公开(公告)号：US20240167391A1

公开(公告)日：2024-05-23

申请号：US17990244

申请日：2022-11-18

Applicant: Raytheon Technologies Corporation

Inventor： Daniel S. Rogers ,  Joseph Micucci

IPC: F01D11/08

CPC classification number: F01D11/08 ,  F05D2220/32 ,  F05D2240/55

Abstract: A blade outer air seal has seal mount hooks on both a leading edge of the central web and a trailing edge of the central web. The seal mount hooks have a generally radially outward extending section extending to a generally axially extending section. The seal mount hooks have a support face which is to be supported on a support mount hook. The support face is generally formed about a single radius of curvature over at least 50% of a circumferential length defined from a radially inner end of the support face to a radially outer end of the support face. A radius of curvature of the inner support surface is greater than or equal to 0.150 inch and less than or equal to 0.300 inch. A blade outer air seal and a gas turbine engine are also disclosed.

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：US11982187B1

公开(公告)日：2024-05-14

申请号：US18085864

申请日：2022-12-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel S. Rogers ,  Joseph Micucci ,  Peter J. Rosenfeld ,  Giovanni Lawrence ,  Aaron Tomich

IPC: F01D11/08 ,  F01D5/28

CPC classification number: F01D11/08 ,  F01D5/282 ,  F05D2220/32 ,  F05D2250/75 ,  F05D2300/6033 ,  F05D2300/6034

Abstract: A blade outer air seal arc segment includes a ceramic matrix composite body that defines a core gaspath side, a non-core gaspath side opposite the core gaspath side, a forward end, an aft end, and circumferential sides. The ceramic matrix composite body has first and second flanges on the non-core gaspath side. The ceramic matrix composite body is comprised of fiber plies disposed in a ceramic matrix. The fiber plies include flange fiber plies that have a +/−15-75 degree ply layup arrangement.

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：US11352979B2

公开(公告)日：2022-06-07

申请号：US16857661

申请日：2020-04-24

Applicant: Raytheon Technologies Corporation

Inventor： Yuk-Kwan Brian Yuen ,  Christopher T. Anglin ,  Matthew Nickerson ,  Daniel S. Rogers

IPC: F02K3/06 ,  F01D9/06 ,  F01D25/16 ,  F01D25/18

Abstract: A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.

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：US20210332775A1

公开(公告)日：2021-10-28

申请号：US16857661

申请日：2020-04-24

Applicant: Raytheon Technologies Corporation

Inventor： Yuk-Kwan Brian Yuen ,  Christopher T. Anglin ,  Matthew Nickerson ,  Daniel S. Rogers

IPC: F02K3/06 ,  F02C7/36 ,  F01D25/16 ,  F02C7/06

Abstract: A fan assembly of a gas turbine engine includes a fan rotor including a fan rotor hub, and a plurality of fan blades extending radially outwardly from the fan rotor hub, and a fan case including an inner case portion and an outer case portion surrounding the plurality of fan blades. A plurality of struts extend between the inner case portion and the outer case portion. A bearing assembly is configured to support the fan rotor at the inner case portion. The bearing assembly includes a bearing inner race secured to the fan rotor, a bearing outer race secured to the inner case portion, and a plurality of bearing elements located radially between the bearing inner race and the bearing outer race.

公开(公告)号：US12012870B1

公开(公告)日：2024-06-18

申请号：US18071060

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Daniel S. Rogers ,  Robert A. White, III

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

CPC classification number: F01D5/288 ,  F01D5/147 ,  F01D5/3007 ,  F05D2220/323 ,  F05D2230/31 ,  F05D2240/30

Abstract: A gas turbine engine turbine blade includes a turbine blade body including an inner platform. An airfoil extends radially outwardly of the inner platform. The airfoil has a leading edge and a trailing edge, and a suction wall and a pressure wall. The turbine blade body has mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side each having a radially outer face. The turbine blade body is formed of one of a polymer, metal or ceramic matrix composite. There is a protective coating on the radially outer faces of the at least one enlarged mount portions. A gas turbine engine is also disclosed.

公开(公告)号：US20240191628A1

公开(公告)日：2024-06-13

申请号：US18080430

申请日：2022-12-13

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel S. Rogers ,  Robert A. White, III

IPC: F01D5/28 ,  F01D11/12 ,  F01D25/00

CPC classification number: F01D5/288 ,  F01D11/122 ,  F01D25/005 ,  F05D2230/90 ,  F05D2240/55 ,  F05D2300/20 ,  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：US20240175365A1

公开(公告)日：2024-05-30

申请号：US18071060

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Daniel S. Rogers ,  Robert A. White, III

IPC: F01D5/28 ,  F01D5/14 ,  F01D5/30

CPC classification number: F01D5/288 ,  F01D5/147 ,  F01D5/3007 ,  F05D2220/323 ,  F05D2230/31 ,  F05D2240/30

Abstract: A gas turbine engine turbine blade includes a turbine blade body including an inner platform. An airfoil extends radially outwardly of the inner platform. The airfoil has a leading edge and a trailing edge, and a suction wall and a pressure wall. The turbine blade body has mount structure including at least one circumferentially outwardly extending mount portion on a suction wall side and a pressure wall side each having a radially outer face. The turbine blade body is formed of one of a polymer, metal or ceramic matrix composite. There is a protective coating on the radially outer faces of the at least one enlarged mount portions. A gas turbine engine is also disclosed.