公开(公告)号：US11492914B1

公开(公告)日：2022-11-08

申请号：US17080969

申请日：2020-10-27

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Adam P. Generale ,  Raymond Surace ,  Lucas Dvorozniak

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/12 ,  F01D25/12

Abstract: A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.

公开(公告)号：US11313242B2

公开(公告)日：2022-04-26

申请号：US16574840

申请日：2019-09-18

Applicant: Raytheon Technologies Corporation

Inventor： Alan D. Cetel ,  Dilip N. Shah ,  Eric A. Hudson ,  Raymond Surace

IPC: F01D11/00 ,  C22C19/00 ,  F01D25/00

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

公开(公告)号：US20210277785A1

公开(公告)日：2021-09-09

申请号：US17322211

申请日：2021-05-17

Applicant: Raytheon Technologies Corporation

Inventor： Christopher J. Peters ,  Emma J. Place ,  Jeffrey J. DeGray ,  Dominic J. Mongillo ,  Timothy J. Jennings ,  Raymond Surace ,  Jeremy B. Fredette

IPC: F01D5/18 ,  B22D25/02

Abstract: An airfoil core includes a first core portion that has a hybrid skin core, a tip flag core, and a trailing edge core. A second core portion has a serpentine core and a leading edge core.

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：US20240173890A1

公开(公告)日：2024-05-30

申请号：US18070962

申请日：2022-11-29

Applicant: Raytheon Technologies Corporation

Inventor： Raymond Surace ,  Jun Nable ,  Kathryn S. Read ,  Ying She

IPC: B28B11/00

CPC classification number: B28B11/003

Abstract: A fixture for processing a ceramic matrix composite article includes first and second tool segments that each have an exterior side and an interior side. The tool segments define there between a working region for holding a fiber preform that is to be densified with a ceramic material. Each of the interior sides has grooves there along for delivering a precursor gas to the working region.

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：US11898450B2

公开(公告)日：2024-02-13

申请号：US17323436

申请日：2021-05-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Raymond Surace ,  San Quach ,  Bryan P. Dube

IPC: F01D11/12 ,  F01D5/28 ,  F01D5/14 ,  F01D25/12

CPC classification number: F01D11/12 ,  F01D5/282 ,  F01D5/147 ,  F01D25/12 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/125 ,  F05D2300/20 ,  F05D2300/6033

Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.

公开(公告)号：US20230021707A1

公开(公告)日：2023-01-26

申请号：US17954619

申请日：2022-09-28

Applicant: Raytheon Technologies Corporation

Inventor： Dilip M. Shah ,  Alan D. Cetel ,  Venkatarama K. Seetharaman ,  Raymond Surace

IPC: F01D5/18

Abstract: A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

公开(公告)号：US11555452B1

公开(公告)日：2023-01-17

申请号：US17378005

申请日：2021-07-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Brian T. Hazel ,  Raymond Surace ,  Robert A. White, III ,  Zhongfen Ding

IPC: F02C7/28 ,  F02C3/04 ,  C23C4/134 ,  C23C4/11 ,  C23C4/18

Abstract: A seal system includes a ceramic component, a metallic component, a coating system. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The coating system includes a silicon-containing layer on the surface region of the ceramic component and barrier layer on the silicon-containing layer. The silicon containing layer has a surface in contact with the barrier layer and the barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer serves to limit interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer includes at least one of mullite, zircon, or hafnon.

公开(公告)号：US20220372888A1

公开(公告)日：2022-11-24

申请号：US17323436

申请日：2021-05-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Raymond Surace ,  San Quach ,  Bryan P. Dube

IPC: F01D11/12 ,  F01D5/28

Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.