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公开(公告)号：US10006293B1
公开(公告)日：2018-06-26
申请号：US14805918
申请日：2015-07-22
申请人： Russell B Jones
发明人： Russell B Jones
IPC分类号： F01D5/18 , B22F5/04 , B22F7/08 , B22F3/105 , F01D25/12 , B23P15/02 , B23K15/00 , B33Y80/00 , B33Y10/00 , F01D5/00
CPC分类号： F01D5/186 , B22F3/1055 , B22F5/04 , B22F7/06 , B22F7/08 , B22F2005/103 , B22F2999/00 , B23K15/0086 , B23P15/02 , B23P15/04 , B23P2700/06 , B33Y10/00 , B33Y80/00 , F01D5/005 , F01D25/12 , F05D2220/32 , F05D2230/22 , F05D2230/233 , F05D2230/237 , F05D2230/30 , F05D2250/25 , F05D2250/71 , F05D2260/202 , F05D2300/131 , Y02P10/295 , B22F2201/03
摘要： A part formed using an metal additive manufacturing process such as a turbine airfoil with an oversized feature such as an oversized hole, where the oversized hole is filled with a preform having a shape of a normal sized hole and secured within the part using a braze or weld material, and where the preform is removed to leave within the part the normal sized hole. The preform is made of a refractory material that can be removed from the part by exposure to oxygen.
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公开(公告)号：US10001013B2
公开(公告)日：2018-06-19
申请号：US14198659
申请日：2014-03-06
CPC分类号： F01D5/082 , B23P15/02 , F01D5/187 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/201 , Y02T50/676 , Y10T29/49341
摘要： Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.
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公开(公告)号：US20180117720A1
公开(公告)日：2018-05-03
申请号：US15342648
申请日：2016-11-03
CPC分类号： B23P15/02 , C23C14/022 , C23C14/028 , C23C14/083 , C23C14/325 , F01D5/00 , F05D2240/30 , Y02T50/6765
摘要： The present invention relates to a conditioning method of gas turbine engine components (e.g. compressor blades and vanes) for aerodynamic noise reduction. The gas turbine engine components are plasma treated in a high vacuum environment to generally reach a surface roughness (Ra) below 150 nanometers and in some cases below 25 nanometers. Then during the same process the components are coated using either a metallic or ceramic, hard, thin coating ranging from 100 to 3000 nanometers in thickness depending on desired surface smoothness and non-fouling properties. The same treatment combined with a surface relaxation process, which is part of a smoothing process, allows applying even up to 100 micrometers of hard coating without changes to high cycle fatigue properties and overall performance. Improved surface smoothness of the components and enhanced non-adhesiveness of the contaminants advance the quality of the flow through the gas path and compressor aerodynamic noise reduction.
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公开(公告)号：US20170334010A1
公开(公告)日：2017-11-23
申请号：US15656063
申请日：2017-07-21
IPC分类号： B23K9/04 , F23R3/00 , B23K9/173 , F02C7/22 , F01D5/22 , B23P15/04 , F01D5/28 , B23K9/32 , F01D5/12 , B23P15/02 , F01D5/18 , B23K103/18 , B23K101/00 , F01D5/00
CPC分类号： B23K9/044 , B23K9/048 , B23K9/173 , B23K9/32 , B23K2101/001 , B23K2103/26 , B23P15/02 , B23P15/04 , B23P2700/06 , F01D5/005 , F01D5/12 , F01D5/186 , F01D5/225 , F01D5/286 , F02C7/22 , F05D2230/12 , F05D2230/80 , F05D2260/20 , F23R3/002 , Y10T428/13 , Y10T428/24273
摘要： A method for modifying an aperture in a component, a system for modifying flow through a component, and a turbine component are disclosed. The method includes providing a substrate having at least one aperture having an electrically-conductive surface, providing a deposition device including an ESD torch, the ESD torch including an aperture penetrating electrode including a conductive material, inserting the aperture penetrating electrode at least partially into the aperture, and generating an arc between the aperture penetrating electrode and the electrically-conductive surface to deposit electrode material within the aperture. The system includes the ESD torch removably supported in an electrode holder. The turbine component includes at least one aperture having an electrospark deposited material along an electrically-conductive surface, the electrospark deposited material providing modified fluid flow through the turbine component.
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公开(公告)号：US09803258B2
公开(公告)日：2017-10-31
申请号：US13584257
申请日：2012-08-13
申请人： David S. Murphy
发明人： David S. Murphy
CPC分类号： C21D10/005 , B23K26/356 , B23P9/00 , B23P15/02 , B24B19/14 , B24C1/00 , F01D5/286 , Y10T29/49336
摘要： A method of post processing a laser peened component to remove a laser remelt layer is proposed. The post processing includes a series of steps including grit blasting, chemical etching and mechanical finishing the component. This will ensure that the mechanical property (i.e., damage tolerance) benefit of laser peening is restored to the surface of the component.
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公开(公告)号：US20170274451A1
公开(公告)日：2017-09-28
申请号：US15518570
申请日：2015-08-06
发明人： PHILIP HATHERLEY , SUSANNE KAMENZKY , GARY B. MERRILL , SAMUEL R. MILLER, Jr. , DIMITRIOS THOMAIDIS
CPC分类号： B22D31/002 , B23H3/04 , B23H9/10 , B23H9/14 , B23H9/16 , B23P15/02 , F01D5/18 , F05D2230/11
摘要： A method of forming a component for a gas turbine engine, including: casting a component around a ceramic core, wherein the ceramic core forms a pilot channel (40) in the component, the pilot channel oriented from a base (176) to a tip (20) of the component; sinking an ECM electrode into the pilot channel; and enlarging the pilot channel to form an inner surface of an external wall (120) of the component via electro-chemical machining, wherein a contour (94) of the inner surface is different than a contour of the pilot channel.
