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1. 发明授权

US10502064B2 Power beam welded cavity-back titanium hollow fan blade 有权
公开(公告)号：US10502064B2
公开(公告)日：2019-12-10
申请号：US15670654
申请日：2017-08-07
申请人： United Technologies Corporation
发明人： Daniel A. Bales , Dmitri Novikov , Robert C. Dolan , Kenneth A. Frisk , Steven T. Gordon , William R. Graves , Eric W. Malmborg , Francis B. Parisi , Randy P. Salva , Michael A. Weisse , Russell A. Beers , Xuedong Zhou , Christopher Treese , Tri Nguyen
IPC分类号： F01D5/00 , F01D5/14 , F04D29/26 , B23P15/04 , B23K15/00 , B23K26/28 , F01D5/30 , F01D5/18 , B23K1/00 , B23K26/244 , F04D29/02 , F04D29/32 , F01D9/04 , B23K101/00
CPC分类号： F01D5/147 , B23K1/0018 , B23K15/0006 , B23K15/0053 , B23K26/244 , B23K26/28 , B23P15/04 , F01D5/18 , F01D5/3061 , F04D29/023 , F04D29/26 , F04D29/324 , B23K2101/001 , F01D9/044 , F05D2220/323 , F05D2220/36 , F05D2230/10 , F05D2230/233 , F05D2230/234 , F05D2240/30 , F05D2250/185 , F05D2300/133
摘要： An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

2. 发明申请

US20180281071A1 CLAD ARTICLE AND METHOD FOR FORMING CLAD ARTICLE 审中-公开
公开(公告)号：US20180281071A1
公开(公告)日：2018-10-04
申请号：US15477846
申请日：2017-04-03
申请人： GENERAL ELECTRIC COMPANY
发明人： Srikanth Chandrudu KOTTILINGAM , Brian Lee TOLLISON , Yan CUI
IPC分类号： B22F5/00 , C08J5/12 , C23C10/48 , B21B1/02 , B23K35/00
CPC分类号： B22F5/00 , B21B1/026 , B23K35/005 , B32B2262/101 , C08J5/124 , C23C10/48 , F01D5/005 , F01D5/288 , F01D9/02 , F01D9/023 , F05D2230/22 , F05D2230/233 , F05D2230/234 , F05D2230/237 , F05D2230/80 , F05D2230/90 , F05D2300/611 , F05D2300/6111
摘要： A clad article is disclosed including an article and a cladding layer. The article includes a surface layer, at least one cavity disposed within the article below the surface layer, and at least one microcrack disposed in the surface layer. The surface layer includes an HTW alloy. The cladding layer is disposed on a surface of the surface layer, and is formed from a PSP brazed to the article. The cladding layer is disposed over the at least one microcrack. A method for forming the clad article is disclosed including disposing the PSP on the article and brazing the PSP to the article. Brazing the PSP to the article forms the cladding layer disposed on the article over the at least one microcrack.

3. 发明申请

US20180003063A1 Cavity Sealing 审中-公开
公开(公告)号：US20180003063A1
公开(公告)日：2018-01-04
申请号：US15635869
申请日：2017-06-28
申请人： ROLLS-ROYCE plc
发明人： Phillip J. DOORBAR
IPC分类号： F01D5/26 , B22F7/08 , F01D5/28 , F04D29/66 , B22F3/10 , F04D29/38 , B23K20/10
CPC分类号： F01D5/26 , B22F3/10 , B22F5/04 , B22F7/08 , B23K20/10 , B23P6/002 , F01D5/005 , F01D5/16 , F01D5/28 , F04D29/083 , F04D29/324 , F04D29/388 , F04D29/668 , F05D2220/32 , F05D2230/233 , F05D2230/234 , F05D2230/31
摘要： A method of sealing one or more openings provided in a wall of an aerofoil for a gas turbine engine, the aerofoil comprising at least one cavity which is at least partly filled with a vibration damping material, the method comprising steps to provide a metallic material onto the wall of the aerofoil in order to cover the opening and bond the metallic material to the wall of the aerofoil to seal the opening.

