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公开(公告)号：US20190153866A1
公开(公告)日：2019-05-23
申请号：US15819047
申请日：2017-11-21
Applicant: United Technologies Corporation
Inventor： Dmytro Mykolayovych Voytovych , Alexander Staroselsky , Om P. Sharma , Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.
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公开(公告)号：US11248789B2
公开(公告)日：2022-02-15
申请号：US16212879
申请日：2018-12-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lawrence Binek , Jesse R. Boyer , Dmytro Mykolayovych Voytovych
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.
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3.发明申请公开(公告)号：US20200325790A1
公开(公告)日：2020-10-15
申请号：US16384076
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Simon W. Evans , Dilip Prasad , Gorazd Medic , Georgi Kalitzin , Dmytro Mykolayovych Voytovych
Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.
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公开(公告)号：US20200088408A1
公开(公告)日：2020-03-19
申请号：US16130837
申请日：2018-09-13
Applicant: United Technologies Corporation
Inventor： Lawrence Binek , Evan Butcher , Matthew B. Kennedy , Vijay Narayan Jagdale , Jesse R. Boyer , Dmytro Mykolayovych Voytovych
Abstract: A component for a gas turbine engine is disclosed. In various embodiments, the component includes a diffuser ring, a combustor and a spring element connecting the diffuser ring to the combustor.
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5.发明授权公开(公告)号：US11179895B2
公开(公告)日：2021-11-23
申请号：US16153259
申请日：2018-10-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lawrence Binek , Matthew B. Kennedy , Evan Butcher , Jesse R. Boyer , Vijay Narayan Jagdale , Dmytro Mykolayovych Voytovych
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.
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Patent Agency Ranking
公开(公告)号：US10954810B2
公开(公告)日：2021-03-23
申请号：US16221911
申请日：2018-12-17
Applicant: United Technologies Corporation
Inventor： Lawrence Binek , Matthew B. Kennedy , Evan Butcher , Jesse R. Boyer , Vijay Narayan Jagdale , Dmytro Mykolayovych Voytovych
Abstract: A unitary rub strip comprises a casing having an inner surface and an outer surface opposite the inner surface; a unitary rub strip is formed integral with the casing proximate the inner surface, wherein the unitary rub strip comprises a modified structure within the casing configured to abrade responsive to an interaction with a rotating element.
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公开(公告)号：US11136901B2
公开(公告)日：2021-10-05
申请号：US16415327
申请日：2019-05-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lawrence A. Binek , Jesse R. Boyer , Evan J. 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.
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公开(公告)号：US11078805B2
公开(公告)日：2021-08-03
申请号：US16384076
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Simon W. Evans , Dilip Prasad , Gorazd Medic , Georgi Kalitzin , Dmytro Mykolayovych Voytovych
Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.
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公开(公告)号：US10907544B2
公开(公告)日：2021-02-02
申请号：US14665081
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Dmytro Mykolayovych Voytovych , Om P. Sharma
Abstract: A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.
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公开(公告)号：US20200182467A1
公开(公告)日：2020-06-11
申请号：US16212879
申请日：2018-12-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lawrence Binek , Jesse R. Boyer , Dmytro Mykolayovych Voytovych
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.
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