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11. 发明申请

US20160107269A1 DUCTILE BORON BEARING NICKEL BASED WELDING MATERIAL 审中-公开
标题翻译： DUCTILE BORON轴承镍基焊接材料
公开(公告)号：US20160107269A1
公开(公告)日：2016-04-21
申请号：US14834840
申请日：2015-08-25
申请人： Liburdi Engineering Limited
发明人： Alexander B. Goncharov , Joseph Liburdi , Paul Lowden
IPC分类号： B23K35/30 , B23K35/02 , C22C19/05
CPC分类号： B23K35/304 , B23K35/0227 , B23K35/0233 , B23K35/0244 , B23K35/0255 , B23K35/0261 , C22C19/055 , C22F1/10
摘要： A ductile boron bearing nickel based welding material which includes boron within the range of 0.4-0.6 wt. % B, carbon from a trace amount to 0.04 wt. % C, 17-23 wt. % Cr, 0.35-10 wt. % Mo, 0.1-4.15 wt. % Nb with nickel or iron and impurities to balance for manufacturing of welding and brazing wires, powders and foils used in the repair of various articles made of nickel, cobalt and iron based alloys.
摘要翻译：一种延性硼轴承镍基焊接材料，其包括在0.4-0.6重量％范围内的硼。％B，微量至0.04重量％的碳。％C，17-23wt。％Cr，0.35-10wt。％Mo，0.1-4.15wt。用镍或铁制造的Nb和用于制造用于镍，钴和铁基合金制成的各种制品的焊接和钎焊线，粉末和箔的制造中的杂质。

12. 发明申请

US20150298263A1 COMPOSITE WELDING WIRE AND METHOD OF MANUFACTURING 审中-公开
标题翻译：复合焊接线及其制造方法
公开(公告)号：US20150298263A1
公开(公告)日：2015-10-22
申请号：US14515001
申请日：2014-10-15
申请人： Liburdi Engineering Limited
发明人： Alexander B. Goncharov , Joseph Liburdi , Paul Lowden , Scott Hastie
IPC分类号： B23K35/02 , B23K35/40 , C25D11/02 , C23C14/34 , C22C19/07 , C23C16/48 , C22C38/54 , C22C38/02 , C22C19/05 , B23K35/30 , C23C14/30
CPC分类号： B23K35/0261 , B23K35/304 , B23K35/3046 , B23K35/3086 , B23K35/404 , C22C19/055 , C22C19/07 , C22C38/02 , C22C38/54 , C23C8/68 , C23C8/70 , C23C10/44 , C23C10/46 , C23C12/02 , C23C14/30 , C23C14/34 , C23C16/487 , C23C24/085 , C25D11/028
摘要： The present invention is a composite welding wire for fusion welding of components manufactured of superalloys. The composite weld wire includes an inner core wire and a surface layer applied and bonded to the inner core wire. The surface layer includes alloying elements selected from among B and Si with a total bulk content of B and Si in the composite welding wire of 0.1 to 10 wt. %. Preferably the total bulk content of B is less than 4 wt. % and the surface layer comprises from 5 to 95 wt. % of the alloying elements selected from among B and Si.
摘要翻译：本发明是用于熔焊由超级合金制成的部件的复合焊丝。复合焊丝包括内芯线和施加并结合到内芯线的表面层。表面层包括选自B和Si中的合金元素，复合焊丝的总体积含量为B，Si为0.1〜10重量％。％。优选地，B的总体积含量小于4wt。％，表层包含5至95wt。从B和Si中选出合金元素的百分比。

