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    INFINITELY DIRECTIONAL TRANSLATING CLAMP FOR WELDING A FAN BLADE COVER
    31.
    发明申请
    INFINITELY DIRECTIONAL TRANSLATING CLAMP FOR WELDING A FAN BLADE COVER 审中-公开

    公开(公告)号：US20200254588A1

    公开(公告)日：2020-08-13

    申请号：US16269728

    申请日：2019-02-07

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales

    IPC: B25B5/06 ,  B25B5/02

    Abstract: A directional translating clamping device comprises a housing that includes a distal housing end and proximate housing end separated along a central axis, and a housing recess at the proximate housing end and extending along the central axis end. The device also includes a slide located in the housing recess, and the slide comprises a slide recess at a slide proximate end co-axial with the housing recess, and a detent in a radial sidewall of the slide prevents the slide from translating beyond a predetermined axial distance along the central axis. A spring is located in the housing recess and exerts an axial force on the distal end of the slide. A stub shaft extends from the distal end of the housing. A roller ball assembly includes a threaded sidewall that engages with the slide recess to removably and replaceably secure the roller ball assembly to the slide.

    WELD CONFIGURATION
    32.
    发明申请
    WELD CONFIGURATION 审中-公开

    公开(公告)号：US20200049350A1

    公开(公告)日：2020-02-13

    申请号：US16658520

    申请日：2019-10-21

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： Daniel A. Bales

    IPC: F23R3/28 ,  F02C7/22 ,  B23K31/02

    Abstract: A float assembly according to an example of the present disclosure includes a guide extending in a first direction that has a stand-up and a shelf. A cover is oriented in a second direction substantially perpendicular to the first direction and welded to the stand-up at a weld joint. An undersurface of the cover abuts the shelf, and the abutment begins at a first distance in the second direction from the weld joint and ends at a second distance in the second direction from the weld joint.

    Uber-cooled turbine section component made by additive manufacturing
    35.
    发明授权
    Uber-cooled turbine section component made by additive manufacturing 有权
    Uber冷却涡轮机部件由添加剂制造制成

    公开(公告)号：US09393620B2

    公开(公告)日：2016-07-19

    申请号：US13714561

    申请日：2012-12-14

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Agnes Klucha ,  Gregory M. Dolansky

    IPC: B22F5/04 ,  B33Y10/00 ,  B22F3/105 ,  B33Y30/00 ,  B33Y80/00

    CPC classification number: B22F5/04 ,  B22F3/1055 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y50/00 ,  B33Y80/00 ,  Y02P10/295 ,  Y10T29/49339 ,  Y10T29/49341

    Abstract: A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.

    Abstract translation: 具有内部冷却通道的燃气轮机翼型通过附加制造形成。 超级合金粉末的层通过能量束熔合，使用二维图案，提供在其中形成通道的未熔化区域。 使用足够的二维图案加入并熔化粉末层，以形成具有所需图案的内部冷却通道的整个翼型。 在翼型形成完成之后，可以进行热等静压，定向重结晶，粘结涂层，并覆盖有热障层。

    Powder metallurgy method using a four-wall cylindrical canister
    38.
    发明授权
    Powder metallurgy method using a four-wall cylindrical canister 有权

    公开(公告)号：US12233461B2

    公开(公告)日：2025-02-25

    申请号：US16590644

    申请日：2019-10-02

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Andrew L. Haynes

    IPC: B22F3/15

    Abstract: A powder metallurgy method includes a canister that has canister walls that define a hermetic chamber that circumscribes an open central region. A metallic alloy powder is inserted into the hermetic chamber, followed by evacuating the hermetic chamber. The canister with the metallic alloy powder is then subjected to a hot isostatic pressing process that includes heating the canister and the metallic alloy powder and applying isostatic pressure to the canister. The heating and the isostatic pressure causes fusion and consolidation of the metallic alloy powder to form a solid workpiece. The canister is then removed from the solid workpiece.

    Method for removing refractory metal cores
    39.
    发明授权
    Method for removing refractory metal cores 有权

    公开(公告)号：US11325182B2

    公开(公告)日：2022-05-10

    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 ,  F27B5/00 ,  F27B5/02 ,  F27B5/06

    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.

    Hybridized airfoil for a gas turbine engine
    40.
    发明授权
    Hybridized airfoil for a gas turbine engine 有权

    公开(公告)号：US11248477B2

    公开(公告)日：2022-02-15

    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: F01D5/14 ,  F01D5/30 ,  B23K1/00 ,  F04D29/38 ,  B23K101/00

    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.

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