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公开(公告)号：US20170248029A1
公开(公告)日：2017-08-31
申请号：US15054346
申请日：2016-02-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy HAFNER , Gary Michael ITZEL , Sandip DUTTA
CPC classification number: F01D11/005 , F01D5/18 , F01D9/041 , F01D9/065 , F01D25/08 , F01D25/12 , F05D2230/642 , F05D2240/11 , F05D2240/128 , F05D2240/55 , F05D2260/2212 , F05D2260/231 , F05D2300/175 , F05D2300/603 , F05D2300/6033
Abstract: Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.
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公开(公告)号：US20170044923A1
公开(公告)日：2017-02-16
申请号：US14825636
申请日：2015-08-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Frederic Woodrow ROBERTS , Victor John MORGAN , Matthew Troy HAFNER
CPC classification number: F01D11/22 , F05D2240/11 , F05D2260/50 , F05D2300/6033
Abstract: A turbine shroud assembly is disclosed including an inner shroud having a surface adjacent to a hot gas path, an outer shroud, and a biasing apparatus. The biasing apparatus is arranged and disposed to bias the inner shroud in a direction away from the hot gas path, loading the inner shroud to the outer shroud. In another embodiment, the biasing apparatus is a springless biasing apparatus including at least one bellows, at least one thrust piston, or a combination of at least one bellows and at least one thrust piston. A method for loading the turbine shroud assembly is disclosed including biasing the inner shroud having a surface adjacent to a hot gas path in a direction away from the hot gas path toward the outer shroud, wherein biasing the inner shroud includes a biasing force exerted by the biasing apparatus.
Abstract translation: 公开了一种涡轮机护罩组件，其包括具有与热气体路径相邻的表面的内护罩，外护罩和偏置装置。 偏压装置被布置和设置成沿着远离热气体路径的方向偏压内护罩，将内护罩装载到外护罩。 在另一个实施例中，偏置装置是一弹簧偏压装置，其包括至少一个波纹管，至少一个推力活塞或至少一个波纹管和至少一个推力活塞的组合。 公开了一种用于装载涡轮机护罩组件的方法，包括：将具有与热气体路径相邻的表面的内护罩偏压在远离热气路径的方向朝向外护罩的偏压，其中偏压内护罩包括由 偏置装置。
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公开(公告)号：US20160214283A1
公开(公告)日：2016-07-28
申请号：US14604910
申请日：2015-01-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： David Edward SCHICK , Jason Robert PAROLINI , Matthew Troy HAFNER , Steven BARNELL
CPC classification number: B29C33/56 , B29C33/3842 , B29C33/76 , B29C70/44 , B29C70/70 , B29C70/865 , B29K2105/0872 , B29K2901/12 , B29K2905/08 , B33Y80/00 , F01D5/282 , F05D2220/30 , F05D2230/40 , F05D2230/90 , F05D2250/20 , F05D2300/43 , Y02T50/672 , Y02T50/673
Abstract: Provided are a composite tool and a method for forming composite components. The composite tool includes a three dimensionally printed polymer body, the body having a geometry corresponding to at least one surface of a gas turbine component; and a coating overlaying the body, the coating providing the printed polymer body a greater resistance to heat exposure than an uncoated printed polymer body. The method for forming a composite component includes providing a composite tool; laying-up a plurality of composite plies on a surface of the composite tool; densifying the composite plies to form a composite component; and removing the composite tool from the composite component. The composite component includes a surface geometry corresponding to at least a portion of the composite tool. Also provided is a method of forming the composite tool.
Abstract translation: 提供了复合工具和用于形成复合部件的方法。 该复合工具包括三维打印的聚合物主体，该主体具有对应于燃气轮机部件的至少一个表面的几何形状; 以及覆盖该主体的涂层，该涂层为印刷聚合物主体提供比未涂覆的印刷聚合物主体更大的耐热暴露性。 形成复合部件的方法包括提供复合工具; 在复合工具的表面上铺设多个复合层; 致密化复合层以形成复合材料; 并从复合组件中移除复合工具。 复合部件包括对应于复合工具的至少一部分的表面几何形状。 还提供了形成复合工具的方法。
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公开(公告)号：US20200182067A1
公开(公告)日：2020-06-11
申请号：US16787819
申请日：2020-02-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip DUTTA , James ZHANG , Gary Michael ITZEL , John McConnell DELVAUX , Matthew Troy HAFNER
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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公开(公告)号：US20200049017A1
公开(公告)日：2020-02-13
申请号：US16656650
申请日：2019-10-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip DUTTA , James ZHANG , Gary Michael ITZEL , John McConnell DELVAUX , Matthew Troy HAFNER
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.
