公开(公告)号：US11933223B2

公开(公告)日：2024-03-19

申请号：US16388206

申请日：2019-04-18

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence Binek ,  Matthew B. Kennedy ,  Jesse R. Boyer

IPC: F02C7/00 ,  B22F10/28 ,  F02C7/22 ,  B22F10/66 ,  F23N1/00 ,  F23R3/36 ,  F23R3/60

CPC classification number: F02C7/22 ,  B22F10/28 ,  B22F10/66 ,  F05D2220/32 ,  F23N1/00 ,  F23R3/36 ,  F23R3/60

Abstract: An attritable engine includes an engine case, which includes an outer wall and a fuel rail integral with the outer wall. The fuel rail includes a fuel line integral with the outer wall, a fuel ring configured to receive fuel from the fuel line, and an injector throat configured to receive aerated fuel from the fuel ring. The engine case includes counter distortion webbing defining the injector throat and is integral with the fuel rail and the outer wall. The engine case includes a combustion chamber configured to receive fuel from the injector throat.

公开(公告)号：US11806939B2

公开(公告)日：2023-11-07

申请号：US17503880

申请日：2021-10-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lawrence Binek ,  Matthew B. Kennedy ,  Evan Butcher ,  Jesse R. Boyer ,  Vijay Narayan Jagdale ,  Dmytro Mykolayovych Voytovych

IPC: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/04 ,  B33Y30/00 ,  B33Y80/00 ,  B33Y10/00

CPC classification number: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/045 ,  B33Y10/00 ,  B33Y30/00 ,  B33Y80/00 ,  F05D2230/22 ,  F05D2230/233

Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

公开(公告)号：US11739690B2

公开(公告)日：2023-08-29

申请号：US17746206

申请日：2022-05-17

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesse R. Boyer ,  Evan J. Butcher ,  Michael Winter ,  Jesus A. Garcia ,  Sean R. Jackson

IPC: F02C7/055 ,  B22F10/28

CPC classification number: F02C7/055 ,  B22F10/28 ,  F05D2230/31 ,  F05D2260/607 ,  B22F2999/00 ,  B22F10/28 ,  B22F3/1115

Abstract: A turbine engine has: a compressor; a combustor; a turbine, a gas flowpath passing consecutively through the compressor, combustor, and turbine; and inlet member along the gas flowpath upstream of the compressor. The inlet member includes the unitarily-formed single piece combination of: a three dimensional (3D) lattice portion; and a nose cap body surrounding the lattice portion.

公开(公告)号：US20250067198A1

公开(公告)日：2025-02-27

申请号：US18453093

申请日：2023-08-21

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesse R. Boyer

IPC: F01D25/28 ,  F01D9/04

Abstract: A stator vane for a gas turbine engine combustor has a vane segment that includes a vane having a leading edge, a trailing edge, a suction side, a pressure side, a vane inner base, and a vane outer base, an inner shroud segment attached to the vane at the vane inner base, and an outer shroud segment attached to the vane at the vane outer base. The stator vane further includes a support structure attached to the vane at a vane trailing edge, and a first weld shield attached to the support structure by a first connector. The first weld shield is positioned over and spaced away from the suction side. The vane, inner shroud segment, outer shroud segment, support structure, and first weld shield are integrally formed during a single, continuous additive manufacturing process.

公开(公告)号：US20250001503A1

公开(公告)日：2025-01-02

申请号：US18345835

申请日：2023-06-30

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Matthew Siopis ,  Jesse R. Boyer

IPC: B22F12/30 ,  B29C64/245 ,  B33Y30/00

Abstract: A build plate for a powder bed fusion-laser (PBF-L) additive manufacturing system has a support region and a top region. The top region is formed on the support region by a cold spray process, such that the top region is under a compressive stress. The build plate can be prepared by preparing the build plate support region to receive the top region and depositing, using a cold spray process, a layer of metal on the support region. The layer of metal is formed with a compressive stress to form the top region. The top region is then machined to provide a desired surface roughness.

公开(公告)号：US12053821B2

公开(公告)日：2024-08-06

申请号：US18122207

申请日：2023-03-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lawrence Binek ,  Jesse R. Boyer ,  Dmytro Mykolayovych Voytovych

IPC: F23R3/16 ,  B22F10/25 ,  F23R3/00 ,  F23R3/26

CPC classification number: B22F10/25 ,  F23R3/002 ,  F23R3/16 ,  F23R3/26

Abstract: A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

公开(公告)号：US20230241681A1

公开(公告)日：2023-08-03

申请号：US18122207

申请日：2023-03-16

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lawrence Binek ,  Jesse R. Boyer ,  Dmytro Mykolayovych Voytovych

IPC: B22F10/25 ,  F23R3/16 ,  F23R3/26 ,  F23R3/00

CPC classification number: B22F10/25 ,  F23R3/16 ,  F23R3/26 ,  F23R3/002

Abstract: A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.

公开(公告)号：US20220032554A1

公开(公告)日：2022-02-03

申请号：US17503880

申请日：2021-10-18

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Lawrence Binek ,  Matthew B. Kennedy ,  Evan Butcher ,  Jesse R. Boyer ,  Vijay Narayan Jagdale ,  Dmytro Mykolayovych Voytovych

IPC: B29C64/40 ,  B29C64/153 ,  F01D5/02 ,  F01D21/04

Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.

公开(公告)号：US12234986B2

公开(公告)日：2025-02-25

申请号：US16930797

申请日：2020-07-16

Applicant: Raytheon Technologies Corporation

Inventor： Lawrence A. Binek ,  Jesse R. Boyer

IPC: F02C3/14 ,  F23R3/00

Abstract: A method of manufacturing a nested combustor liner includes manufacturing a nested combustor liner into a green state including a plurality of annular interior walls radially adjacent to one another and circumferentially surrounding an exhaust duct aperture and a plurality of annular exterior walls radially adjacent to one another and radially spaced apart from and circumferentially surrounding the plurality of annular interior walls and an ignitor wall attached to a first annular interior wall at a first interior end, extending radially toward and attached to a first annular exterior wall at a first exterior end. The method includes assembling the plurality of annular interior walls and the plurality of annular exterior walls, forming an assembled combustor liner. The method includes densifying the assembled combustor liner.

公开(公告)号：US11904405B2

公开(公告)日：2024-02-20

申请号：US17665788

申请日：2022-02-07

Applicant: Raytheon Technologies Corporation

Inventor： Vijay Narayan Jagdale ,  Jesse R. Boyer ,  Om P. Sharma ,  Evan J. Butcher ,  Lawrence Binek ,  Bryan G. Dods

IPC: F01D25/24 ,  B23K26/00 ,  B22F10/25 ,  B22F10/38 ,  B33Y10/00 ,  B33Y80/00 ,  B22F10/366

CPC classification number: B23K26/0006 ,  B22F10/25 ,  B22F10/38 ,  F01D25/24 ,  B22F10/366 ,  B33Y10/00 ,  B33Y80/00 ,  F05D2230/22 ,  F05D2230/30 ,  F05D2250/181 ,  F05D2250/63

Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.