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：US20210396151A1

公开(公告)日：2021-12-23

申请号：US17465244

申请日：2021-09-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D25/00

Abstract: A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.

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：US20210388761A1

公开(公告)日：2021-12-16

申请号：US17147129

申请日：2021-01-12

Applicant: Raytheon Technologies Corporation

Inventor： Dmytro Mykolayovych Voytovych ,  Om P. Sharma

IPC: F02C7/04 ,  B64D27/00 ,  F01D5/02 ,  B64D33/02 ,  B64D27/14

Abstract: A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.

公开(公告)号：US11988140B2

公开(公告)日：2024-05-21

申请号：US17147129

申请日：2021-01-12

Applicant: Raytheon Technologies Corporation

Inventor： Dmytro Mykolayovych Voytovych ,  Om P. Sharma

IPC: F02C7/04 ,  B64C39/10 ,  B64D27/00 ,  B64D27/14 ,  B64D33/02 ,  F01D5/02

CPC classification number: F02C7/04 ,  B64D27/00 ,  B64D27/14 ,  B64D33/02 ,  F01D5/02 ,  B64C2039/105 ,  B64D2033/0253 ,  F05D2250/14 ,  F05D2250/312 ,  Y02T50/10

Abstract: A blended wing aircraft including a blended wing fuselage and at least one embedded gas turbine engine in the fuselage. The gas turbine engine includes an inlet duct formed with a generally elliptical shape that includes a first set of ellipse sections along an upper portion of the inlet duct and a second set of ellipse sections along a lower portion of the inlet duct. The inlet duct includes a vertical centerline. The first set of ellipse sections at a throat of the inlet duct is larger in area than an area of an upstream most end of the second set of ellipse sections. The area of the second set of ellipse sections increases toward a downstream end of the inlet duct. A fan section has an axis of rotation that is spaced from the vertical centerline and is disposed within an inlet duct orifice. The inlet duct is upstream of the fan section.

公开(公告)号：US20220221151A1

公开(公告)日：2022-07-14

申请号：US17591054

申请日：2022-02-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F23R3/00 ,  F23R3/16 ,  F23R3/26 ,  F23R3/04 ,  F23R3/06

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：US11612938B2

公开(公告)日：2023-03-28

申请号：US17591054

申请日：2022-02-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

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

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：US11578614B2

公开(公告)日：2023-02-14

申请号：US17465244

申请日：2021-09-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F01D25/00

Abstract: A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.