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公开(公告)号：US11092029B2
公开(公告)日：2021-08-17
申请号：US16531775
申请日：2019-08-05
Applicant: General Electric Company
Inventor： Jason David Shapiro , Jonathan David Baldiga
Abstract: A shroud hanger assembly or shroud assembly is provided for a gas turbine engine wherein a hanger includes a radially depending and axially extending arm. The arm or retainer engages a pocket formed in a shroud so as to retain the shroud in a desired position relative to the hanger. An aft retaining structure is provided on the hanger and provides a seat for a seal structure which biases the retainer so that the arm of the hanger maintains engagement in the shroud pocket. A baffle may be utilized at the hanger to cool at least some portion of the shroud.
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公开(公告)号：US10774008B2
公开(公告)日：2020-09-15
申请号：US15710954
申请日：2017-09-21
Applicant: General Electric Company
Inventor： Suresh Subramanian , Mark Eugene Noe , James Dale Steibel , Jason David Shapiro , Brandon ALIanson Reynolds , Kurtis C. Montgomery , Jared Hogg Weaver , Daniel Gene Dunn
IPC: C04B37/00 , C04B35/80 , C04B35/657 , C04B35/628 , F02K9/97 , F01D11/08 , F01D25/00 , F01D5/28 , F23R3/00 , C04B35/573 , F01D9/04 , F02K1/82 , B32B18/00
Abstract: 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：US10753223B2
公开(公告)日：2020-08-25
申请号：US15724628
申请日：2017-10-04
Applicant: General Electric Company
Inventor： Jason David Shapiro
Abstract: 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：US10465558B2
公开(公告)日：2019-11-05
申请号：US15318121
申请日：2015-04-28
Applicant: General Electric Company
Inventor： Jason David Shapiro , Michael John Franks , David Scott Stapleton
Abstract: A shroud hanger assembly or shroud assembly is provided for components which may be formed of materials having differing coefficient thermal expansion. The assembly includes a multi-piece hanger including a shroud positioned in a cavity between a first hanger portion and a second hanger portion. A shroud may be formed of a low coefficient of thermal expansion material which may have a differing coefficient thermal expansion than the material defining the shroud hanger. The shroud is deflected by an axial force acting between the hanger and the shroud which also forms a seal. The seal compensates for differing rates of thermal growth between the shroud and the hanger throughout the engine operating envelope.
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公开(公告)号：US10253641B2
公开(公告)日：2019-04-09
申请号：US15440294
申请日：2017-02-23
Applicant: General Electric Company
Inventor： Jason David Shapiro , Donald Brett Desander , Edward Charles Vickers
Abstract: 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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Patent Agency Ranking
公开(公告)号：US10233844B2
公开(公告)日：2019-03-19
申请号：US14708385
申请日：2015-05-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Justin H. Bogard , Jason David Shapiro
Abstract: In one aspect the present subject matter is directed to a system for thermally shielding a portion of a shroud assembly for a gas turbine. The system includes a shroud support having a forward wall that includes a front side that is axially spaced from a back side and a radially inner surface that extends axially between the front and back sides. A shroud is mounted to the shroud support. The shroud includes a leading edge portion that extends towards the forward wall of the shroud support and a trailing edge portion that extends towards the aft wall of the shroud support. A radial gap is defined between a top surface of the leading edge portion and the radially inner surface of the forward wall. A thermal shield is disposed along a bottom portion of the forward wall and is oriented to face towards a flow of combustion gases.
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27.发明申请公开(公告)号：US20180238182A1
公开(公告)日：2018-08-23
申请号：US15440235
申请日：2017-02-23
Applicant: General Electric Company
CPC classification number: F01D9/042 , F01D9/023 , F01D11/02 , F02C3/14 , F05D2230/53 , F05D2230/60 , F05D2240/35 , F05D2300/6033 , Y02T50/672 , Y02T50/673
Abstract: 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：US20170044922A1
公开(公告)日：2017-02-16
申请号：US14825201
申请日：2015-08-13
Applicant: General Electric Company
Inventor： Jason David Shapiro
CPC classification number: F01D11/16 , F01D5/12 , F01D9/041 , F01D11/22 , F05D2220/32 , F05D2240/11 , F05D2260/50 , F05D2300/6033 , Y02T50/672
Abstract: In one aspect the present subject matter is directed to a system for supporting a turbine shroud. The system includes a shroud support at least partially defining a first piston sleeve and a piston assembly having a first piston head disposed within the first piston sleeve and a second piston head coupled to the first piston head. The first piston head is slideably engaged with an inner surface of the first piston sleeve. The second piston head is slideably engaged with an inner surface of a second piston sleeve. The system also includes a turbine shroud that is fixedly connected to the piston assembly and that extends radially inwardly from the shroud support. The piston assembly provides for radially inward and radially outward movement of the turbine shroud in response to a change in a radial force applied to a hot side surface of the turbine shroud.
