公开(公告)号：US20240173743A1

公开(公告)日：2024-05-30

申请号：US18071055

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Brian T. Hazel ,  Robert A. White, III ,  Daniel S. Rogers ,  John E. Holowczak

IPC: B05D3/12

CPC classification number: B05D3/12 ,  F01D11/00 ,  F05D2230/10 ,  F05D2230/90 ,  F05D2300/6033

Abstract: A method of coating a seal slot according to an exemplary embodiment of this disclosure, among other possible things includes applying a coating to a slot in a component and machining the coating to provide an open width configured to receive a seal. after the applying, the slot has an initial open width that is smaller than the open width after the machining. A method of forming a sealing assembly is also disclosed.

公开(公告)号：US20230407755A1

公开(公告)日：2023-12-21

申请号：US17843434

申请日：2022-06-17

Applicant: Raytheon Technologies Corporation

Inventor： Raymond Surace ,  Robert A. White, III

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F05D2240/12 ,  F05D2230/60 ,  F05D2300/6033 ,  F05D2300/175

Abstract: An assembly for a gas turbine engine includes a plurality of vanes having a radially outer platform with a flange that extends radially outward therefrom and a plurality of notches in the flange. A ring is located radially outward from the radially outer platform of the plurality of vanes. An axially extending projection extends through and corresponds with each of the plurality of notches on the flange.

公开(公告)号：US20230366352A1

公开(公告)日：2023-11-16

申请号：US17743735

申请日：2022-05-13

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III

IPC: F02C7/24 ,  F01D25/14

CPC classification number: F02C7/24 ,  F01D25/145 ,  F05D2220/32 ,  F05D2260/231 ,  F05D2230/60

Abstract: A heat shield includes a first wall defined between a first end and a second end; a second wall defined between the first end and the second end, the second wall connected to the first wall at the first and second ends; a space defined between the first wall and the second wall; and thermal insulation disposed in the space. A gas turbine engine and a method of installing a heat shield in a gas turbine engine are also disclosed.

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：US11448075B2

公开(公告)日：2022-09-20

申请号：US17086893

申请日：2020-11-02

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III

IPC: F01D9/06 ,  F01D5/18 ,  F01D5/28

Abstract: A vane arc segment includes a hollow ceramic airfoil section that has walls that define an internal cavity, a trailing edge, a leading edge, a pressure side, and a suction side. A structural spar piece supports the hollow ceramic airfoil section. The spar piece includes a first spar platform, a hollow leg that has a proximal end at the spar platform and an opposed distal end. The hollow leg extends into the internal cavity of the hollow ceramic airfoil section and has an outer surface with raised bearing pads. Multiple ones of the bearing pads contact the walls of the hollow ceramic airfoil section to support the hollow ceramic airfoil section. A second spar platform is secured with the distal end of the leg.

公开(公告)号：US20240190780A1

公开(公告)日：2024-06-13

申请号：US18080508

申请日：2022-12-13

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Ahmed Abdillahi Abdi ,  David A. Litton ,  Daniel S. Rogers

IPC: C04B41/50 ,  C04B41/00 ,  C04B41/85

CPC classification number: C04B41/5024 ,  C04B41/0036 ,  C04B41/009 ,  C04B41/85

Abstract: A method of correcting a manufactured article includes applying a machinable coating to a manufactured ceramic matrix composite article with a manufacturing artifact and machining the machinable coating to provide a desired geometry. A method of correcting a manufactured article and a corrected article are also disclosed.

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：US11976571B1

公开(公告)日：2024-05-07

申请号：US18080495

申请日：2022-12-13

Applicant: Raytheon Technologies Corporation

Inventor： Robert A. White, III ,  Ahmed Abdillahi Abdi ,  David A. Litton ,  Daniel S. Rogers

IPC: F01D5/28

CPC classification number: F01D5/288 ,  F05D2300/502 ,  F05D2300/6033 ,  F05D2300/611

Abstract: A section of a gas turbine engine includes a ceramic component and a metallic component situated adjacent the ceramic component. The ceramic component and the metallic component are situated outside of a core flow path of the gas turbine engine. The section of a gas turbine engine also includes an interface between the ceramic component and a metallic component and a mullite-based coating disposed at the interface. The coating provides thermal protection to the ceramic component and the metallic component, and provides thermochemical protection against interaction between the ceramic component and the metallic component. A gas turbine engine and a method of protecting components in a gas turbine engine are also disclosed.

公开(公告)号：US11939888B2

公开(公告)日：2024-03-26

申请号：US17843434

申请日：2022-06-17

Applicant: Raytheon Technologies Corporation

Inventor： Raymond Surace ,  Robert A. White, III

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2300/175 ,  F05D2300/6033

Abstract: An assembly for a gas turbine engine includes a plurality of vanes having a radially outer platform with a flange that extends radially outward therefrom and a plurality of notches in the flange. A ring is located radially outward from the radially outer platform of the plurality of vanes. An axially extending projection extends through and corresponds with each of the plurality of notches on the flange.

公开(公告)号：US11834967B1

公开(公告)日：2023-12-05

申请号：US17743544

申请日：2022-05-13

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Robert A. White, III

IPC: F01D9/04 ,  F01D25/00

CPC classification number: F01D9/042 ,  F01D25/005 ,  F05D2220/32 ,  F05D2240/12

Abstract: A gas turbine engine includes a first component, a second component, an anti-rotation tab, and a liner. The first component has a first wall that includes a first slot, and the second component has a second wall that includes a second slot that is in register with the first slot to define a groove. The anti-rotation tab extends into the groove and limits rotation of the first component and the second component. The liner lines the groove to limit wear between the anti-rotation tab and the first component and between the anti-rotation tab and the second component.