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公开(公告)号：US10280801B2
公开(公告)日：2019-05-07
申请号：US15623715
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Abstract: A turbine component including an outer shroud arranged within a turbine and including opposed extending portions. An inner shroud shields the outer shroud from a gas flowing along a gas path within the turbine during its operation and including opposed first and second arcuate portions extending around and in direct contact with a corresponding extending portion of the outer shroud. A first pin and second pin have a respective first end and second end. The first arcuate portion having a first engagement region for engaging the first end, and second arcuate portion having a second engagement region for engaging the second end. In response to engagement of the first engagement region and the first end of the first pin, and engagement of the second engagement region and the second end of the second pin, the inner shroud is prevented from twisting relative to the outer shroud.
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公开(公告)号：US10012091B2
公开(公告)日：2018-07-03
申请号：US14818695
申请日：2015-08-05
Applicant: General Electric Company
Inventor： Victor John Morgan , George Andrew Gergely , Frederic Woodrow Roberts, Jr. , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , B23P15/02 , F01D9/065 , F05D2240/81 , F05D2250/314 , F05D2250/75 , F05D2260/2212 , F05D2260/2214
Abstract: Embodiments of the present disclosure provide components for hot gas path (HGP) components and methods of forming the same. A structure according to the present disclosure can include: an HGP component extending radially from a rotor axis of a turbomachine, the HGP component including a tapered edge; a plurality of first passages in fluid communication with a preliminary cooling zone of the HGP component, and extending through a sidewall positioned between the preliminary cooling zone and the tapered edge; and a plurality of second passages extending through at least the tapered edge, wherein each of the plurality of second passages is in fluid communication with the flow path for the operative fluid and at least one passage of the plurality of first passages, and wherein at least one of the plurality of second passages is radially displaced from each passage of the plurality of first passages.
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公开(公告)号：US20160208633A1
公开(公告)日：2016-07-21
申请号：US14597772
申请日：2015-01-15
Applicant: General Electric Company
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D25/246 , F05D2230/60 , F05D2230/90 , F05D2240/11 , F05D2300/6033 , F05D2300/611
Abstract: A turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies includes a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the second shroud block.
Abstract translation: 涡轮机罩组件包括多个弓形护罩块组件，其环形地设置成形成护罩段。 多个护罩块组件包括具有护罩块的第一护罩块组件和具有护罩块的第二护罩块组件。 第一护罩块组件包括密封接口构件和护罩密封件。 密封接口构件具有与第一护罩块的径向侧表面相邻的侧部。 第二护罩块组件包括密封接口构件和护罩密封件。 密封接口构件具有与第二护罩块的径向侧表面相邻的侧部。
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公开(公告)号：US09784116B2
公开(公告)日：2017-10-10
申请号：US14597772
申请日：2015-01-15
Applicant: General Electric Company
CPC classification number: F01D11/08 , F01D25/246 , F05D2230/60 , F05D2230/90 , F05D2240/11 , F05D2300/6033 , F05D2300/611
Abstract: A turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies includes a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface member and a shroud seal. The seal interface member has a side portion that is adjacent to a radial side surface of the second shroud block.
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公开(公告)号：US09771819B2
公开(公告)日：2017-09-26
申请号：US14963735
申请日：2015-12-09
Applicant: General Electric Company
CPC classification number: F01D11/005 , F01D25/005 , F01D25/24 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/14 , F05D2240/55 , F05D2240/57 , F05D2300/502 , F16J15/0825 , F16J15/0887
Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arc segment adjacent to a second arc segment, each arc segment including an end surface and radially facing surfaces extending from opposite ends of the end surface; a slot located between the end surfaces of the first arc segment and the second arc segment; and a first seal disposed in the slot, the first seal contacting the first arc segment at the end surface and extending over the radially facing surfaces of the first arc segment, the first seal including: a shim contacting the first arc segment; a laminate material over the shim and covering the shim; and a conforming material coupling the laminate material to the shim.
