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公开(公告)号：US20190242580A1
公开(公告)日：2019-08-08
申请号：US15889793
申请日：2018-02-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Steven D. Porter , Jon E. Sobanski
CPC classification number: F23R3/002 , F01D5/187 , F01D9/065 , F23M5/04 , F23R3/50 , F23R3/60 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018 , F23R2900/03043 , F23R2900/03044
Abstract: A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface, a rail member disposed on the cold side proximate a first portion of the outer perimeter, the rail member having an outer wall and an inner wall, an undercut portion within the second surface proximate the inner wall of the rail member and an orifice extending through the rail member, from the inner wall to the outer wall.
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公开(公告)号：US11506063B2
公开(公告)日：2022-11-22
申请号：US16676949
申请日：2019-11-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Bryan H. Farrar , Jon E. Sobanski
Abstract: An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.
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公开(公告)号：US11365642B2
公开(公告)日：2022-06-21
申请号：US16844625
申请日：2020-04-09
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Howard J. Liles
Abstract: A gas turbine engine support system includes a vane arc segment, a vane support arc segment piece configured to engage the vane arc segment, and a seal disposed radially between the vane arc segment and the vane support arc segment piece. The seal includes first and second seal sections. The first seal section has a floor wall and first and second side walls that project from the floor wall. The first and second side walls converge to define a disjointed corner. The second seal section nests with the first seal section and seals the disjointed corner.
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公开(公告)号：US20200300469A1
公开(公告)日：2020-09-24
申请号：US16358195
申请日：2019-03-19
Applicant: United Technologies Corporation
Inventor： Steven D. Porter , Jon E. Sobanski
Abstract: An aerodynamic component of a gas turbine engine is provided and is fittable to a shell having a shell shape. The aerodynamic component includes a body having a component shape initially deviating from the shell shape prior to an assembly operation in which the aerodynamic component is to be fit to the shell. Deviation of the component shape from the shell shape aids in an establishment of a final desired shape of the aerodynamic component following the assembly operation.
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公开(公告)号：US11092022B2
公开(公告)日：2021-08-17
申请号：US16672611
申请日：2019-11-04
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Bryan P. Dube
Abstract: A gas turbine engine component includes a vane arc segment that defines an axis. The vane arc segment includes an airfoil section and first and second platforms. The airfoil section has a first radial end, a second radial end, a first side, a second side, a leading edge, and a trailing edge. The airfoil section has associated characteristics, including a center of pressure and an aerodynamic load vector through the center of pressure. The first platform defines a first side chevron face that has a leading leg and a trailing leg that meet at an angle. The leading leg is elongated along a centerline that is non-axially oriented with respect to the axis, the leading leg meets the leading face at a leading first side corner. The leading first side corner is located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.
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Patent Agency Ranking
公开(公告)号：US20210246808A1
公开(公告)日：2021-08-12
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：US20210246788A1
公开(公告)日：2021-08-12
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：US20200298302A1
公开(公告)日：2020-09-24
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：US20190257248A1
公开(公告)日：2019-08-22
申请号：US15902171
申请日：2018-02-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Steven D. Porter
IPC: F02C7/18
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, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
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公开(公告)号：US20190162134A1
公开(公告)日：2019-05-30
申请号：US15824014
申请日：2017-11-28
Applicant: United Technologies Corporation
Inventor： Jon E. Sobanski , Andrew S. Miller , Brandon T. Slaney
Abstract: A nozzle assembly comprises a frame, a bearing seated in a receptacle of the frame, the bearing defining a first hole, a cam including a first flange and a second flange, the first flange including a first surface and a second surface and defining a second hole between the first surface and the second surface, the second flange defining a third hole, where the bearing is disposed between the second surface of the first flange and the second flange, and a pin that includes a first portion and a second portion, where the first portion projects through the first hole, the second hole, and the third hole, and where the second portion abuts the first surface of the first flange.
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