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公开(公告)号：US11352886B2
公开(公告)日：2022-06-07
申请号：US16754302
申请日：2017-10-13
Applicant: General Electric Company
Inventor： James Albert Tallman , Andrew Philip Shapiro , Gary Michael Itzel , Curtis Alan Johnson , Victor John Morgan , Jacob John Kittleson , Bradley Thomas Richards
Abstract: A component includes an outer wall that includes an exterior surface, and at least one plenum defined interiorly to the outer wall and configured to receive a cooling fluid therein. The component also includes a coating system disposed on the exterior surface. The coating system has a thickness. The component further includes a plurality of adaptive cooling openings defined in the outer wall. Each of the adaptive cooling openings extends from a first end inflow communication with the at least one plenum, outward through the exterior surface and to a second end covered underneath at least a portion of the thickness of the coating system.
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公开(公告)号：US11333024B2
公开(公告)日：2022-05-17
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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公开(公告)号：US10774656B2
公开(公告)日：2020-09-15
申请号：US15948207
申请日：2018-04-09
Applicant: General Electric Company
Inventor： Gary Michael Itzel , Jeffrey Clarence Jones , James William Vehr
Abstract: An airport having an exterior wall including a plurality of spaced layers for improved cooling and lifetime is disclosed. The airfoil and exterior wall are made by additive manufacturing. The exterior wall includes an exterior layer, an intermediate layer, and an interior layer each separated from adjacent layers by a plurality of standoff members; a plurality of first cooling chambers between the exterior and intermediate layers, the chambers partitioned by a first partitioning wall; a plurality of second cooling chambers between in the intermediate and interior layers, the chambers partitioned by a second partitioning wall; a thermal barrier coating on the exterior layer; a plurality of impingement openings in the intermediate layer and a second plurality of impingement openings in the interior layer; and a plurality of cooling passages in the exterior layer. The exterior layer may also include plateaus on an exterior face through which the cooling passages extend.
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公开(公告)号：US10480327B2
公开(公告)日：2019-11-19
申请号：US15397249
申请日：2017-01-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas William Rathay , James Albert Tallman , Gary Michael Itzel
Abstract: A component configured for impingement cooling includes an inner wall defining a plurality of apertures. Each aperture of the plurality of apertures is configured to emit a cooling fluid therethrough. The component also includes an outer wall spaced from the inner wall. The outer wall and the inner wall extend along a longitudinal axis of the component. The component further includes a plurality of angled walls extending between the inner wall and the outer wall. The plurality of angled walls define a plurality of angled channels in fluid communication with the plurality of apertures. Each angled wall of the plurality of angled walls extends at an acute angle relative to the longitudinal axis.
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公开(公告)号：US10472973B2
公开(公告)日：2019-11-12
申请号：US15174271
申请日：2016-06-06
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：US20170175541A1
公开(公告)日：2017-06-22
申请号：US14977102
申请日：2015-12-21
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Gary Michael Itzel , Brendon James Leary , Joseph Anthony Weber
CPC classification number: F01D5/187 , F01D5/18 , F01D5/186 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/127 , F05D2240/307 , F05D2240/35 , F05D2260/202 , F05D2260/22141
Abstract: A cooling system according to an embodiment includes: a pin fin bank cooling circuit; and an air feed cavity for supplying cooling air to the pin fin bank cooling circuit; wherein the pin fin bank cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade and a first set of near wall cooling channels of the multi-wall blade.
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7.发明申请公开(公告)号：US20160362985A1
公开(公告)日：2016-12-15
申请号：US14739944
申请日：2015-06-15
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Carlos Miguel Miranda , Gary Michael Itzel
CPC classification number: F01D5/187 , F01D5/147 , F01D5/186 , F01D5/288 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/122 , F05D2240/304 , F05D2240/305 , F05D2240/306 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: A hot gas path component includes a substrate having an outer surface and an inner surface. The inner surface defines an interior space. The outer surface defines a pressure side surface and a suction side surface. The pressure and suction side surfaces are joined together at a leading edge and at a trailing edge. A first cooling passage is formed in the suction side surface of the substrate. It is coupled in flow communication to the interior space. A second cooling passage, separate from the first cooling passage, is formed in the pressure side surface. The second cooling passage is coupled in flow communication to the interior space. A cover is disposed over at least a portion of the first and second cooling passages. The interior space channels a cooling fluid to the first and second cooling passages, which channel the cooling fluid therethrough to remove heat from the component.
Abstract translation: 热气体路径部件包括具有外表面和内表面的基板。 内表面限定了内部空间。 外表面限定了压力侧表面和吸力侧表面。 压力和吸力侧表面在前缘和后缘处连接在一起。 第一冷却通道形成在基板的吸力侧表面上。 它与流动通信耦合到内部空间。 与第一冷却通道分开的第二冷却通道形成在压力侧表面上。 第二冷却通道与内部空间流动联接。 盖子设置在第一和第二冷却通道的至少一部分上。 内部空间将冷却流体引导到第一和第二冷却通道，第一和第二冷却通道将冷却流体通过其中以从部件移除热量。
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公开(公告)号：US11519281B2
公开(公告)日：2022-12-06
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
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公开(公告)号：US20210270141A1
公开(公告)日：2021-09-02
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
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公开(公告)号：US10995621B2
公开(公告)日：2021-05-04
申请号：US16182113
申请日：2018-11-06
Applicant: General Electric Company
Abstract: An airfoil having a wall structure including a plurality of spaced walls for improved cooling and lifetime is disclosed. The airfoil and walls are made by additive manufacturing. The airfoil includes an exterior wall, an intermediate wall, and an interior wall each separated from adjacent walls by a plurality of standoff members; a plurality of outer cooling chambers defined between the exterior and intermediate walls, the chambers partitioned by an outer partition; a plurality of intermediate cooling chambers defined between the intermediate and interior walls, the chambers partitioned by an intermediate partition; a thermal barrier coating on each of the exterior wall and the intermediate wall; a first plurality of impingement openings through the intermediate wall; a second plurality of impingement openings through the interior wall; and a plurality of cooling passages through the exterior wall.
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