公开(公告)号：US11492733B2

公开(公告)日：2022-11-08

申请号：US16798023

申请日：2020-02-21

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: D03D23/00 ,  D03D41/00 ,  D03D49/02

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.

公开(公告)号：US11421543B2

公开(公告)日：2022-08-23

申请号：US16202868

申请日：2018-11-28

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Scott D. Virkler

IPC: F01D11/02 ,  F16J15/44 ,  F01D11/00 ,  F02C7/28 ,  F01D11/16

Abstract: A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

公开(公告)号：US11384936B2

公开(公告)日：2022-07-12

申请号：US16376451

申请日：2019-04-05

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Matthew Andrew Hough ,  Pedro Rivero

IPC: F23R3/10 ,  F04D29/54 ,  F01D9/04

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.

公开(公告)号：US11359506B2

公开(公告)日：2022-06-14

申请号：US16740645

申请日：2020-01-13

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D9/02 ,  F01D9/04 ,  F01D11/08 ,  F01D17/16

Abstract: A vane ring for a gas turbine engine includes a contoured stop that extends from the static flowpath wall, the contoured stop being of an airfoil shape such that a first side of the contoured stop matches a portion of a first side of the first variable vane along a chord length when the first variable vane is pivoted about the longitudinal axis to a first position.

公开(公告)号：US11215084B2

公开(公告)日：2022-01-04

申请号：US16780016

申请日：2020-02-03

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Scott D. Virkler

IPC: F01D25/28 ,  F01D5/02 ,  F01D9/04

Abstract: A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.

公开(公告)号：US20210310363A1

公开(公告)日：2021-10-07

申请号：US16841126

申请日：2020-04-06

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey

IPC: F01D5/28 ,  F01D5/14

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.

公开(公告)号：US20210262354A1

公开(公告)日：2021-08-26

申请号：US16797133

申请日：2020-02-21

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Bryan P. Dube

IPC: F01D5/28 ,  F01D5/14 ,  B28B1/00

Abstract: Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The fibrous core has a three dimensional braided structure and cooling passages. A method of making the ceramic matrix component is also disclosed.

公开(公告)号：US20210246795A1

公开(公告)日：2021-08-12

申请号：US16784346

申请日：2020-02-07

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Bryan P. Dube

IPC: F01D5/18 ,  F01D5/28

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.

公开(公告)号：US20210102468A1

公开(公告)日：2021-04-08

申请号：US16590925

申请日：2019-10-02

Applicant: United Technologies Corporation

Inventor： Michael G. McCaffrey ,  Karl A. Mentz ,  Christopher King ,  Stephen D. Doll ,  Aurelia Ledbetter

IPC: F01D5/28

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.

公开(公告)号：US10969103B2

公开(公告)日：2021-04-06

申请号：US14912132

申请日：2014-08-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Hoyt Y. Chang ,  Michael G. McCaffrey

IPC: F23R3/60 ,  F23R3/00 ,  F02K1/82 ,  F01D11/08 ,  F23M5/04 ,  F02C7/24

Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including a plate, a frame attached to the plate, and a panel. The panel is supported by the frame.