公开(公告)号：US20220186620A1

公开(公告)日：2022-06-16

申请号：US17122017

申请日：2020-12-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski ,  Howard J. Liles

IPC: F01D5/18 ,  F01D25/12

Abstract: A spar for a vane arc segment of a gas turbine engine includes an elongated spar leg that has a spar wall that circumscribes a core passage. There is a plenum passage embedded in the spar wall between inner and outer portions of the spar wall. The inner portion of the spar wall is fully solid such that the plenum passage is fluidly isolated from the core passage. The outer portion of the spar wall has a plurality of cooling through-holes for emitting cooling air from the plenum passage.

公开(公告)号：US20220162988A1

公开(公告)日：2022-05-26

申请号：US17101247

申请日：2020-11-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tyler G. Vincent ,  Howard J. Liles

IPC: F02C3/04 ,  F02C7/18 ,  F02C7/24

Abstract: A gas turbine engine article includes a ceramic body that defines a flange, first and second cooling passages partitioned from each other by the flange, a through-hole in the rib that connects the first and second cooling passages, a thermal insulation bushing that lines the through-hole.

公开(公告)号：US12163446B2

公开(公告)日：2024-12-10

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 ,  F01D5/28

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：US12077288B2

公开(公告)日：2024-09-03

申请号：US17180141

申请日：2021-02-19

Applicant: Raytheon Technologies Corporation

Inventor： Howard J. Liles

IPC: B64C3/18 ,  B64C3/26

CPC classification number: B64C3/187 ,  B64C3/26

Abstract: An airfoil comprises a wall that defines a leading edge and a trailing edge and one or more cavities located within the wall along with a rib that separates the cavities. The rib or the wall comprises a first split ply that comprises a consolidated section and two or more split sections; wherein the split sections emanate from the consolidated section; and where the split sections define the wall and the cavities of the airfoil.

公开(公告)号：US12071864B2

公开(公告)日：2024-08-27

申请号：US17581170

申请日：2022-01-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Howard J. Liles ,  Bryan P. Dube

IPC: F01D9/04 ,  F01D5/28

CPC classification number: F01D9/041 ,  F01D5/284 ,  F01D9/042 ,  F05D2240/12 ,  F05D2240/80 ,  F05D2250/291 ,  F05D2260/30 ,  F05D2300/6033

Abstract: A gas turbine engine includes a turbine section disposed about an engine axis. The turbine section includes inner and outer diameter ceramic support rings that define a gaspath there between. Each of the inner and outer diameter ceramic support rings is monolithic and continuous. Ceramic vane arc segments are disposed in the gaspath and supported by the inner and outer diameter ceramic support rings. Each of the ceramic vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter ceramic support ring with the ceramic vane arc segments to retain the ceramic vane arc segments between the inner and outer diameter ceramic support rings.

公开(公告)号：US12055071B2

公开(公告)日：2024-08-06

申请号：US18319597

申请日：2023-05-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Russell Kim ,  Howard J. Liles

IPC: F01D9/00 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D9/042 ,  F01D5/282 ,  F01D5/284 ,  F05D2240/12 ,  F05D2300/6033

Abstract: A vane arc segment includes a ceramic matrix composite fairing that has first and second platforms and an airfoil section that extends in a radial direction there between. Each of the first and second platforms includes axially-facing leading and trailing sides, a core gaspath side, and a non-core gaspath side. The non-core gaspath side of the first platform has a flange that projects radially there from and extends adjacent the trailing side. The flange has a radial face that is sloped with respect to the radial direction.

公开(公告)号：US20240175368A1

公开(公告)日：2024-05-30

申请号：US18071070

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

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

IPC: F01D11/00

CPC classification number: F01D11/00 ,  F05D2230/90 ,  F05D2300/603 ,  F05D2300/611

Abstract: A method of coating a seal slot includes applying a coating to a slot in a component and machining the coating to provide an open height configured to receive a seal. After the machining a surface roughness of the coating is less than about 100 ra. A scaling assembly is also disclosed.

公开(公告)号：US20230383657A1

公开(公告)日：2023-11-30

申请号：US18319586

申请日：2023-05-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Russell Kim ,  Howard J. Liles ,  Kathryn S. Read

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/282 ,  F01D5/284 ,  F01D5/147 ,  F05D2300/6033 ,  F05D2300/6012 ,  F05D2300/6034

Abstract: An airfoil includes an airfoil section that has an airfoil wall that circumscribes an internal airfoil cavity and defines leading and trailing ends and pressure and suction sides. The airfoil wall is formed of a ceramic matrix composite (CMC) laminate comprised of fiber plies disposed in a ceramic matrix. The fiber plies include a skin fiber ply that defines an exterior of the airfoil section and at least one inner fiber ply that lines the skin fiber ply. At least one inner fiber ply locally terminates at one of the leading end or the trailing end such that the airfoil wall has fewer of the fiber plies in the leading end or the trailing end than in each of the pressure side and the suction side.

公开(公告)号：US20220282628A1

公开(公告)日：2022-09-08

申请号：US17193369

申请日：2021-03-05

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D9/04 ,  F02C3/04

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：US20220228500A1

公开(公告)日：2022-07-21

申请号：US17149914

申请日：2021-01-15

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D9/04 ,  F01D5/18

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 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.