4. 发明授权

US09359897B2 Method for building a gas turbine engine component 有权
标题翻译：燃气涡轮发动机部件的构成方法
公开(公告)号：US09359897B2
公开(公告)日：2016-06-07
申请号：US14460633
申请日：2014-08-15
申请人： Siemens Energy, Inc.
发明人： Gerald J. Bruck , Ahmed Kamel
IPC分类号： B23K9/04 , F01D5/00 , B23K26/06 , B23K26/34 , B23K15/00 , B23P6/00
CPC分类号： F01D5/005 , B22F3/105 , B22F3/1055 , B22F5/04 , B22F7/062 , B23K15/0086 , B23K15/0093 , B23K26/0626 , B23K26/082 , B23K26/34 , B23K2101/001 , B23K2103/26 , B23P6/007 , F01D5/187 , F05D2230/233 , F05D2230/31 , Y02P10/295
摘要： A method, including: providing a layer of powder material (156) on a substrate (130); and traversing an energy beam (15) across the layer of powder material to form a cladding layer (10), wherein the cladding layer forms a layer of an airfoil. The traversing step includes: starting a first path (40) and a second path (44) of traversal of the energy beam from a common initiation point (48); forming a portion (60) of a first side wall (18) of the cladding layer and a first rib section (24) by traversing the energy beam along the first path and concurrently forming a portion (62) of a second side wall (16) of the cladding layer by traversing the energy beam along the second path; and creating not more than one initiation point (72, 96, 118) for each rib section (24, 26, 28) in the cladding layer.
摘要翻译：一种方法，包括：在衬底（130）上提供一层粉末材料（156）; 并穿过所述粉末材料层的能量束（15），以形成包覆层（10），其中所述包覆层形成一个翼型层。横移步骤包括：从公共起始点（48）启动能量束的遍历的第一路径（40）和第二路径（44）; 通过使所述能量束沿着所述第一路径横穿并同时形成第二侧壁（16）的一部分（62），形成所述包层的第一侧壁（18）的一部分（60）和第一肋部（24））通过沿着第二路径横穿能量束; 并且为包覆层中的每个肋部分（24,26,28）创建不超过一个起始点（72,96,118）。

5. 发明授权

US09168606B2 Electrospark deposition process and system for repair of gas turbine 有权
标题翻译：燃气轮机的电喷沉淀工艺及系统
公开(公告)号：US09168606B2
公开(公告)日：2015-10-27
申请号：US13471617
申请日：2012-05-15
申请人： Dechao Lin , John Gregory Obeirne , David Vincent Bucci , Srikanth Chandrudu Kottilingam , Yan Cui
发明人： Dechao Lin , John Gregory Obeirne , David Vincent Bucci , Srikanth Chandrudu Kottilingam , Yan Cui
IPC分类号： B23K9/04 , B23K9/16
CPC分类号： B23K9/044 , B23K9/04 , B23K9/164 , B23K9/173 , B23K9/285 , B23K9/291 , B23K9/32 , B23K9/324 , B23K37/003 , B23K2101/001 , B23P6/007 , F01D5/005 , F05D2230/233
摘要： A system and method for repairing a metal substrate includes an electrospark device and an electrode removably supported in the electrode holder. The electrospark device applies a coating of a material when placed into contact with the metal substrate. A cooling device to lowers the temperature of shielding gas flow below an ambient temperature. A conduit is arranged to direct a flow of the shielding gas to the interface of the electrode and the substrate to cool the area of the substrate receiving the coating.
摘要翻译：用于修复金属基板的系统和方法包括电极装置和可拆卸地支撑在电极支架中的电极。电极装置在与金属基底接触时施加材料的涂层。一种冷却装置，用于降低保护气体流量低于环境温度的温度。导管布置成将保护气体的流动引导到电极和基底的界面，以冷却接收涂层的基底的区域。

