公开(公告)号：US20210332709A1

公开(公告)日：2021-10-28

申请号：US16859180

申请日：2020-04-27

Applicant: Raytheon Technologies Corporation

Inventor： Howard J. Liles ,  James T. Beals

IPC: F01D5/28 ,  B28B7/00 ,  B28B11/10

Abstract: A method of fabricating a barrier layer on a substrate includes mixing gettering particles, diffusive particles, and matrix material in a carrier fluid to form a slurry; applying a layer of the slurry to the substrate; adjusting the surface of the layer of the slurry; and sintering the layer of the slurry to form a barrier layer. An article is also disclosed.

公开(公告)号：US12215606B2

公开(公告)日：2025-02-04

申请号：US18302976

申请日：2023-04-19

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Howard J. Liles

IPC: F01D9/04 ,  F01D5/08 ,  F01D9/06

Abstract: A gas turbine engine includes a circumferential row of vanes arranged about a central engine axis. The vanes include respective internal cavities and vane outlet ports for conveying cooling air. A tangential onboard injector (TOBI) radially supports the vanes at an inner diameter of the circumferential row. The TOBI includes fore and aft annular walls and an outer diameter annular wall. The fore and aft annular walls and the outer diameter annular wall define an annular plenum. The outer diameter annular wall includes TOBI inlet ports that are connected, respectively, with the vane outlet ports to receive the cooling air from each of the vanes into the plenum. The TOBI includes axially-oriented nozzles for discharging the cooling air from the plenum in an aft direction.

公开(公告)号：US12044143B2

公开(公告)日：2024-07-23

申请号：US17553928

申请日：2021-12-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Howard J. Liles ,  Tyler G. Vincent ,  Bryan H. Farrar

IPC: F01D5/18 ,  F01D5/28

CPC classification number: F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/304 ,  F05D2260/202 ,  F05D2260/2214 ,  F05D2300/6033

Abstract: A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.

公开(公告)号：US20240175372A1

公开(公告)日：2024-05-30

申请号：US18070978

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Raymond Surace ,  Howard J. Liles ,  Bryan P. Dube

IPC: F01D25/00 ,  F01D9/04

CPC classification number: F01D25/005 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.

公开(公告)号：US11988104B1

公开(公告)日：2024-05-21

申请号：US18070978

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Raymond Surace ,  Howard J. Liles ,  Bryan P. Dube

IPC: F01D25/00 ,  F01D9/04

CPC classification number: F01D25/005 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.

公开(公告)号：US20240018875A1

公开(公告)日：2024-01-18

申请号：US18187839

申请日：2023-03-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Bryan P. Dube ,  Wojciech Lipka

IPC: F01D9/04 ,  F01D5/18

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/041 ,  F01D5/284

Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.

公开(公告)号：US20230381887A1

公开(公告)日：2023-11-30

申请号：US18302964

申请日：2023-04-19

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Howard J. Liles

IPC: B23K26/00 ,  B23K26/352

CPC classification number: B23K26/0093 ,  B23K26/352

Abstract: A method includes machining a closed-pore surface of a silicon-containing gas turbine engine article to produce a feature. The machining causes removal of the closed-pore surface to produce an open-pore machined surface. The open-pore machined surface is then laser-treated to cause formation of an oxide in the silicon-containing gas turbine engine article that seals the open-pore machined surface to produce a closed-pore treated surface.

公开(公告)号：US20230193764A1

公开(公告)日：2023-06-22

申请号：US17553928

申请日：2021-12-17

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Howard J. Liles ,  Tyler G. Vincent ,  Bryan H. Farrar

IPC: F01D5/18 ,  F01D5/28

CPC classification number: F01D5/187 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/304 ,  F05D2260/202 ,  F05D2300/6033 ,  F05D2260/2214

Abstract: A gas turbine engine component includes a supply cavity and a manifold cavity that shares a common divider wall with the supply cavity. The common divider wall includes inlet metering holes that connect the supply cavity and the manifold cavity. An exterior wall has an exterior surface and an opposed interior surface that bounds portions of the supply cavity and of the manifold cavity. Outlet cooling holes extend through the exterior wall and connect the manifold cavity with the exterior surface. The number of the inlet metering holes is equal to or less than the number of the outlet cooling holes, and at least one of the inlet holes is coaxial with at least one of the outlet holes.

公开(公告)号：US11668199B2

公开(公告)日：2023-06-06

申请号：US17193369

申请日：2021-03-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles ,  Chang Gao

IPC: F01D9/00 ,  F01D9/04 ,  F02C3/04

CPC classification number: F01D9/041 ,  F02C3/04 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2300/6033

Abstract: A vane arc segment includes an airfoil fairing that has first and second platforms and an airfoil section. The platforms have first and second openings that open into the airfoil section. The platforms each define first and second circumferential mate faces, forward and aft sides, a gaspath side, a non-gaspath side. The first platform has a first flange that projects radially from the non-gaspath side aft of the first opening and a second flange that projects radially from the non-gaspath side forward of the first opening. The first and second flanges are exclusive flanges on the first platform. The second platform has a third flange that projects radially from the non-gaspath side aft of the second opening.

公开(公告)号：US20220356810A1

公开(公告)日：2022-11-10

申请号：US17307139

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Raymond Surace ,  Howard J. Liles

IPC: F01D11/08 ,  F01D25/12 ,  F01D11/00 ,  F02C7/28

Abstract: A seal assembly includes first, second, and third gas turbine engine components, such as vane assemblies, that are successively arranged around an axis. Each component has first and second mate faces such that the first mate face of the first component and the second mate face of the second component define a first mate face gap, and the first mate face of the second component and the second mate face of the third component to define a second mate face gap. A seal arc segment has first and second seal portions and a connector portion that joins the seal portions. The first seal portion bridges the first mate face gap to seal the first mate face gap, the second seal portion bridges the second mate face gap to seal the second mate face gap, and the connector portion spans circumferentially across the second component.