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公开(公告)号：US09718735B2
公开(公告)日：2017-08-01
申请号：US14612806
申请日：2015-02-03
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John McConnell Delvaux , Andres Jose Garcia-Crespo , Victor John Morgan , Jacob John Kittleson
IPC: B32B3/24 , F01D25/12 , F01D25/24 , C04B35/00 , C04B35/44 , C04B35/52 , C04B35/565 , B29C70/54 , F01D5/18 , B29C71/04 , F01D25/14 , F01D5/28 , F01D11/08 , F02C6/06 , F02C6/08 , B29L31/00 , B32B3/26 , F01D11/24
CPC classification number: C04B35/565 , B29C70/545 , B29C71/04 , B29L2031/7504 , B32B3/266 , C04B35/44 , C04B35/52 , F01D5/186 , F01D5/282 , F01D5/284 , F01D5/288 , F01D11/08 , F01D11/24 , F01D25/12 , F01D25/14 , F02C6/06 , F02C6/08 , F05D2230/90 , F05D2240/11 , F05D2260/202 , F05D2260/232 , F05D2270/09 , F05D2270/11 , F05D2270/112 , F05D2300/2261 , F05D2300/6033
Abstract: Components are disclosed which include a CMC substrate having a first surface and a second surface. The first surface is in fluid communication with a compressed, dry fluid, and the second surface is in fluid communication with a wet fluid stream and includes a hermetic coating. The components further include at least one opening extending from the first surface through a portion of the CMC substrate, wherein, upon removal of a fragment of one or both of the hermetic coating and the CMC substrate, the at least one opening selectively permits a flow of the compressed, dry fluid to the second surface. In one embodiment, the component is a gas turbine component, the wet fluid stream is a hot combustion stream, the hermetic coating is an environmental barrier coating, and the flow reduces or eliminates volatilization of the CMC substrate. Methods for forming the components are also disclosed.
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22.发明申请公开(公告)号：US20170173685A1
公开(公告)日：2017-06-22
申请号：US14973595
申请日：2015-12-17
Applicant: General Electric Company
Inventor： Jacob John Kittleson
Abstract: A mold assembly for use in forming a component having a first internal passage defined therein includes a mold that defines a mold cavity therein. The mold assembly also includes a lattice structure selectively positioned at least partially within the mold cavity and formed from a first material. The first material is at least partially absorbable by a component material in a molten state. The mold assembly further includes a first segmented core that includes at least one joint segment coupled to the lattice structure. The at least one joint segment is coupled in serial flow communication to at least one extension segment such that a first hollow structure is defined. A first inner core is disposed within the first hollow structure such that at least a portion of the first inner core defines the first internal passage when the component is formed in the mold assembly.
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公开(公告)号：US09581037B2
公开(公告)日：2017-02-28
申请号：US14697765
申请日：2015-04-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Victor John Morgan , Jacob John Kittleson , Neelesh N. Sarawate
CPC classification number: F01D11/005 , F01D25/12 , F02C7/18 , F05D2220/32 , F05D2240/55 , F05D2260/20 , F16J15/064
Abstract: The present application provide a seal for use between components engine facing a high pressure cooling air flow and a hot gas path in a gas turbine. The seal may include a first shim, a second shim with an air exit hole, one or more middle layers positioned between the first shim and the second shim, and one or more cooling pathways extending through the middle layers for the high pressure cooling air flow to pass therethrough and exit via the air exit hole into the hot gas path.