6. 发明申请

US20130101425A1 Turbine Blade, and Turbine Rotor and Steam Turbine Using the Turbine Blade 审中-公开
标题翻译：涡轮叶片，以及使用涡轮叶片的涡轮转子和汽轮机
公开(公告)号：US20130101425A1
公开(公告)日：2013-04-25
申请号：US13654468
申请日：2012-10-18
申请人： Hitachi, Ltd.
发明人： Masahiko Arai , Hiroyuki Doi , Hideo Yoda , Katsumi Tanaka
IPC分类号： F03B3/12
CPC分类号： F01D5/288 , B23K15/0006 , B23K15/0093 , B23K2101/001 , F01D5/28 , F05D2230/233 , F05D2300/11 , F05D2300/17
摘要： Disclosed is a turbine blade including a turbine blade substrate including an iron-base alloy; an erosion shield plate including a Co-base alloy; and a shim including a Ni—Fe alloy, in which the erosion shield plate is fixed to a leading edge of the turbine blade substrate with the shim therebetween by an electron beam welding. Thus, a turbine blade having a highly reliable, bonded portion of an erosion shield, and a turbine rotor and a steam turbine using the turbine blade are provided.
摘要翻译：公开了一种涡轮叶片，其包括具有铁基合金的涡轮叶片基板; 包括Co基合金的侵蚀屏蔽板; 以及包括Ni-Fe合金的垫片，其中通过电子束焊接，其间的垫片将侵蚀屏蔽板固定到涡轮叶片基板的前缘。因此，提供了具有高度可靠的防腐蚀屏蔽部分的涡轮叶片，以及使用该涡轮机叶片的涡轮机转子和蒸汽轮机。

7. 发明申请

US20130017067A1 METHOD OF BEAM WELDING OF AN IMPELLER WITH PERFORMANCE OF TWO PASSES ON A SLOT ; IMPELLER AND TURBO MACHINE HAVING SUCH WELD CONFIGURATION 审中-公开
标题翻译：叶片焊接方法，其具有两个通道在槽上的性能; 具有这种焊接配置的叶轮和涡轮机
公开(公告)号：US20130017067A1
公开(公告)日：2013-01-17
申请号：US13515223
申请日：2010-12-07
申请人： Ugo Cantelli , Enzo Miniati , Mirco Innocenti
发明人： Ugo Cantelli , Enzo Miniati , Mirco Innocenti
IPC分类号： F04D29/28 , F04D29/056 , B23K15/00 , B23P15/00 , B23K26/20
CPC分类号： B23K26/26 , B23K15/006 , B23K26/0604 , B23K26/32 , B23K2101/001 , F04D17/12 , F04D29/023 , F04D29/284 , F05D2230/233 , F05D2230/234
摘要： Systems and methods according to these exemplary embodiments provide welding techniques for impeller blades associated with impellers in centrifugal compressors. According to one exemplary embodiment, a connection area of the impeller blade has a “hammer”-shaped cross-sectional area which facilitates beam welding of the connection area to a slot in the surface or body to which the blade is to be connected.
摘要翻译：根据这些示例性实施例的系统和方法提供了与离心式压缩机中的叶轮相关联的叶轮叶片的焊接技术。根据一个示例性实施例，叶轮叶片的连接区域具有锤形横截面面积，其有助于将连接区域焊接到刀片将被连接到的表面或主体中的狭槽。