Abstract translation: 在一个方面，本主题涉及一种用于支撑涡轮机护罩的系统。 该系统包括至少部分地限定第一活塞套筒和活塞组件的护罩支撑件，该活塞组件具有设置在第一活塞套筒内的第一活塞头和联接到第一活塞头的第二活塞头。 第一活塞头可滑动地与第一活塞套筒的内表面接合。 第二活塞头可滑动地与第二活塞套筒的内表面接合。 该系统还包括固定地连接到活塞组件并从护罩支撑件径向向内延伸的涡轮罩。 响应于施加到涡轮机护罩的热侧表面的径向力的变化，活塞组件提供涡轮机护罩的径向向内和径向向外的运动。
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29.发明申请公开(公告)号：US20160333788A1
公开(公告)日：2016-11-17
申请号：US14708385
申请日：2015-05-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Justin H. Bogard , Jason David Shapiro
CPC classification number: F02C7/24 , F01D5/08 , F01D11/005 , F01D11/08 , F01D25/08 , F02C3/04 , F05D2220/32 , F05D2240/11 , F05D2240/15 , F05D2260/231 , F05D2300/6033 , Y02T50/672 , Y02T50/676
Abstract: In one aspect the present subject matter is directed to a system for thermally shielding a portion of a shroud assembly for a gas turbine. The system includes a shroud support having a forward wall that includes a front side that is axially spaced from a back side and a radially inner surface that extends axially between the front and back sides. A shroud is mounted to the shroud support. The shroud includes a leading edge portion that extends towards the forward wall of the shroud support and a trailing edge portion that extends towards the aft wall of the shroud support. A radial gap is defined between a top surface of the leading edge portion and the radially inner surface of the forward wall. A thermal shield is disposed along a bottom portion of the forward wall and is oriented to face towards a flow of combustion gases.
Abstract translation: 在一个方面，本主题涉及一种用于热屏蔽用于燃气轮机的护罩组件的一部分的系统。 该系统包括具有前壁的护罩支撑件，该前壁包括与背侧轴向间隔开的前侧和在前侧和后侧之间轴向延伸的径向内表面。 护罩安装到护罩支架上。 护罩包括朝向护罩支撑件的前壁延伸的前缘部分和朝向护罩支撑件的后壁延伸的后缘部分。 径向间隙限定在前缘部分的顶表面和前壁的径向内表面之间。 热屏蔽沿着前壁的底部设置并且朝向朝向燃烧气体的流动定向。
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30.发明授权公开(公告)号：US11890836B2
公开(公告)日：2024-02-06
申请号：US17851241
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Matthew Hockemeyer , Jason David Shapiro , K. M. K. Genghis Khan , James Scott Vartuli , Daniel Gene Dunn , Shatil Sinha , Douglas Decesare , Suresh Subramanian
IPC: C04B35/80 , B32B18/00 , C04B37/00 , C04B35/571 , B28B1/52 , B28B11/08 , C04B35/565 , C04B35/626 , C04B35/628 , F01D5/00 , F01D5/28 , F01D9/02 , F23R3/00
CPC classification number: B32B18/00 , B28B1/522 , B28B11/08 , C04B35/565 , C04B35/571 , C04B35/6267 , C04B35/62884 , C04B35/80 , C04B37/001 , F01D5/005 , F01D5/282 , F01D9/02 , F23R3/007 , B32B2262/105 , C04B2235/3826 , C04B2235/5244 , C04B2235/614 , C04B2235/9607 , C04B2237/38 , C04B2237/584 , F05D2220/32 , F05D2230/31 , F05D2300/6033
Abstract: Ceramic matrix composite articles include, for example a first plurality of plies of ceramic fibers in a ceramic matrix defining a first extent, and a local at least one second ply in said ceramic matrix defining a second extent on and/or in said first plurality of plies with the second extent being less than said first extent. The first plurality of plies has a first property, the at least one second ply has at least one second property, and said first property being different from said at least one second property. The different properties may include one or more different mechanical (stress/strain) properties, one or more different thermal conductivity properties, one or more different electrical conductivity properties, one or more different other properties, and combinations thereof.
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