Abstract translation: 本申请提供了在面向高压冷却空气流的部件发动机和燃气涡轮机中的热气体路径之间使用的密封件。 密封件可以包括第一垫片，具有空气出口孔的第二垫片，位于第一垫片和第二垫片之间的一个或多个中间层，以及延伸穿过用于高压冷却空气流的中间层的一个或多个冷却路径 从而通过空气出口孔流入热气路径。
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公开(公告)号：US20150174837A1
公开(公告)日：2015-06-25
申请号：US14568443
申请日：2014-12-12
Applicant: General Electric Company
Inventor： Sandra Beverly Kolvick , Don Mark Lipkin , Jonathan Matthew Lomas , Thomas Robert Reid , Jacob John Kittleson
IPC: B29C73/02
CPC classification number: B29C73/025 , B29K2103/04 , B29L2031/08
Abstract: A turbine component patch delivery system can include a support arm and a deposition tool supported by the support arm. The deposition tool can include a reservoir configured to house a turbine component patch material and a dispenser configured to dispense the turbine component patch material from the reservoir onto a surface of a turbine component.
Abstract translation: 涡轮机部件补片输送系统可以包括由支撑臂支撑的支撑臂和沉积工具。 沉积工具可以包括构造成容纳涡轮机部件补片材料的储存器和配置成将涡轮机部件补片材料从储存器分配到涡轮机部件的表面上的分配器。
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公开(公告)号：US11852018B1
公开(公告)日：2023-12-26
申请号：US17818760
申请日：2022-08-10
Applicant: General Electric Company
Inventor： Jacob John Kittleson
CPC classification number: F01D11/001 , F01D9/04 , F01D11/08 , F05D2220/32 , F05D2240/128 , F05D2240/55
Abstract: A nozzle includes an endwall connected to an airfoil at one of a tip and root of the airfoil. The endwall includes a first and second side slash faces at respective circumferential edges thereof. The endwall also includes an inner surface extending between the first and second side slash faces. The inner surface includes a first planar surface portion adjacent to the first side slash face, a second planar surface portion adjacent to the second side slash face, and an arcuate surface portion extending between the first and second planar surface portions. The planar surface portions reduce a chute height by reducing hot gas path curvature locally along the side slash faces, which reduces working fluid ingestion between endwalls of the adjacent nozzles. The planar surface portions can be applied to an inner and/or an outer endwall of a nozzle.
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Patent Agency Ranking
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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27.发明申请公开(公告)号：US20210254484A1
公开(公告)日：2021-08-19
申请号：US16793266
申请日：2020-02-18
Applicant: General Electric Company
Inventor： Jacob John Kittleson , Robert Frank Hoskin
Abstract: A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at an arc having a peak that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.
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公开(公告)号：US10443410B2
公开(公告)日：2019-10-15
申请号：US15624893
申请日：2017-06-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Peter de Diego , Jacob John Kittleson
IPC: F01D5/00 , F01D5/28 , F01D5/14 , C04B35/71 , C04B35/622
Abstract: A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.
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公开(公告)号：US20190255550A1
公开(公告)日：2019-08-22
申请号：US15898285
申请日：2018-02-16
Applicant: General Electric Company
Abstract: A method of forming a cooling assembly in a turbomachine part is provided. The method includes placing an encapsulated diffuser insert partially into a hole in the turbomachine part. The encapsulated diffuser insert has an unobstructed central passageway with a generally circular cross-section at a first end and an elongated rectangular cross-section at a second end opposing the first end. The second end has a sacrificial cap. A coating step coats the turbomachine part to at least partially encapsulate the encapsulated diffuser insert in a coating. A removing step removes the sacrificial cap to enable air flow through the central passageway. The encapsulated diffuser insert remains in the hole of the turbomachine part and the coating, thereby providing the unobstructed central passageway with a generally circular first end and an elongated rectangular second end adjacent to an outer surface of the turbomachine part.
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公开(公告)号：US10022921B2
公开(公告)日：2018-07-17
申请号：US14568458
申请日：2014-12-12
Applicant: General Electric Company
Inventor： Jacob John Kittleson , Don Mark Lipkin
Abstract: A turbine component patch delivery system can include a compressed gas source fluidly connected to a delivery line comprising a dispensing end. The turbine component patch delivery system can further include one or more turbine component patch carriers that can be projected out of the dispensing end of the delivery line by the compressed gas source, wherein each of the one or more turbine component patch carriers comprise a turbine component patch material housed within a breakaway shell.
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