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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
摘要： 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：US11034842B2
公开(公告)日：2021-06-15
申请号：US16220804
申请日：2018-12-14
发明人： Matthew Troy Hafner , John McConnell Delvaux , Jason Robert Parolini , Rajendra Kumar Bordia , Quan Li
摘要： A coating includes: at least 34.9 percent by mass silicon dioxide; at least 9.1 percent by mass aluminum oxide; and at least 16.1 percent by mass yttrium oxide.
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公开(公告)号：US20210140328A1
公开(公告)日：2021-05-13
申请号：US17151799
申请日：2021-01-19
摘要： A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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4.发明申请公开(公告)号：US20200256204A1
公开(公告)日：2020-08-13
申请号：US16270071
申请日：2019-02-07
IPC分类号： F01D5/30
摘要： A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US10544701B2
公开(公告)日：2020-01-28
申请号：US15623990
申请日：2017-06-15
摘要： A turbine shroud assembly is disclosed including an inner shroud, an outer shroud, a shroud dampening pin, and a biasing apparatus. The inner shroud is adjacent to a hot gas path. The outer shroud is adjacent to the inner shroud and distal from the hot gas path, and includes a channel extending from an aperture adjacent to the inner shroud. The shroud dampening pin is within the channel and contacts the inner shroud, and includes a shaft, a contact surface, and a cap. The shaft is within the channel. The contact surface extends through the aperture in contact with the inner shroud. The cap is distal across the shaft from the contact surface. The biasing apparatus contacts the cap, is driven by a pressurized fluid, and provides a biasing force away from the outer shroud along the shroud dampening pin to the inner shroud through the contact surface.
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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
摘要： 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：US09664052B2
公开(公告)日：2017-05-30
申请号：US13633928
申请日：2012-10-03
CPC分类号： F01D5/282 , F01D5/288 , F05D2220/30 , F05D2260/941 , F05D2300/2261 , F05D2300/6012 , F05D2300/6033 , Y10T29/49336
摘要： A turbine component, a turbine blade, and a turbine component fabrication process are disclosed. The turbine component includes ceramic matrix composite plies and a feature configured for preventing interlaminar tension of the ceramic matrix composite plies. The feature is selected from the group consisting of ceramic matrix composite tows or precast insert tows extending through at least a portion of the ceramic matrix composite plies, a woven fabric having fiber tows or a precast insert preventing contact between a first set of the ceramic matrix composite plies and a second set of the ceramic matrix composite plies, and combinations thereof. The process includes laying up ceramic matrix composite plies in a preselected arrangement and securing a feature configured for interlaminar tension.
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公开(公告)号：US11572791B1
公开(公告)日：2023-02-07
申请号：US17574084
申请日：2022-01-12
摘要： A vibration damping system for a turbine nozzle or blade includes a vibration damping element including a plurality of contacting members including a plurality of damper pins. Each damper pin includes a body. A wire mesh member surrounds the body of at least one of the plurality of damper pins. The wire mesh member has a first outer dimension sized for frictionally engaging within a body opening in the turbine nozzle or blade to damp vibration. Spacer members devoid of a wire mesh member may also be used. The damper pins can have different sizes to accommodate contiguous body openings of different sizes in the nozzle or blade. The body opening can be angled relative to a radial extent of the nozzle or blade.
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公开(公告)号：US20210340874A1
公开(公告)日：2021-11-04
申请号：US16865999
申请日：2020-05-04
摘要： A coating is applied to a base material. The coating comprises a viscoelastic layer; and a constraint layer; wherein the viscoelastic layer is disposed on the base material and the constraint layer is disposed on the viscoelastic layer.
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公开(公告)号：US11143036B1
公开(公告)日：2021-10-12
申请号：US16998207
申请日：2020-08-20
摘要： A turbine blade includes an airfoil body having an outer tip and a platform; and a part-span shroud positioned between the outer tip and the platform of the airfoil body. The part-span shroud has a first opening extending through the airfoil body and having a first inner surface. The airfoil body includes a second opening extending radially from the first opening and having a second inner surface. A first elongated vibration-damping element is disposed in the first opening, and a second elongated vibration-damping element disposed radially in the second opening. The second elongated vibration-damping element includes a free radially outer end and a radially inner end coupled to the first elongated vibration-damping element. The first elongated vibration-damping element frictionally damps vibration, and the second elongated vibration-damping element damps vibration using impact within the second opening.
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