13. 发明授权

US4803127A Vapor deposition of metal compound coating utilizing metal sub-halides and coated metal article 失效
标题翻译：使用金属副卤化物和涂覆金属制品的金属化合物涂层的气相沉积
公开(公告)号：US4803127A
公开(公告)日：1989-02-07
申请号：US111144
申请日：1987-10-22
申请人： M. Javid Hakim
发明人： M. Javid Hakim
IPC分类号： C23C16/32 , C23C16/34 , C23C16/36 , C23C16/448 , B32B15/04 , B32B19/00
CPC分类号： C23C16/36 , C23C16/32 , C23C16/34 , C23C16/4488 , Y10T428/31678
摘要： A process for the chemical vapor deposition on substrates of coatings comprising compounds of a titanium sub-group of metals, the vanadium sub-group of metals and the chromium sub-group of metals at temperatures in the range of 250.degree. C. is disclosed. Sub-halides, such as TiCl.sub.3, are reacted with N.sub.2 and H.sub.2 and thermodynamic and kinetic parameters are manipulated by flow rates and partial pressures of the reactants to achieve the deposition reaction in the temperature range of 250.degree. C. to 850.degree. C. The invention also relates to a metal compound coated article. An apparatus for performing the process is also disclosed.
摘要翻译：公开了一种在250℃的温度范围内化学气相沉积在包含金属钛族金属组分，金属钒族金属和金属铬金属组分的涂层基板上的方法。次卤化物如TiCl 3与N 2和H 2反应，热力学和动力学参数通过流速和反应物的分压来操纵，以在250℃至850℃的温度范围内实现沉积反应。本发明还涉及金属化合物涂层制品。还公开了一种用于执行该处理的装置。

14. 发明授权

US4699082A Apparatus for chemical vapor deposition 失效
标题翻译：化学气相沉积设备
公开(公告)号：US4699082A
公开(公告)日：1987-10-13
申请号：US864139
申请日：1986-05-16
申请人： M. Javid Hakim
发明人： M. Javid Hakim
IPC分类号： C23C16/32 , C23C16/34 , C23C16/36 , C23C16/448 , C23C16/00
CPC分类号： C23C16/32 , C23C16/34 , C23C16/36 , C23C16/4488
摘要： An apparatus for the chemical vapor deposition on substrates of coatings comprising compounds of a titanium sub-group of metals, the vanadium sub-group of metals and the chromium sub-group of metals at temperatures in the range of 250.degree. to 850.degree. C. is disclosed. Sub-halides, such as TiCl.sub.3, are reacted with N.sub.2 and H.sub.2 and thermodynamic and kinetic parameters are manipulated by flow rates and partial pressures of the reactants to achieve the deposition reaction in the temperature range of 250.degree. to 850.degree. C.
摘要翻译：一种用于化学气相沉积在包衣的基底上的装置，其包括金属钛亚属化合物，金属钒族金属和金属铬亚组，温度范围为250至850℃。被披露。次卤化物如TiCl 3与N 2和H 2反应，热力学和动力学参数通过流速和反应物的分压来操纵，以在250℃至850℃的温度范围内实现沉积反应。

15. 发明授权

US11180840B2 High gamma prime nickel based superalloy, its use, and method of manufacturing of turbine engine components 有权
公开(公告)号：US11180840B2
公开(公告)日：2021-11-23
申请号：US16249010
申请日：2019-01-16
申请人： Liburdi Engineering Limited
发明人： Alexander B. Goncharov , Joseph Liburdi , Paul Lowden
IPC分类号： C22C19/05 , C22F1/10 , B33Y10/00 , B33Y70/00 , B23K26/342 , B23K26/00 , B33Y80/00 , B23K101/00 , B23K103/08
摘要： The invention is related to a high gamma prim nickel based superalloy, its use and a method of manufacturing of turbine engine components by welding, 3D additive manufacturing, casting and hot forming, and the superalloy comprises 9.0-10.5 wt. % Cr, 20-22 wt. % Co, 1.0-1.4 wt. % Mo, 5.0-5.8 wt. % W, 2.0-6.0 wt. % Ta, 3.0-6.5 wt. % Al, 0.2-0.5 wt. % Hf, 0.01-0.16 wt. % C, 1.5-3.5 wt. % Re, 0-1.0 Ge wt. %, 0-0.2 wt. % Y, 0-1 wt. % Si, 0-0.015 wt. % B and nickel with impurities to balance.

