公开(公告)号：US20240352861A1

公开(公告)日：2024-10-24

申请号：US18304922

申请日：2023-04-21

Applicant: Raytheon Technologies Corporation

Inventor： Emma J. Place ,  Bryan P. Dube ,  Pedro D. Laureano ,  Bernard Joseph Reilly, III ,  Mohamed Hassan ,  Edwin Otero ,  Andrew Correia ,  William R. Hackbarth, II ,  Jeffrey M. Jacques

IPC: F01D5/30 ,  F01D5/02

CPC classification number: F01D5/3007 ,  F01D5/02

Abstract: An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.

公开(公告)号：US11808154B2

公开(公告)日：2023-11-07

申请号：US17952693

申请日：2022-09-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Bryan P. Dube ,  Erik R. Granstand ,  Michael G. McCaffrey ,  Stephen G. Pixton

IPC: F01D11/00 ,  F01D5/14 ,  F01D9/04

CPC classification number: F01D11/005 ,  F01D5/147 ,  F01D9/042 ,  F05D2240/12 ,  F05D2300/6033

Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.

公开(公告)号：US11725527B2

公开(公告)日：2023-08-15

申请号：US17972833

申请日：2022-10-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Alyson T. Burdette ,  Bryan P. Dube

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F05D2220/32 ,  F05D2240/10

Abstract: A method of fabricating an airfoil fairing for a vane arc segment includes providing a mandrel that necks down through a mandrel neck portion, providing fiber plies around the mandrel to form a tube that defines at least a portion of an airfoil profile of an airfoil section of an airfoil fairing, the fiber plies following the mandrel neck portion such that the tube has a corresponding tube neck portion that necks down to a collar, and removing the mandrel from the tube.

公开(公告)号：US20230250726A1

公开(公告)日：2023-08-10

申请号：US18298047

申请日：2023-04-10

Applicant: Raytheon Technologies Corporation

Inventor： Michael G. McCaffrey ,  Bryan P. Dube

IPC: F01D5/28 ,  C04B35/628 ,  C04B35/80 ,  C23C16/04 ,  F01D5/18

CPC classification number: F01D5/282 ,  C04B35/62844 ,  C04B35/62884 ,  C04B35/80 ,  C23C16/045 ,  F01D5/18 ,  C04B2235/5252 ,  C04B2235/614 ,  F05D2220/32 ,  F05D2230/314 ,  F05D2300/6033

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 ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

公开(公告)号：US11536147B2

公开(公告)日：2022-12-27

申请号：US17216973

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D11/00

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

公开(公告)号：US11530614B2

公开(公告)日：2022-12-20

申请号：US17480511

申请日：2021-09-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Alyson T. Burdette ,  Bryan P. Dube

IPC: F01D9/04

Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and a hollow airfoil section that extends there from. The hollow airfoil section defines an airfoil profile and surrounds an internal cavity. The fairing platform defines a gaspath side and a non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite comprised of fiber plies. The fiber plies include at least one cavity fiber ply that is arranged as a tube that circumscribes the internal cavity. The at least one cavity fiber ply extends through the fairing platform and defines at least a portion of an upstanding collar on the non-gaspath side of the fairing platform. The upstanding collar defines a collar profile. The tube necks down through a neck portion such that at least a portion of the collar profile is narrower than the airfoil profile.

公开(公告)号：US20220356814A1

公开(公告)日：2022-11-10

申请号：US17313099

申请日：2021-05-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Robert A. White, III ,  Bryan P. Dube

IPC: F01D25/24 ,  F02C3/04 ,  F01D5/18

Abstract: A vane system includes a plurality of vane assemblies and a continuous support ring. The vane assemblies are arranged circumferentially about an axis and each include a hollow airfoil fairing and a spar. The spar has a spar flange and a spar leg extending radially inwardly from the spar flange and through the hollow airfoil fairing. The continuous support ring has radially inner and outer sides and defines a circumferential row of through-holes between the radially inner and outer sides. The spar legs extend through the through-holes and the spar flanges are affixed at the radially outer side of the continuous support ring.

公开(公告)号：US20220316350A1

公开(公告)日：2022-10-06

申请号：US17216973

申请日：2021-03-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D11/00

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.

公开(公告)号：US11346228B1

公开(公告)日：2022-05-31

申请号：US17182389

申请日：2021-02-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Alyson T. Burdette ,  Bryan P. Dube ,  Howard J. Liles ,  James T. Roach

IPC: F01D5/14 ,  F01D9/04 ,  B29B11/16 ,  D03D25/00

Abstract: A vane arc segment includes an airfoil fairing that has a fairing platform and an airfoil section that extends there from. The fairing platform defines a gaspath side and a non-gaspath side and includes a flange that projects from the non-gaspath side. The airfoil fairing is formed of a fiber-reinforced composite that includes a wishbone-shaped fiber layer structure that has first and second arms that converge and merge into a single leg. The first and second arms are formed of fiber plies comprised of a network of fiber tows. The single leg comprises fiber tows from each of the fiber plies of the first and second arms. The fiber tows of the first arm are interwoven in the single leg with the fiber tows of the second arm. The first arm, the second arm, or the single leg forms at least a portion of the flange.

公开(公告)号：US12012866B1

公开(公告)日：2024-06-18

申请号：US18208684

申请日：2023-06-12

Applicant: Raytheon Technologies Corporation

Inventor： Dana K. Bondarevsky ,  Christopher Corcoran ,  Bryan P. Dube ,  Yuta Yoshimura ,  David D. Chapdelaine ,  Christopher Paul Perron

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F05D2260/20

Abstract: An airfoil for a gas turbine engine is configured to extend in a radial direction relative to an engine axis from an inner diameter to an outer diameter. The airfoil comprises a body having a base disposed at the inner diameter, a tip disposed at the outer diameter, a leading edge, a trailing edge, and pressure and suction side walls extending between the leading edge and the trailing edge and between the base and the tip. The body defines an interior cavity. A first wall is disposed in the interior cavity, extends radially, and adjoins the pressure side wall and the suction side wall to form a first cooling channel. A first hole through the first wall connects the first cooling channel to a second cooling channel. The first hole has a profile that tapers inward toward the base.