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1.发明授权公开(公告)号：US11384651B2
公开(公告)日：2022-07-12
申请号：US16371362
申请日：2019-04-01
摘要： Flow path assemblies and methods for assembling a flow path assembly of a gas turbine engine are provided. For example, a flow path assembly comprises a unitary outer wall including combustor and turbine portions that are integrally formed as a single unitary structure; a single piece, generally annular inner band; and a plurality of nozzle airfoils extending from the unitary outer wall to the inner band. Each nozzle airfoil interfaces with the inner band to position the inner band within the assembly. An exemplary assembly method comprises inserting an inner band into a flow path having a unitary outer wall as its outer boundary; inserting a plurality of nozzle airfoils into the flow path; and securing the nozzle airfoils with respect to the unitary outer wall. The inner band interfaces with an inner end of each nozzle airfoil to radially locate the inner band within the flow path.
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公开(公告)号：US20190084892A1
公开(公告)日：2019-03-21
申请号：US15710954
申请日：2017-09-21
发明人： Suresh Subramanian , Mark Eugene Noe , James Dale Steibel , Jason David Shapiro , Brandon ALlanson Reynolds , Kurtis C. Montgomery , Jared Hogg Weaver , Daniel Gene Dunn
IPC分类号： C04B37/00 , C04B35/80 , C04B35/657 , C04B35/628
摘要： A ceramic matrix composite article includes a chemical vapor infiltration ceramic matrix composite base portion including ceramic fiber reinforcement material in a ceramic matrix material having between 0% and 5% free silicon. The ceramic matrix composite article further includes a melt infiltration ceramic matrix composite covering portion including a ceramic fiber reinforcement material in a ceramic matrix material having a greater percentage of free silicon than the chemical vapor infiltration ceramic matrix composite base portion.
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公开(公告)号：US10024193B2
公开(公告)日：2018-07-17
申请号：US14945789
申请日：2015-11-19
发明人： Jason David Shapiro
IPC分类号： F01D11/08 , F01D25/28 , F01D25/00 , F04D29/02 , B29C70/34 , B29C53/02 , B29C70/54 , F04D29/54 , F01D25/24 , B29C70/12 , B29K105/12 , B29L31/00 , B29C53/04
摘要： The present disclosure is directed to a component for a gas turbine. The component includes a component wall having a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface. A first boss extends radially outwardly from the radially outer surface, includes a first circumferentially outer surface, and defines a first aperture extending axially therethrough. A second boss extends radially outwardly from the radially outer surface and is circumferentially spaced apart from the first boss. The second boss includes a second circumferentially outer surface and defines a second aperture extending axially therethrough. The first circumferentially outer surface of the first boss and the second circumferentially outer surface of the second boss form a pair of angles with respect to the radially inner surface.
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公开(公告)号：US11015613B2
公开(公告)日：2021-05-25
申请号：US15404608
申请日：2017-01-12
发明人： Daniel Patrick Kerns , Dennis Paul Dry , Megan Elizabeth Scheitlin , Alexander Martin Sener , Jason David Shapiro
摘要： A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.
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5.发明申请公开(公告)号：US20190226349A1
公开(公告)日：2019-07-25
申请号：US16371362
申请日：2019-04-01
摘要： Flow path assemblies and methods for assembling a flow path assembly of a gas turbine engine are provided. For example, a flow path assembly comprises a unitary outer wall including combustor and turbine portions that are integrally formed as a single unitary structure; a single piece, generally annular inner band; and a plurality of nozzle airfoils extending from the unitary outer wall to the inner band. Each nozzle airfoil interfaces with the inner band to position the inner band within the assembly. An exemplary assembly method comprises inserting an inner band into a flow path having a unitary outer wall as its outer boundary; inserting a plurality of nozzle airfoils into the flow path; and securing the nozzle airfoils with respect to the unitary outer wall. The inner band interfaces with an inner end of each nozzle airfoil to radially locate the inner band within the flow path.
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公开(公告)号：US10309244B2
公开(公告)日：2019-06-04
申请号：US15102370
申请日：2014-12-04
摘要： A shroud and shroud hanger are provided wherein at least the shroud is formed of ceramic matrix composite material. The shroud and hanger extend in a circumferential direction. A generally C-shaped clip extends radially to retain the hanger and shroud together.
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公开(公告)号：US20190101016A1
公开(公告)日：2019-04-04
申请号：US15724628
申请日：2017-10-04
发明人： Jason David Shapiro
摘要： A rotor assembly apparatus that includes a rotatable component and a ring-shroud. The rotatable component is mounted for rotation about a first axis. The ring-shroud defines an inner surface that surrounds the rotatable component and that defines a second axis. A sensing system is configured to monitor the position of the first axis relative to the second axis. A casing surrounds the ring-shroud and an actuation system is configured to move the ring-shroud relative to the casing, in response to the sensing system.
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公开(公告)号：US09874104B2
公开(公告)日：2018-01-23
申请号：US14634060
申请日：2015-02-27
发明人： Jason David Shapiro
CPC分类号： F01D11/08 , F01D25/246 , F05D2220/32 , F05D2240/14 , F05D2260/15 , F05D2260/941 , F05D2300/6033 , Y02T50/672
摘要： A shroud and hanger assembly for a gas turbine engine and a method of transferring load from a ceramic matrix composite (CMC) shroud to a CMC shroud hanger assembly are provided. The shroud and hanger assembly includes a shroud hanger assembly formed of a first material having a first coefficient of thermal expansion, the shroud hanger assembly having a forward hanger portion and a separate aftward hanger portion and a shroud formed of a second material having a second coefficient of thermal expansion, the forward and aftward hanger portions configured to couple together to clamp across a forward radially extending wall of the shroud.
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公开(公告)号：US20140202168A1
公开(公告)日：2014-07-24
申请号：US14220434
申请日：2014-03-20
CPC分类号： F01D11/08 , F01D9/04 , F01D11/18 , F01D25/246 , F05D2300/603
摘要： A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.
摘要翻译： 由支撑组件支撑的复合环形护罩，所述支撑组件包括至少一个环并至少部分地设置在所述环内。 护罩偏压抵靠环的内凸缘并与其密封接合。 三环组件包括设置在外环的径向向内设置的中环的径向向内的内环，并且护罩至少部分地设置在内环内。 至少三个定时销从中间环径向向内延伸穿过内圈中的槽，使其处于护罩中的凹口。 中间环可以是固定地连接到发动机主干的支撑环的后端。 安装销可以压配合到中间环的销孔中，并从中间环径向向外延伸穿过外环的径向孔。
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公开(公告)号：US20220213798A1
公开(公告)日：2022-07-07
申请号：US17706761
申请日：2022-03-29
摘要： Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.
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