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公开(公告)号：US10731471B2
公开(公告)日：2020-08-04
申请号：US16235095
申请日：2018-12-28
发明人： Stanley Kevin Widener , John McConnell Delvaux , Matthew Troy Hafner , James Zhang , Peter de Diego
摘要： A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.
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公开(公告)号：US10590776B2
公开(公告)日：2020-03-17
申请号：US15174332
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. 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：US10391724B2
公开(公告)日：2019-08-27
申请号：US15433548
申请日：2017-02-15
发明人： Jason Robert Parolini , John McConnell Delvaux , Canan Uslu Hardwicke , Glenn Curtis Taxacher , James Joseph Murray
摘要： A method of forming a pre-form ceramic matrix composite mold for a ceramic matrix composite (CMC) component including providing pieces of CMC remnant scrap material and randomly arranging the pieces of CMC remnant scrap material relative to one another. The method further includes debulking the pieces of CMC remnant scrap material into a rigidized shape, the rigidized shape having gaps between adjacent pieces of CMC remnant scrap material of about 10 microns and about 10 mm and a gap spacing between about 50 microns and about 50 mm, and forming the rigidized shape into a mold.
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公开(公告)号：US10287894B2
公开(公告)日：2019-05-14
申请号：US15174182
申请日：2016-06-06
IPC分类号： F01D5/18 , B33Y10/00 , B33Y80/00 , B23K26/342 , B23K26/70 , B22F3/105 , B22F3/24 , B23K15/00 , B23K26/00 , C23C28/04 , F01D9/02 , F01D25/12 , F01D5/14 , F01D5/28 , B23K101/00 , B23K103/08
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. 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：US09981438B2
公开(公告)日：2018-05-29
申请号：US14734028
申请日：2015-06-09
CPC分类号： B29D99/0028 , F01D5/282 , F01D5/284 , F05D2300/222 , Y10T29/4998
摘要： A pre-form CMC cavity and method of forming pre-form CMC cavity for a ceramic matrix component includes providing a mandrel, applying a base ply to the mandrel, laying-up at least one CMC ply on the base ply, removing the mandrel, and densifying the base ply and the at least one CMC ply. The remaining densified base ply and at least one CMC ply form a ceramic matrix component having a desired geometry and a cavity formed therein. Also provided is a method of forming a CMC component.
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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
发明人： Paul Stephen DiMascio , Victor John Morgan , Jason Robert Parolini , Glenn Curtis Taxacher , Frederic Woodrow Roberts, Jr. , Jacob John Kittleson , John McConnell Delvaux
IPC分类号： 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分类号： 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
摘要： 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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公开(公告)号：US20160208625A1
公开(公告)日：2016-07-21
申请号：US15086539
申请日：2016-03-31
IPC分类号： F01D5/30
CPC分类号： F01D5/3015 , F01D5/147 , F01D5/3007 , F01D5/303 , F01D5/3084 , F05D2300/6033
摘要： An assembly and method for affixing a turbomachine rotor blade to a rotor wheel are disclosed. In an embodiment, an adaptor member is provided disposed between the blade and the rotor wheel, the adaptor member including an adaptor attachment slot that is complementary to the blade attachment member, and an adaptor attachment member that is complementary to the rotor wheel attachment slot. A coverplate is provided, having a coverplate attachment member that is complementary to the rotor wheel attachment slot, and a hook for engaging the adaptor member. When assembled, the coverplate member matingly engages with the adaptor member, and retains the blade in the adaptor member, and the assembly in the rotor wheel.
摘要翻译： 公开了一种用于将涡轮机转子叶片固定到转子轮的组件和方法。 在一个实施例中，设置在叶片和转子轮之间的适配器构件，适配器构件包括与叶片附接构件互补的适配器附接槽和与转子轮附接槽互补的适配器附接构件。 提供了一种盖板，其具有与转子轮附接槽互补的盖板附接构件和用于接合适配器构件的钩。 当组装时，盖板构件与适配器构件配合地接合，并将叶片保持在适配器构件中，并且组件在转子轮中。
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公开(公告)号：US20150192029A1
公开(公告)日：2015-07-09
申请号：US13623854
申请日：2012-09-20
CPC分类号： F01D11/12 , F01D5/147 , F01D5/20 , F01D11/08 , F05D2220/32 , Y02T50/672
摘要： Embodiments of the present disclosure are directed toward systems including a tip shroud insert having a retained portion configured to be retained within a pocket of a turbomachine blade and an exposed portion configured to form a dynamic seal with a stationary structural component surrounding the turbomachine blade.
摘要翻译： 本公开的实施例涉及包括尖端护罩插入件的系统，其具有被配置为保持在涡轮机叶片的凹部内的保持部分和被构造成与围绕涡轮机叶片的固定结构部件形成动态密封的暴露部分。
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公开(公告)号：US12071862B2
公开(公告)日：2024-08-27
申请号：US17815376
申请日：2022-07-27
CPC分类号： F01D5/26 , F01D9/041 , F05D2240/128 , F05D2260/38 , F05D2260/96
摘要： A vibration damping system includes a vibration damping element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade between the tip end and the base end thereof, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration damping element includes a plurality of stacked plate members within the body opening. Each plate member is in surface contact with at least one adjacent plate member to cause friction that dampens vibration of the nozzle or blade. The body opening has an inner dimension, and each plate member has an outer dimension sized to frictionally engage the inner dimension of the body opening to damp vibration. Plate members may each include a central opening therein, and a fixed elongated body or cable may extend through the central openings. The damping element may alternatively include a helical metal ribbon spring.
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公开(公告)号：US11976565B2
公开(公告)日：2024-05-07
申请号：US17815372
申请日：2022-07-27
IPC分类号： F01D5/16
CPC分类号： F01D5/16 , F05D2220/32 , F05D2260/96
摘要： A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.
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