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Patent Agency Ranking
公开(公告)号：US20180223689A1
公开(公告)日：2018-08-09
申请号：US15428462
申请日：2017-02-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy HAFNER , Jason Robert PAROLINI , Canan Uslu HARDWICKE
CPC classification number: F01D25/14 , F01D5/147 , F01D5/187 , F01D9/023 , F01D9/065 , F05D2240/81 , F05D2260/20 , F05D2300/6033 , F23R3/002 , F23R3/007 , F23R2900/00018
Abstract: An apparatus is disclosed, including a first article, a second article, at least one interface structure, and a thermal break directly adjacent to the at least one interface structure. The first article includes a first material composition having a first thermal tolerance. The second article includes a second material composition having a second thermal tolerance greater than the first thermal tolerance. The first article and the second article are in contact with one another through the interface structure. The thermal break interrupts a thermal conduction path from the second article to the first article.
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公开(公告)号：US20170350259A1
公开(公告)日：2017-12-07
申请号：US15174182
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip DUTTA , James ZHANG , Gary Michael ITZEL , John McConnell DELVAUX , Matthew Troy HAFNER
IPC: F01D5/18 , B23K26/342 , B23K26/70 , B22F3/105 , B22F3/24 , B23K15/00 , B23K26/00 , F01D25/12 , C23C28/04 , F01D9/02 , B33Y80/00 , B33Y10/00 , B23K103/08 , B23K101/00
CPC classification number: F01D5/187 , B22F3/1055 , B22F3/24 , B22F2998/10 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/342 , B23K26/70 , B23K2101/001 , B23K2103/08 , B33Y10/00 , B33Y80/00 , C23C28/042 , F01D5/147 , F01D5/282 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/22 , F05D2230/30 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/20 , F05D2260/204 , F05D2300/175 , F05D2300/6033
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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公开(公告)号：US20170350256A1
公开(公告)日：2017-12-07
申请号：US15174332
申请日：2016-06-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip DUTTA , James ZHANG , Gary Michael ITZEL , John McConnell DELVAUX , Matthew Troy HAFNER
CPC classification number: F01D5/186 , F01D5/147 , F01D5/187 , F01D5/282 , F01D9/041 , F01D25/005 , F01D25/12 , F05D2230/22 , F05D2230/237 , F05D2230/31 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/202 , F05D2260/204 , F05D2300/175 , F05D2300/6033
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
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公开(公告)号：US20160376893A1
公开(公告)日：2016-12-29
申请号：US14752186
申请日：2015-06-26
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Canan Uslu HARDWICKE , John McConnell DELVAUX , Jason Robert PAROLINI , Matthew Troy HAFNER
CPC classification number: F01D5/14 , B23P6/005 , B28B1/002 , B29C65/002 , B29C65/02 , B29C73/04 , B29L2031/7504 , C04B37/005 , C04B2235/5252 , C04B2235/5268 , C04B2235/60 , C04B2235/606 , C04B2237/083 , C04B2237/086 , C04B2237/78 , C04B2237/84 , F01D5/005 , F01D5/187 , F01D5/282 , F01D5/284 , F01D5/288 , F01D9/02 , F01D25/246 , F01D25/30 , F02K1/82 , F02K1/822 , F02K1/827 , F05D2230/40 , F05D2230/60 , F05D2230/64 , F05D2260/36 , F05D2300/224 , F05D2300/2261 , F05D2300/6012 , F05D2300/6033 , F05D2300/6034 , F05D2300/701 , Y02T50/675
Abstract: A method for treating a field operated component is disclosed which includes providing the component including a ceramic matrix composite and removing a first portion of the component, forming a first exposed surface on the component. The method further includes providing a second portion including the composite, the second portion having a second exposed surface including a conformation adapted to mate with the first exposed surface. The second portion is positioned in association with the component so as to replace the first portion, and the second portion and the component are joined to form a treated component. Another method is disclosed wherein the component is a turbine component which further includes removing an environmental barrier coating from the component, arranging and conforming the first exposed surface and the second exposed surface to define a joint, and applying an environmental barrier coating to the treated component.
Abstract translation: 公开了一种用于处理场致动部件的方法，其包括提供包括陶瓷基体复合材料的部件并且去除部件的第一部分，从而在部件上形成第一暴露表面。 该方法还包括提供包括复合材料的第二部分，第二部分具有包括适于与第一暴露表面配合的构型的第二暴露表面。 第二部分与部件相关联地定位以便替换第一部分，并且第二部分和部件被连接以形成处理的部件。 公开了另一种方法，其中所述部件是涡轮机部件，其进一步包括从所述部件移除环境阻挡涂层，将所述第一暴露表面和所述第二暴露表面布置和配合以限定接头，以及将环境阻挡涂层施加到所述被处理部件 。
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公开(公告)号：US20180363508A1
公开(公告)日：2018-12-20
申请号：US15623715
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D25/26 , F01D25/005 , F05D2260/30 , F05D2300/175 , F05D2300/603
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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