8. 发明授权

US08262350B2 Heat insulating structure for expansion turbine, and method of manufacturing the same 失效
标题翻译：用于膨胀涡轮机的隔热结构及其制造方法
公开(公告)号：US08262350B2
公开(公告)日：2012-09-11
申请号：US12054916
申请日：2008-03-25
申请人： Seiichiro Yoshinaga , Toshio Takahashi , Hirohisa Wakisaka
发明人： Seiichiro Yoshinaga , Toshio Takahashi , Hirohisa Wakisaka
IPC分类号： F01D5/08 , F04D29/58
CPC分类号： F01D15/005 , F01D25/145 , F05D2230/233 , F05D2260/903 , Y10T29/49236
摘要： A heat insulating structure for an expansion turbine includes an adiabatic expansion device including an expander body that includes an outlet passage for refrigerant fluid at a central portion thereof and an introduction chamber for refrigerant fluid communicating with an inlet of the outlet passage on an outer peripheral portion thereof, and a turbine impeller that is rotatably provided at the inlet and braked by a braking device. The adiabatic expansion device adiabatically expands refrigerant fluid by rotating the turbine impeller with refrigerant fluid that flows from the introduction chamber to the outlet passage side. A heat-insulating layer, which surrounds the entire periphery of the outlet passage over the entire length of the introduction chamber, is formed between the introduction chamber and the outlet passage. Accordingly, it is possible to improve turbine efficiency by reducing transfer of heat of refrigerant fluid from the introduction chamber to the outlet passage.
摘要翻译：用于膨胀涡轮机的绝热结构包括绝热膨胀装置，该绝热膨胀装置包括膨胀机体，该膨胀机主体包括在其中心部分处的用于制冷剂流体的出口通道和用于在外周部分与出口通道的入口连通的制冷剂流体导入室以及可旋转地设置在入口处并由制动装置制动的涡轮叶轮。绝热膨胀装置通过从引入室流向出口通道侧的制冷剂流体旋转涡轮叶轮，绝热地膨胀制冷剂流体。在引入室和出口通道之间形成有在引入室的整个长度上围绕出口通道的整个周边的绝热层。因此，可以通过减少制冷剂流体从引入室向出口通道的转移而提高涡轮效率。

9. 发明授权

US08061981B2 Blade for a flow machine 有权
标题翻译：刀片为流动机
公开(公告)号：US08061981B2
公开(公告)日：2011-11-22
申请号：US11719412
申请日：2004-12-03
申请人： Pieter Groth , Hans Mårtensson
发明人： Pieter Groth , Hans Mårtensson
IPC分类号： F01D9/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/186 , F05D2230/232 , F05D2230/233 , F05D2230/234 , F05D2230/60 , F05D2250/712 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： In a blade intended to be exposed to a gas flow at high speed during operation of a flow machine comprising the blade, the blade includes a front end designed to face towards the incoming gas flow and a rear end. The front end is provided with a concave area that is such that during operation a stagnation point for the incoming gas flow arises at a distance in front of an outer blade surface that defines the concave area and such that the outer blade surface is thereby at least partially protected from the incoming gas flow.
摘要翻译：在旨在在包括叶片的流动机器的操作期间高速暴露于气体流的叶片中，叶片包括设计成面向进入气流的前端和后端。前端设置有凹面积，使得在操作期间，用于进入气流的停滞点在限定凹区的外刀片表面前方一定距离处产生，从而至少外刀片表面至少部分地防止进入的气流。

10. 发明授权

US07837437B2 Turbine nozzle segment and repair method 有权
标题翻译：涡轮喷嘴段和修理方法
公开(公告)号：US07837437B2
公开(公告)日：2010-11-23
申请号：US11683005
申请日：2007-03-07
申请人： Wayne R. Grady , Timothy L. Siebert
发明人： Wayne R. Grady , Timothy L. Siebert
IPC分类号： F01D9/02
CPC分类号： F01D5/005 , B23P6/005 , F01D9/041 , F05D2230/10 , F05D2230/21 , F05D2230/233 , F05D2230/237 , Y02T50/67 , Y10T29/49238 , Y10T29/49318
摘要： A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.
摘要翻译：一种维修涡轮喷嘴段的方法，其具有设置在外带和内带之间的至少一个叶片。该方法包括从不可修复的喷嘴段使用诸如蜂窝背衬条残留物的可抢救部分，以及将蜂窝背衬条连接到替换铸件。替代铸件包括形成在内带上的榫头，其与形成在蜂窝背衬带的背侧上的榫接合。还公开了与该方法相关使用的喷嘴段和喷嘴段铸造。

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