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    Multi-cover gas turbine engine component
    12.
    发明授权
    Multi-cover gas turbine engine component 有权

    公开(公告)号：US11236619B2

    公开(公告)日：2022-02-01

    申请号：US16404774

    申请日：2019-05-07

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Michael DuPont ,  Eric W. Malmborg

    IPC: B23K1/00 ,  F01D5/00 ,  F01D5/18 ,  B23K101/00

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets. The plurality of cover skins formed from a common cover having a perimeter that is dimensioned to mate with the perimeter of the recess. A method of forming a gas turbine engine component is also disclosed.

    Airfoil with cover for gas turbine engine
    13.
    发明授权
    Airfoil with cover for gas turbine engine 有权

    公开(公告)号：US11174737B2

    公开(公告)日：2021-11-16

    申请号：US16828056

    申请日：2020-03-24

    Applicant: United Technologies Corporation

    Inventor： Robert C. Dolan ,  Michael A. Weisse ,  Daniel A. Bales ,  Steven T. Gordon ,  Dmitri Novikov ,  Eric W. Malmborg ,  Francis B. Parisi

    IPC: F01D5/00 ,  F01D5/18

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body defining a recessed region and including at least one rib dimensioned to loop about a respective pocket within a perimeter of the recessed region. At least one cover skin is welded to the airfoil body along the at least one rib to enclose the recessed region. The at least one cover skin is welded to the at least one rib along a respective weld path. The weld path defines a weld width, the at least one rib defines a rib width, and a ratio of the weld width to the rib width is equal to or greater than 3:1 for each position along the weld path. A method of forming a gas turbine engine component is also disclosed.

    Infinitely directional translating clamp for welding a fan blade cover
    14.
    发明授权
    Infinitely directional translating clamp for welding a fan blade cover 有权

    公开(公告)号：US11130212B2

    公开(公告)日：2021-09-28

    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.

    Method of forming gas turbine engine components
    17.
    发明授权
    Method of forming gas turbine engine components 有权

    公开(公告)号：US10808542B2

    公开(公告)日：2020-10-20

    申请号：US16245383

    申请日：2019-01-11

    Applicant: United Technologies Corporation

    Inventor： Daniel A. Bales ,  Thomas DeMichael

    IPC: B23K101/00 ,  F01D5/14 ,  B23K35/38 ,  B23K37/00 ,  B23K37/04

    Abstract: A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to define pressure and suction sides of an airfoil, and moving the airfoil in a forming line including a plurality of stations. The plurality of stations include a set of heating stations, a deforming station and a set of cool down stations. The moving step includes positioning the airfoil in the set of heating stations to progressively increase a temperature of the airfoil, then positioning the airfoil in the deforming station including causing the airfoil to deform between first and second dies, and then positioning the airfoil in the set of cool down stations to progressively decrease the temperature of the airfoil.

    UBER-COOLED TURBINE SECTION COMPONENT MADE BY ADDITIVE MANUFACTURING
    20.
    发明申请
    UBER-COOLED TURBINE SECTION COMPONENT MADE BY ADDITIVE MANUFACTURING 有权
    通过添加剂制造的UBER-COOLED TURBINE SECTION COMPUENT

    公开(公告)号：US20140169981A1

    公开(公告)日：2014-06-19

    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

    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。

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