Weave control grid
    1.
    发明授权

    公开(公告)号:US11492733B2

    公开(公告)日:2022-11-08

    申请号:US16798023

    申请日:2020-02-21

    Abstract: Disclosed is a weaving method including placing a first section of a fill fiber between warp fibers, forming a pick, moving a base to reposition the warp fibers, and placing a second section of the fill fiber between the warp fibers to form a woven structure, wherein at least a portion of the warp fibers are introduced to the woven structure using a weave control grid. Also disclosed is a weaving assembly including a base, a base positional controller, a weave control grid, warp fiber arms, a warp fiber arm positional controller and a fill fiber wand.

    Pre-diffuser for a gas turbine engine

    公开(公告)号:US11384936B2

    公开(公告)日:2022-07-12

    申请号:US16376451

    申请日:2019-04-05

    Abstract: A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts; and a multiple of diffusion passage ducts attached to the ring-strut-ring structure. A pre-diffuser for a gas turbine engine includes an exit guide vane ring having a multiple of exit guide vanes defined around an engine longitudinal axis; a ring-strut-ring structure adjacent to the exit guide vane ring to form a multiple of diffusion passages defined around the engine longitudinal axis, an inlet to each of the multiple of diffusion passages smaller than an exit from each of the multiple diffusion passage through the ring-strut-ring structure; a diffusion passage duct attached to the ring-strut-ring structure at the exit from each of the multiple diffusion passage.

    BALANCED COMPOSITE ROOT REGION FOR A BLADE OF A GAS TURBINE ENGINE

    公开(公告)号:US20210310363A1

    公开(公告)日:2021-10-07

    申请号:US16841126

    申请日:2020-04-06

    Abstract: A rotor blade for a gas turbine engine including an inner ply layer group includes a flared region and an airfoil region, a neck region between the flared region and the airfoil region; and a platform shell that comprises a platform shell root region, a platform shell platform region, and a platform shell neck region between the platform shell root region and the platform shell platform region, the platform shell root region sheathes the flared region, and the platform shell neck region flares outwardly away from the neck region to intersect the platform shell platform region at a platform shell neck region perimeter around an airfoil opening perimeter.

    CMC COMPONENT WITH COOLING PROTECTION

    公开(公告)号:US20210246795A1

    公开(公告)日:2021-08-12

    申请号:US16784346

    申请日:2020-02-07

    Abstract: A gas turbine engine component includes a ceramic matrix composite (CMC) body that includes an interior surface that defines a blind cavity. A barrier coating is disposed on an exterior of the CMC body. A ceramic body in the blind cavity lines at least a portion of the interior surface of the CMC body. The ceramic body defines an open, interconnected network of pores.

    CERAMIC MATRIX COMPOSITE ROTOR BLADE ATTACHMENT AND METHOD OF MANUFACTURE THEREFOR

    公开(公告)号:US20210102468A1

    公开(公告)日:2021-04-08

    申请号:US16590925

    申请日:2019-10-02

    Abstract: A process for manufacturing a composite rotor blade includes manufacturing an oversized root region of a root region of a composite rotor blade; fixturing the CMC blade into a machining fixture at a primary Y and Z axis datum located at an attachment fillet radii of the root region; machining V-notches into the oversized root region to form a Y′ and Z′ axis datum of a sacrificial datum system in relation to the primary Y and Z axis datum; applying an oversized coating layer over the attachment fillet radii of the root region; fixturing the CMC blade into a machining fixture at the Y′ and Z′ axis datum of the sacrificial datum system; machining the oversized coating layer to a machined coating layer forming a Y″ and Z″ axis datum with respect to the Y′ and Z′ axis datum of the sacrificial datum system; fixturing the CMC blade into a machining fixture at the Y″ and Z″ axis datum; and machining off the sacrificial datum system removing the V-notches.

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