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公开(公告)号：US20210317786A1
公开(公告)日：2021-10-14
申请号：US16844596
申请日：2020-04-09
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Howard J. Liles
IPC: F02C7/20
Abstract: A gas turbine engine support system includes a support arc segment piece that defines radially inner and outer sides, axially forward and aft sides, and first and second circumferential mate face sides. The radially inner side has a radially open socket that is configured to engage a mating component and transmit loads from the mating component. The radially open socket is elongated in an axial direction with respect to the axially forward and aft sides The support arc segment piece has radial and axial reaction surfaces that are configured, respectively, to transmit radial and axial components of the loads from the mating component.
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公开(公告)号：US20210102469A1
公开(公告)日：2021-04-08
申请号：US16592884
申请日：2019-10-04
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Howard J. Liles , Bryan H. Farrar , Cheng Gao
IPC: F01D5/28
Abstract: A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.
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公开(公告)号：US10953461B2
公开(公告)日：2021-03-23
申请号：US16360145
申请日：2019-03-21
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Jon E. Sobanski
Abstract: An investment casting method includes providing a stock investment casting core, bending the stock investment casting core to thereby form a production investment casting core that conforms to a design cooling passage shape, and casting an alloy around the production investment casting core to form a cast article.
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公开(公告)号：US20200041132A1
公开(公告)日：2020-02-06
申请号：US16053296
申请日：2018-08-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Steven D. Porter
Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, and a rail disposed about a periphery of the cold side, the rail including a first rail member having a first length extending along the panel, a first height extending from the cold side, and a first thickness that varies along the first length.
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公开(公告)号：US11466577B2
公开(公告)日：2022-10-11
申请号：US16592884
申请日：2019-10-04
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Howard J. Liles , Bryan H. Farrar , Cheng Gao
Abstract: A vane arc segment includes a continuous airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The airfoil section has a pressure side and a suction side. The first platform defines axially-sloped suction and pressure side circumferential mate faces, first and second axial sides, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along at least a portion the axially-sloped suction side circumferential mate face.
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Patent Agency Ranking
公开(公告)号：US11333037B2
公开(公告)日：2022-05-17
申请号：US16783300
申请日：2020-02-06
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Howard J. Liles
Abstract: A vane arc segment includes an airfoil piece that defines a first platform and an airfoil section that extends from the first platform. The first platform defines a radial flange that extends along at least a portion of a circumferential mate face of the first platform. The airfoil piece is formed of a fiber-reinforced composite that has fibers that are continuous between the airfoil section and the first platform. The airfoil section carries a second platform radially opposite the first platform. The second platform includes a through-hole, and the airfoil section extends through the through-hole.
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公开(公告)号：US11255194B2
公开(公告)日：2022-02-22
申请号：US16787083
申请日：2020-02-11
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Bryan H. Farrar
Abstract: A vane arc segment includes an airfoil piece that has a first platform, a second platform, and an airfoil section between the first platform and the second platform. At least the first platform is formed of a fiber-reinforced composite (FRC) and defines a radial flange. A cap is fitted on the radial flange.
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公开(公告)号：US11047575B2
公开(公告)日：2021-06-29
申请号：US16383999
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Jon E. Sobanski , Steven D. Porter
Abstract: A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.
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公开(公告)号：US20200326072A1
公开(公告)日：2020-10-15
申请号：US16383999
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Jonathan Jeffery Eastwood , Jon E. Sobanski , Steven D. Porter
IPC: F23R3/06
Abstract: A combustor for use in a gas turbine engine, the combustor enclosing a combustion chamber having a combustion area. The combustor includes: a shell having a kink; and a kinked heat shield panel in facing spaced relationship with the shell, the kinked heat shield panel including a kink located proximate the kink in the shell, wherein the kinked heat shield panel further includes a first surface, a second surface opposite the first surface, and a mounting stud located proximate the kink of the kinked heat shield panel and extending away from the second surface.
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公开(公告)号：US10563626B2
公开(公告)日：2020-02-18
申请号：US16020021
申请日：2018-06-27
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Jon E. Sobanski
Abstract: A method of controlling fuel injection into a combustor of a gas turbine engine including: applying a first electrical charge to fuel such that the fuel becomes a charged fuel; and applying a second electrical charge to a component of the combustor, wherein the first electrical charge is applied to the fuel at a first frequency and the second electrical charge is applied to the component at a second frequency such that at least one of a selected tone, a selected screech, and a selected noise is produced by spraying the charged fuel through the component and into a combustion chamber of the combustor from a fuel nozzle.
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