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公开(公告)号：US20170252896A1
公开(公告)日：2017-09-07
申请号：US15512215
申请日：2015-09-15
申请人： EUROPE TECHNOLOGIES
CPC分类号： B24C1/10 , B23P15/02 , F01D5/005 , F01D5/147 , F01D5/282 , F01D5/284 , F01D5/286 , F01D5/288 , F01D9/02 , F05D2220/36 , F05D2230/90 , F05D2300/171 , F05D2300/173 , F05D2300/603 , F05D2300/6033
摘要： A method for treating a composite part including a metal protective duct fixed to a core by a binder, so as to be able to separate the duct from the core, including the steps of: subjecting the metal duct to compressive stresses tending to lengthen same, and b) if necessary, heating or cooling the part in order to soften or weaken the binder.
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公开(公告)号：US20170138208A1
公开(公告)日：2017-05-18
申请号：US15214219
申请日：2016-07-19
申请人： ROLLS-ROYCE plc
发明人： Steven HILLIER
CPC分类号： F01D9/06 , B23P15/02 , C04B35/00 , F01D5/282 , F01D5/284 , F01D9/02 , F01D9/041 , F05D2220/32 , F05D2230/10 , F05D2300/6033 , F05D2300/614
摘要： A method of constructing the nozzle guide passage may include the steps of: providing a tubular pre-form having a plurality of layers of unconsolidated CMC fibres in which the internal walls of the tubular preform provide either working surfaces which define the main gas path walls of the assembled nozzle vane, or extraneous wall portions which do not provide working surfaces of the assembled nozzle guide vane arrangement; cutting the wall portions to provide one or more flaps which remain attached to the pre-form via a connecting portion of wall; and, displacing the flap from a first pre-cut position, to a second consolidation position to provide one or more ancillary features.
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9.发明授权Apparatus for workpiece processing having integrated energy guide and media storage and related system and method 有权具有集成能量指导和媒体存储的相关系统和方法的工件处理装置公开(公告)号：US09586298B2
公开(公告)日：2017-03-07
申请号：US14566542
申请日：2014-12-10
发明人： Jason B. Jones , Peter Coates
IPC分类号： B05B12/00 , B05B13/02 , B23K26/00 , B23K26/34 , B23K26/14 , B05C19/00 , B23P23/04 , B23K26/08 , B05C19/06 , B29C67/00 , B05C5/00 , B05D1/02 , B05D3/00 , B23K10/02 , B23K15/00 , B23K15/08 , B23K26/06 , B23K26/36 , B22F3/105 , B41J2/175 , B23K9/32 , B33Y30/00
CPC分类号： B23P23/04 , B05B7/228 , B05B12/00 , B05B13/02 , B05B15/65 , B05C5/001 , B05C19/06 , B05D1/02 , B05D3/002 , B22F3/1055 , B23K9/04 , B23K9/323 , B23K10/027 , B23K15/0026 , B23K15/0086 , B23K15/08 , B23K26/0093 , B23K26/0626 , B23K26/082 , B23K26/0876 , B23K26/0884 , B23K26/1482 , B23K26/34 , B23K26/342 , B23K26/36 , B23K26/702 , B23K2101/001 , B23P15/02 , B29C64/20 , B29C73/24 , B29L2031/082 , B33Y10/00 , B33Y30/00 , B33Y80/00 , B41J2/175
摘要： A system includes a machine tool having a clamp. The system also includes a processing head configured to be temporarily held by the clamp of the machine tool. The processing head is also configured to deposit one or more media onto a workpiece. The processing head includes a guide configured to direct energy from an energy source onto the workpiece and/or the one or more media. The processing head also includes one or more supplies including one or more reservoirs within the processing head. The one or more reservoirs are configured to receive the one or more media, store the one or more media as the processing head is moved from one location to another location, and provide the one or more media.
摘要翻译： 一种系统包括具有夹具的机床。 该系统还包括配置成由机床的夹具临时保持的加工头。 处理头还被配置成将一个或多个介质沉积到工件上。 处理头包括引导件，其构造成将能量从能量源引导到工件和/或一个或多个介质上。 处理头还包括一个或多个包括处理头内的一个或多个储存器的供给源。 一个或多个储存器被配置为接收一个或多个介质，当处理头从一个位置移动到另一个位置时存储一个或多个介质，并提供一个或多个介质。
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10.发明申请公开(公告)号：US20160375530A1
公开(公告)日：2016-12-29
申请号：US15106235
申请日：2014-12-09
申请人： SNECMA
发明人： Patrick Emilien Paul Emile Huchin , Sébastien Deschandol , Sébastien Digard Brou De Cuissart , Serge Fargeas , Marc Soisson , Anthony Texier , Valéry Piaton
IPC分类号： B23P15/02
摘要： The invention relates to a method for producing multiple metal turbine engine parts, comprising steps consisting in: a) casting a metal alloy in a mould in order to produce a blank (3); and b) machining the blank in order to produce the parts, characterized in that the blank obtained by casting is a solid polyhedron with two generally trapezoidal opposing sides (30a, 30b), and the parts are machined in the blank.
摘要翻译： 本发明涉及一种生产多个金属涡轮发动机部件的方法，包括以下步骤：a）在模具中铸造金属合金以制造坯料（3）; 以及b）加工所述坯件以制造所述零件，其特征在于，通过铸造获得的坯料是具有两个大致梯形的相对侧（30a，30b）的实心多面体，并且所述零件在坯料中加工。
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