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公开(公告)号：US20220325889A1
公开(公告)日：2022-10-13
申请号：US17651743
申请日：2022-02-18
发明人： Ryan Christopher Jones , Paul Christopher Schilling , Andrew Scott Bilse , Daniel Endecott Osgood , Donald Lee Gardner
摘要： Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.
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公开(公告)号：US11440097B2
公开(公告)日：2022-09-13
申请号：US16273474
申请日：2019-02-12
发明人： Ryan Christopher Jones , Jun Zheng Hu , John Alan Manteiga , Xuefeng Zhang , Earl Neal Dunham , Paul Christopher Schilling , Johnnattan Tennessee Ugarte , Justin Michael Stekli , Justin Adam Masters
IPC分类号： B29C64/153 , B29C64/40 , B22F3/24 , B22F10/80 , B22F10/47 , B22F10/66 , B22F10/62 , B22F3/11 , B33Y10/00 , B33Y40/00 , B33Y50/02 , B22F10/20 , B29C64/393 , B22F10/30
摘要： A method for additively manufacturing a component includes generating, via imaging software, a plurality of slices of a support structure of the component based on component geometry. The method also includes melting or fusing, via the additive manufacturing system, layers of material to a build platform of the component so as to form the support structure according to the plurality of slices. The support structure includes a lattice configuration having of a plurality of support members arranged together to form a plurality of cells. Further, the method includes melting or fusing, via the additive manufacturing system, a component body to the support structure. After the component body solidifies, the method includes removing all of the support structure from the component body to form the component.
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公开(公告)号：US20220268443A1
公开(公告)日：2022-08-25
申请号：US17663079
申请日：2022-05-12
发明人： Andrew Scott Bilse , Craig Alan Gonyou , Paul Christopher Schilling , Hojjat Nasr , Ryan Christopher Jones , Donald Lee Gardner
摘要： A combustor assembly for a heat engine is generally provided. The combustor assembly includes a liner wall defining a combustion chamber, and a deflector assembly. The deflector assembly includes a radially extended first wall disposed adjacent to the combustion chamber, and further an axially extended second wall disposed forward of the first wall and adjacent thereto. The second wall is coupled to the liner wall.
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公开(公告)号：US11408290B2
公开(公告)日：2022-08-09
申请号：US17314530
申请日：2021-05-07
发明人： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
摘要： A cast component having reduced cross flow linking cavities and method of casting may include a body. The body may define a plurality of internal flow channels. The plurality of internal flow channels may include a first internal flow channel and a second internal flow channel. The cast component may also include a plurality of linking cavities obstructing unintended fluid communication between the first internal flow channel and the second internal flow channel through the plurality of linking cavities.
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公开(公告)号：US20200024951A1
公开(公告)日：2020-01-23
申请号：US16037662
申请日：2018-07-17
发明人： William Charles Herman , Jacob Romeo Rendon , Duane Allan Busch , Ryan Christopher Jones , Paul Christopher Schilling , Zachary Daniel Webster , Tingfan Pang , Gregory Terrence Garay , Steven Robert Brassfield
IPC分类号： F01D5/08
摘要： An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a passage. The cooling hole can include a laid back section where a coating can be applied. The method can include forming the cooling hole in the component and applying the coating to the component to maintain a specific geometry.
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公开(公告)号：US20230358139A1
公开(公告)日：2023-11-09
申请号：US18104371
申请日：2023-02-01
CPC分类号： F01D5/147 , F01D25/12 , F23C7/02 , F01D25/14 , F05D2300/70 , F05D2300/60
摘要： A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
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公开(公告)号：US11585224B2
公开(公告)日：2023-02-21
申请号：US16987872
申请日：2020-08-07
摘要： A method of forming a gas turbine engine component, the method including forming a plurality of cooling apertures in a preform structure of the component, the plurality of cooling apertures of the preform structure comprising a first cooling aperture and a second cooling aperture, wherein cross-sectional shapes of the first and second cooling apertures of the preform structure are different from one another, as measured in a same relative plane; and applying a coating to at least a portion of the preform structure to form the component, wherein a cross-sectional shape of the first and second cooling apertures of the component are approximately the same as one another, as measured in the same relative plane.
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公开(公告)号：US11299998B2
公开(公告)日：2022-04-12
申请号：US17158670
申请日：2021-01-26
发明人： Ryan Christopher Jones , Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Tingfan Pang
摘要： A turbomachinery sealing apparatus including a first turbomachinery component having a first end face, and a seal extending away from the first end face, the seal being connected to a wall of the component by a tab extending between the wall and the seal.
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公开(公告)号：US11280492B2
公开(公告)日：2022-03-22
申请号：US16110162
申请日：2018-08-23
发明人： Ryan Christopher Jones , Donald Lee Gardner , Paul Christopher Schilling , Andrew Scott Bilse , Daniel Endecott Osgood
摘要： Embodiments of a combustor assembly for a turbine engine are generally provided. The combustor assembly includes a first separable portion defining a dome assembly, and a second separable portion defining a deflector assembly. The first separable portion and the second separable portion are coupled together at a fitted interface.
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公开(公告)号：US10981217B2
公开(公告)日：2021-04-20
申请号：US16195089
申请日：2018-11-19
发明人： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
IPC分类号： B22C9/10 , B22C9/12 , B22C9/26 , B22C7/02 , B22C21/14 , F01D5/18 , B28B7/34 , B28B1/00 , B33Y10/00 , B33Y80/00 , B33Y50/00
摘要： A leachable casting core and method of manufacture may include a plurality of legs configured to establish a plurality of internal flow channels of a cast component. Tie bars, with a first tie bar end and a second tie bar end opposite thereof, may couple to at least two of the plurality of legs. At least one of the tie bars may be oriented to form a linking cavity within the cast component between the internal flow channels. The linking cavity may serve as an obstruction to fluid communication through the linking cavity.
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