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Patent Agency Ranking
公开(公告)号：US09709275B2
公开(公告)日：2017-07-18
申请号：US14314075
申请日：2014-06-25
Applicant: General Electric Company
CPC classification number: F23R3/02 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2260/607 , F23R3/002
Abstract: A casing for a turbo-machine at least partially defines a flow path for a working fluid through or around one or more of a compressor section, a combustor assembly, or a turbine section. The casing defines an inner surface and the inner surface defines a plurality of debris routing channels. The plurality of debris routing channels are configured to route debris in a working fluid within the casing towards a debris collection mechanism.
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公开(公告)号：US11525397B2
公开(公告)日：2022-12-13
申请号：US17008775
申请日：2020-09-01
Applicant: General Electric Company
Inventor： Brendon James Leary , Frederic Woodrow Roberts, Jr. , Ibrahim Sezer , Tyler Christopher Henson
IPC: F02C7/05
Abstract: A gas turbine component includes an ejection circuit for removing debris from cooling air flowing through a gas turbine component. The gas turbine component includes: an impingement insert and a debris ejection circuit. The impingement insert, which is disposed within a cavity in the component, includes an end wall and distribution holes for directing cooling air against a wall of the cavity. The debris ejection circuit includes: a bypass aperture defined in the end wall, which fluidly couples an interior of the impingement insert and an end section of the cavity; and an ejection channel, which fluidly couples the end section of the cavity to the wheelspace cavity or the hot gas path. A pressure differential between the interior of the impingement insert and the wheelspace cavity or hot gas path directs debris in the cooling air through the bypass aperture and the ejection channel.
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公开(公告)号：US11415001B1
公开(公告)日：2022-08-16
申请号：US17198839
申请日：2021-03-11
Applicant: General Electric Company
Abstract: A gas turbine component includes a turbine component having an outer wall and an internal cooling passage; a cooling air supply hole through the outer wall in fluid communication with the internal cooling passage; and a filter mound disposed over the cooling air supply hole. The filter mound includes a filter mound wall projecting from the turbine component and defining an interior of the filter mound. At least one hole in the filter mound wall extending through the filter mound wall is configured to permit cooling air supply to pass therethrough while blocking debris from passing through the interior of the filter mound and clogging the cooling air supply hole in fluid communication with the internal cooling passage. The turbine component and the filter mound are formed during manufacturing of the turbine component.
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公开(公告)号：US10415406B2
公开(公告)日：2019-09-17
申请号：US15585340
申请日：2017-05-03
Applicant: General Electric Company
Inventor： Neil Ristau , Russell DeForest , Frederic Woodrow Roberts, Jr.
IPC: F01D9/04
Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US09719420B2
公开(公告)日：2017-08-01
申请号：US14292969
申请日：2014-06-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Stephen DiMascio , Victor John Morgan , Jason Robert Parolini , Glenn Curtis Taxacher , Frederic Woodrow Roberts, Jr. , Jacob John Kittleson , John McConnell Delvaux
IPC: F02C7/00 , B23K1/00 , B23P6/00 , B24B33/00 , C04B41/00 , C04B41/45 , C04B41/50 , C04B41/53 , C04B41/85 , C04B41/91 , C04B41/87 , C04B41/88 , C04B41/51 , C23C16/24
CPC classification number: F02C7/00 , B23K1/0018 , B23P6/002 , B23P6/007 , B24B33/00 , C04B41/009 , C04B41/4531 , C04B41/5025 , C04B41/5096 , C04B41/5144 , C04B41/53 , C04B41/85 , C04B41/87 , C04B41/88 , C04B41/91 , C23C16/24 , F05D2230/30 , F05D2230/90 , F05D2300/6033 , Y10T156/10 , Y10T428/24355 , C04B35/00 , C04B35/80 , C04B41/4529 , C04B41/4539 , C04B41/5133 , C04B41/0072
Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.
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