molybdenum-alloy refractory metal core; a flow passage thermally coupled to the retort furnace configured to heat a fluid flowing through the flow passage and deliver the fluid to the molybdenum-alloy refractory metal core causing sublimation of the molybdenum-alloy refractory metal core.

    MECHANICAL ATTACHMENT SCHEME FOR ISOGRID DUCTS
    43.
    发明申请
    MECHANICAL ATTACHMENT SCHEME FOR ISOGRID DUCTS 有权

    公开(公告)号：US20210140345A1

    公开(公告)日：2021-05-13

    申请号：US16677349

    申请日：2019-11-07

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel A. Bales ,  William Bogue ,  Stuart C. Kozan

    IPC: F01D25/24

    Abstract: A clamp for securing a component to an isogrid case of a gas turbine engine includes a top having an attachment feature for coupling the clamp to the component. The clamp further includes a bottom. The clamp further includes two sides extending from the top towards the bottom, each of the two sides being thicker at the bottom than at the top, and the two sides defining a shaped slot closer to the bottom than the top for receiving a rib of the isogrid case.

    HYBRIDIZED AIRFOIL FOR A GAS TURBINE ENGINE
    45.
    发明申请
    HYBRIDIZED AIRFOIL FOR A GAS TURBINE ENGINE 有权

    公开(公告)号：US20210032997A1

    公开(公告)日：2021-02-04

    申请号：US16530917

    申请日：2019-08-02

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Dmitri Novikov ,  Robert C. Dolan ,  Eric W. Malmborg ,  Steven T. Gordon

    IPC: F01D5/30 ,  F01D5/14 ,  F04D29/38 ,  B23K1/00

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, a first portion welded to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section mountable to a rotatable hub. The airfoil section includes an airfoil body extending between leading and trailing edges in a chordwise direction, extending between pressure and suction sides separated in a thickness direction, and extending from the root section in a spanwise direction to a tip portion. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib bounding a respective pocket within a perimeter of the recessed region. A cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. A method of forming a gas turbine engine component is also disclosed.

    Fan blade for a gas turbine engine
    46.
    发明授权
    Fan blade for a gas turbine engine 有权

    公开(公告)号：US10808541B2

    公开(公告)日：2020-10-20

    申请号：US16219164

    申请日：2018-12-13

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Eric W. Malmborg

    IPC: F01D5/14 ,  B23K101/00 ,  B23K26/244

    Abstract: An airfoil includes an airfoil body portion that has a pressure side and a suction side. A recessed area in the airfoil body portion is located on one of the pressure side or the suction side. At least one rib divides the recessed area into at least one geometric shape. A cover encloses the recessed area and includes at least one pedestal that engages a distal end of at least one rib. A weld extends through the cover and a portion of at least one rib. The weld spans a width of the distal end of at least one rib.

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