16. 发明申请

US20210130932A1 HIGH GAMMA PRIME NICKEL BASED SUPERALLOY, ITS USE, AND METHOD OF MANUFACTURING OF TURBINE ENGINE COMPONENTS 有权
公开(公告)号：US20210130932A1
公开(公告)日：2021-05-06
申请号：US16744952
申请日：2020-01-16
申请人： Liburdi Engineering Limited
发明人： Alexander B. GONCHAROV , Joseph LIBURDI , Paul LOWDEN
IPC分类号： C22C19/05 , C22F1/10 , B33Y70/00
摘要： The specification relates to a high gamma prim nickel based superalloy, its use and a method of manufacturing of turbine engine components by welding, 3D additive manufacturing, casting and hot forming, and the superalloy comprises by wt %: from 9.0 to 10.5% Cr, from 16 to 22% Co, from 1.0 to 1.4% Mo, from 5.0 to 5.8% W, from 2.0 to 6.0% Ta, from 1.0 to 4.0% Nb provided that total content of Ta and Nb remains with a range from 3.0 to 7.0%, from 3.0 to 6.5% Al, from 0.2 to 1.5% Hf, from 0.01 to 0.2% C, from 0 to 1.0% Ge, from 0 to 1.0 wt. % Si, from 0 to 0.2 wt. % Y, from 0 to 0.015 wt. % B, from 1.5 to 3.5 wt. % Re, and nickel with impurities to balance.

17. 发明授权

US10384316B2 Method of repairing and manufacturing of turbine engine components and turbine engine component repaired or manufactured using the same 有权
公开(公告)号：US10384316B2
公开(公告)日：2019-08-20
申请号：US14964653
申请日：2015-12-10
申请人： Liburdi Engineering Limited
发明人： Alexander B Goncharov , Joseph Liburdi , Paul Lowden
IPC分类号： B23P6/00 , C22C19/05 , C22F1/10 , F01D5/14 , B23P15/02 , B23K9/04 , B23K9/167 , B23K9/235 , B23K10/02 , B23K15/00 , B23K26/34 , F01D5/00 , B23K101/00 , F01D5/28
摘要： Method of repairing and manufacturing of turbine engine components includes application of a transition layer by fusion welding with dissimilar nickel based filler material, preferably comprising from about 0.05 wt. % to about 1.2 wt. % B and other alloying elements, followed by a diffusion and primary aging heat treatment and application of the top oxidation resistance layer using dissimilar nickel based filler materials comprised 3-6 wt. % Al, 0.5-6 wt. % Si, 12-25 wt. % Cr and other alloying elements that enhance strength and oxidation resistance followed by a secondary aging heat treatment and machining of the repaired area to restore geometry of turbine engine components. The inventions also relates to a turbine engine components repaired and manufactured by the method.

