公开(公告)号：US11486257B2

公开(公告)日：2022-11-01

申请号：US16856558

申请日：2020-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Allan N. Arisi ,  Dominic J. Mongillo ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18

Abstract: A gas turbine engine article includes an article wall that has an inner portion at least partially defining a cavity and an outer portion. A plurality of first cooling passage networks each define first dimensions and are embedded in the article wall between the inner portion and the outer portion of the article wall. A plurality of second cooling passage networks each define second dimensions and are embedded into the article wall between the inner portion and the outer portions of the article wall. The plurality of first and second cooling passage networks are arranged in one of a first column of radially positioned networks and a second column of radially positioned networks. At least one cooling hole in the first column of radially positioned networks is located upstream of and radially aligned with at least one second mid-span wall between adjacent networks in the second column of networks.

公开(公告)号：US20220341720A1

公开(公告)日：2022-10-27

申请号：US17238351

申请日：2021-04-23

Applicant: Raytheon Technologies Corporation

Inventor： Guolin Oo ,  Tracy A. Propheter-Hinckley

IPC: G01B5/06

Abstract: Disclosed herein is a gauge for slurry coating thickness determination. The gauge includes a body and at least three probes extending from the body. The at least three probes provide a go-no-go indicator including a first demarcation that defines a minimum slurry coating thickness and a second demarcation that defines a maximum slurry coating thickness. A minimum no-go region is defined between the first demarcation and a probe tip, a maximum no-go region is defined between the second demarcation and the body, and a go region is defined between the first demarcation and the second demarcation.

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：US11286790B2

公开(公告)日：2022-03-29

申请号：US17009936

申请日：2020-09-02

Applicant: Raytheon Technologies Corporation

Inventor： San Quach ,  Christopher King ,  Tracy A. Propheter-Hinckley

IPC: F01D5/18 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  F02C7/18 ,  F23R3/00 ,  F04D29/32

Abstract: A gas turbine engine component includes a wall that has an inner surface and an outer surface. An inlet is defined by the inner surface. At least one non-rectangular slot is defined by the outer surface and includes at least one protrusion extending into the slot. A slot passage fluidly connects the inlet to the at least one non-rectangular slot. The slot passage comprises an inlet portion that extends through the wall from the inlet to an intermediate portion. An outlet portion extends through the wall from the intermediate portion to the at least one non-rectangular slot.

公开(公告)号：US11203981B1

公开(公告)日：2021-12-21

申请号：US16986493

申请日：2020-08-06

Applicant: Raytheon Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Allan N. Arisi

IPC: F02C7/28 ,  F02C3/04 ,  F01D5/18

Abstract: Airfoils for gas turbine engines are described. The airfoils include an airfoil body having a pressure and suction side walls and an internal rib and defining a cavity between, at least, the pressure side wall, the suction side wall, and the internal rib. A baffle insert is arranged within the cavity and includes a sealing portion arranged adjacent to the internal rib of the airfoil body with a gap therebetween. A seal element is arranged within the cavity and located in the gap. The seal element is free to move relative to each of the baffle insert and the airfoil body within the gap. When a pressure differential exists across the seal element, the seal element will sealingly engage between sealing portion of the baffle insert and the internal rib of the airfoil body to block a flow through the gap.

公开(公告)号：US10968752B2

公开(公告)日：2021-04-06

申请号：US16373008

申请日：2019-04-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： James Tilsley Auxier ,  Tracy A. Propheter-Hinckley ,  Allan N. Arisi

IPC: F01D5/18

Abstract: A turbine airfoil includes an airfoil outer wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. At least one cooling passage is embedded in the airfoil outer wall and has a radially-elongated entrance manifold, a radially-elongated diffuser orifice that opens to an exterior surface of the airfoil outer wall, and a bank of sub-passages fluidly connecting the radially-elongated entrance manifold with the radially-elongated diffuser orifice. The radially-elongated diffuser orifice is sloped relative to the radially-elongated entrance manifold.

公开(公告)号：US11982203B2

公开(公告)日：2024-05-14

申请号：US18339839

申请日：2023-06-22

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Ron I. Prihar ,  Tracy A. Propheter-Hinckley

IPC: F01D11/12 ,  F01D5/14

CPC classification number: F01D5/14 ,  F01D11/122 ,  F05D2230/72

Abstract: A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.

公开(公告)号：US11951532B2

公开(公告)日：2024-04-09

申请号：US16701614

申请日：2019-12-03

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Tracy A. Propheter-Hinckley ,  Dominic J. Mongillo, Jr. ,  Benjamin T. Fisk

IPC: B22C9/10 ,  B22C9/00 ,  B22C9/04 ,  B22C9/22 ,  B22C9/24 ,  B22F5/00 ,  B22F10/28 ,  B22F10/38 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/64 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04 ,  F01D11/08 ,  F01D25/12 ,  B22F3/24

CPC classification number: B22C9/04 ,  B22C9/00 ,  B22C9/10 ,  B22C9/103 ,  B22C9/106 ,  B22C9/22 ,  B22C9/24 ,  B22F5/009 ,  B22F10/28 ,  B22F10/38 ,  F01D5/147 ,  F01D5/187 ,  F01D5/284 ,  F01D9/041 ,  F01D11/08 ,  F01D25/12 ,  B22F3/24 ,  B22F2003/244 ,  B33Y10/00 ,  B33Y80/00 ,  C04B35/64 ,  F05D2220/32 ,  F05D2230/211 ,  F05D2230/22 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2260/202 ,  F05D2300/211 ,  F05D2300/2112

Abstract: A method of preparing a casting article for use in manufacturing a gas turbine engine part according to an exemplary aspect of the present disclosure includes, among other things, communicating a powdered material to an additive manufacturing system and preparing a casting article that includes at least one trunk and a skin core that extends from the at least one trunk out of the powdered material. A casting article is also disclosed.

公开(公告)号：US11806953B2

公开(公告)日：2023-11-07

申请号：US17894221

申请日：2022-08-24

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jonas S. Banhos ,  Tracy A. Propheter-Hinckley ,  Michael Parkin

IPC: B29C70/54 ,  B29C70/56 ,  B32B37/10 ,  B32B37/18 ,  B32B38/18 ,  F01D5/28 ,  F01D25/16

CPC classification number: B29C70/541 ,  B29C70/543 ,  B29C70/56 ,  B32B37/10 ,  B32B37/18 ,  B32B38/1808 ,  F01D5/282 ,  F01D5/284 ,  F01D25/162 ,  B32B2305/72 ,  B32B2309/12 ,  F05B2230/90 ,  F05C2253/04 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2260/30 ,  F05D2300/6033

Abstract: An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

公开(公告)号：US11702987B2

公开(公告)日：2023-07-18

申请号：US17480325

申请日：2021-09-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Scott A. Kovach ,  Tracy A. Propheter-Hinckley

IPC: F02C7/18 ,  F01D5/18 ,  F01D9/04 ,  B23Q3/06

CPC classification number: F02C7/18 ,  F01D5/188 ,  F01D5/189 ,  F01D9/041 ,  B23Q3/063 ,  F05D2230/10

Abstract: A gas turbine engine article includes a baffle that is configured to be mounted in a cavity of a gas turbine engine component. The baffle has a baffle wall that circumscribes an open interior region. The baffle wall includes a forward wall, side walls, and an aft wall. The side walls include impingement orifices, and the aft wall defines two datum features. At least one of the datum features is a dimple that is a portion of a sphere.