公开(公告)号：US11339667B2

公开(公告)日：2022-05-24

申请号：US16990420

申请日：2020-08-11

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Bryan P. Dube ,  Tracy A. Propheter-Hinckley ,  Allan N. Arisi ,  Adam P. Generale ,  Lucas Dvorozniak ,  Howard J. Liles

IPC: F01D5/18 ,  F01D5/28

Abstract: A gas turbine engine component according to an example of the present disclosure includes a wall extending in a thickness direction between first and second wall surfaces. The first wall surface bounds an internal cavity. The wall includes a plurality of cooling passages. Each of the cooling passages extend in a first direction between an inlet port and an outlet port coupled to a respective diffuser, and the inlet port coupled to the internal cavity along the first wall surface. Sidewalls of adjacent diffusers are conjoined to establish a common diffuser region interconnecting the diffusers and a common outlet along the second wall surface. A method of cooling a gas turbine engine component is also disclosed.

公开(公告)号：US20240300142A1

公开(公告)日：2024-09-12

申请号：US18118443

申请日：2023-03-07

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Andrew Joseph Lazur ,  Mary Colby ,  Howard J. Liles ,  Robin H. Fernandez

IPC: B28B21/48 ,  B28B7/30 ,  C04B41/45

CPC classification number: B28B21/48 ,  B28B7/30 ,  C04B41/4531 ,  C04B2235/614

Abstract: A mandrel suitable for supporting an airfoil preform includes a first piece extending along a longitudinal axis of the mandrel, and a second piece in physical contact with the first piece at first interface region and extending along the longitudinal axis of the mandrel. The first piece is formed from a first material, and the second piece is formed from a second material.

公开(公告)号：US12044145B2

公开(公告)日：2024-07-23

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 ,  F01D5/147 ,  F01D5/284 ,  F05D2300/6012 ,  F05D2300/6033 ,  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：US20240068374A1

公开(公告)日：2024-02-29

申请号：US18319597

申请日：2023-05-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Russell Kim ,  Howard J. Liles

IPC: F01D9/04 ,  F01D25/00

CPC classification number: F01D9/04 ,  F01D25/005 ,  F05D2220/32 ,  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：US11713679B1

公开(公告)日：2023-08-01

申请号：US17585760

申请日：2022-01-27

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Christian X. Campbell ,  Howard J. Liles ,  Russell Kim

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/141 ,  F01D5/282 ,  F05D2220/32 ,  F05D2250/71 ,  F05D2300/6033

Abstract: A gas turbine engine includes a turbine section that has a plurality of turbine vanes. Each of the turbine vanes includes inner and outer platforms and an airfoil section that extends there between. The airfoil section is hollow and rib-less and has a first end at the outer platform and a second end at the inner platform. The airfoil section is tangentially bowed from the first end to the second end with a radius of curvature that is from 17 centimeters to 130 centimeters.

公开(公告)号：US20230235675A1

公开(公告)日：2023-07-27

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 ,  F01D9/042 ,  F01D5/284 ,  F05D2240/12 ,  F05D2240/80 ,  F05D2250/291 ,  F05D2300/6033 ,  F05D2260/30

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：US11674404B2

公开(公告)日：2023-06-13

申请号：US17307139

申请日：2021-05-04

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Raymond Surace ,  Howard J. Liles

IPC: F01D11/08 ,  F01D9/04 ,  F01D11/00 ,  F01D25/12 ,  F02C7/28

CPC classification number: F01D11/08 ,  F01D9/04 ,  F01D11/001 ,  F01D11/005 ,  F01D25/12 ,  F02C7/28 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/56 ,  F05D2260/201 ,  F05D2300/6033

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.

公开(公告)号：US11668200B2

公开(公告)日：2023-06-06

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 ,  F01D5/28

CPC classification number: F01D9/042 ,  F01D5/18 ,  F01D9/041 ,  F01D5/284 ,  F05D2300/6033

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.

公开(公告)号：US11555451B2

公开(公告)日：2023-01-17

申请号：US17101247

申请日：2020-11-23

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tyler G. Vincent ,  Howard J. Liles

IPC: 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：US11486256B2

公开(公告)日：2022-11-01

申请号：US17113166

申请日：2020-12-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： San Quach ,  Tyler G. Vincent ,  Cheng Gao ,  Howard J. Liles

IPC: F01D5/18 ,  F01D5/14 ,  F01D5/28 ,  F01D25/24 ,  F01D9/04

Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.