18. 发明申请

US20140366996A1 METHOD OF CLADDING AND FUSION WELDING OF SUPERALLOYS 审中-公开
标题翻译：超级合金的焊接和熔融焊接方法
公开(公告)号：US20140366996A1
公开(公告)日：2014-12-18
申请号：US14468680
申请日：2014-08-26
申请人： Liburdi Engineering Limited
发明人： Alexander B. Goncharov , Joseph Liburdi , Paul Lowden , Scott Hastie
IPC分类号： B23K1/19 , B23K1/005 , B23K1/00
CPC分类号： B23K1/19 , B23K1/0018 , B23K1/005 , B23K1/0056 , B23K9/042 , B23K9/23 , B23K26/32 , B23K26/342 , B23K35/0244 , B23K35/22 , B23K35/30 , B23K35/3033 , B23K35/304 , B23K35/3046 , B23K2101/001 , B23K2103/02 , B23K2103/18 , B23K2103/26 , C21D9/50 , C22F1/10 , F01D5/005 , F05D2230/232 , F05D2300/13 , Y02T50/672
摘要： The present concept is a method of cladding and fusion welding of superalloys and includes the steps of firstly application of a composite filler powder that consists of 5-50% by weight brazing powder which includes melting point depressants, and 50-95% by weight high temperature welding powder, to a superalloy base material. Secondly there is simultaneous heating of the base material and the composite filler powder by a welding heat source that is movable relative to the base material. There is heating to a temperature that will fully melt the brazing powder and at least partially melt the high temperature welding powder and also melt a surface layer of the base material, thereby forming a weld pool. Thirdly upon solidification and cooling of the weld pool, there is coalescence between the weld bead and the base material.
摘要翻译：本发明的概念是一种超高温合金的熔敷和焊接方法，其中包括首先应用复合填料粉末的步骤，所述复合填料粉末由5-50重量％的包含熔点降低剂的钎焊粉末和50-95重量％温度焊接粉末，到超合金基材。其次，通过可相对于基材移动的焊接热源同时加热基材和复合填料粉末。加热至将使钎焊粉末完全熔化并至少部分熔化高温焊接粉末并且熔化基材表面层的温度，由此形成熔池。第三，在熔池凝固和冷却时，焊缝与基体材料之间存在聚结。

19. 发明申请

US20100173094A1 METHOD FOR MANUFACTURING AN ABRASIVE COATING ON A GAS TURBINE COMPANENT 有权
标题翻译：在燃气涡轮机上制造磨损涂层的方法
公开(公告)号：US20100173094A1
公开(公告)日：2010-07-08
申请号：US12451263
申请日：2007-05-04
申请人： Karl-Heinz Manier , Llya Chuprakov , Roberto Sparling
发明人： Karl-Heinz Manier , Llya Chuprakov , Roberto Sparling
IPC分类号： B05D1/38 , B05D3/02 , B05D3/06
CPC分类号： C23C24/10 , C23C30/00 , F01D5/288 , F05D2230/30 , F05D2230/40 , F05D2300/228 , F05D2300/2283
摘要： A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided.
摘要翻译：一种用于在燃气涡轮机部件，特别是在燃气涡轮转子叶片尖端上制造磨料涂层的方法，至少包括以下步骤：a）提供燃气轮机部件，特别是燃气轮机转子叶片; b）提供高温熔融合金粉末; c）提供磨料颗粒; d）提供低温熔融合金粉末; e）将至少所述高温熔融合金粉末和所述磨料颗粒共混以提供混合物; f）将所述低温熔融合金粉末和所述混合物施加到所述燃气轮机部件的区域，特别是所述涡轮转子叶片的尖端; g）将所述燃气轮机部件的所述区域局部加热至高于所述低温熔融合金粉末的熔点但低于所述高温熔融合金粉末的熔点的温度。

20. 发明公开

US20240124957A1 HIGH GAMMA PRIME NICKEL BASED WELDING MATERIAL FOR REPAIR AND 3D ADDITIVE MANUFACTURING OF TURBINE ENGINE COMPONENTS 审中-公开
公开(公告)号：US20240124957A1
公开(公告)日：2024-04-18
申请号：US17966965
申请日：2022-10-17
申请人： Liburdi Engineering Limited
发明人： Alexander B. GONCHAROV , Paul LOWDEN
IPC分类号： C22C19/05 , B23K35/30 , B33Y70/00
CPC分类号： C22C19/057 , B23K35/3033 , B33Y70/00 , C22C19/056 , B23K2101/001
摘要： The high gamma prime (γ′) nickel based welding material for repair and 3D additive manufacturing of turbine engine components containing from 9.0 to 11.0% Cr, from 16.0 to 24.0% Co, from 1.0 to 1.4% Mo, from 5.0 to 5.8% W, from 1.5 to 1.9% Ta, from 4.5 to 5.5 Al %, from 0.1 to 0.3% Hf, up to 0.02% B, from 0.05 to 0.12% C, from 0.2 to 0.8% Fe, from 1.5 to 2.5% Re, and nickel with impurities to balance.

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