公开(公告)号：US20140024254A1

公开(公告)日：2014-01-23

申请号：US14035872

申请日：2013-09-24

申请人： Robert Chastain ,  Charles D. Davidson, JR. ,  Joshua Blake ,  Yiping Hu

发明人： Robert Chastain ,  Charles D. Davidson, JR. ,  Joshua Blake ,  Yiping Hu

IPC分类号： H01R9/05

CPC分类号： H01R9/0521 ,  H01R13/035 ,  H01R13/5202

摘要： A coaxial cable connector including a body circuit borne by a non-conducting body substrate.

摘要翻译： 一种同轴电缆连接器，包括由不导电的主体基板承载的主体电路。

公开(公告)号：US20120048912A1

公开(公告)日：2012-03-01

申请号：US12869464

申请日：2010-08-26

申请人： Yiping Hu ,  Richard L. Bye

发明人： Yiping Hu ,  Richard L. Bye

IPC分类号： B23K31/02

CPC分类号： F01D5/288 ,  F01D5/005 ,  F05D2230/31 ,  F05D2230/80 ,  F05D2230/90

摘要： Embodiments of a method for forming an MCrAlY coating on a gas turbine engine component are provided, as are embodiments of a method for repairing a structurally-damaged region of a gas turbine engine component utilizing an MCrAlY material. In one embodiment, the method includes the step of preparing an MCrAlY slurry containing an MCrAlY powder, a low melting point powder, a binder, and a dilutant. After application over the gas turbine engine component, the MCrAlY slurry is heated to a predetermined temperature that exceeds the melting point of the low melting point powder to form an MCrAlY coating on the gas turbine engine component. The MCrAlY powder may have any one of a number of different compositions.

摘要翻译： 提供了一种用于在燃气涡轮发动机部件上形成MCrAlY涂层的方法的实施例，其中使用MCrAlY材料修复燃气涡轮发动机部件的结构受损区域的方法的实施例。 在一个实施方案中，该方法包括制备含有MCrAlY粉末，低熔点粉末，粘合剂和稀释剂的MCrAlY浆料的步骤。 在施加在燃气涡轮发动机部件上之后，将MCrAlY浆料加热到超过低熔点粉末的熔点的预定温度，以在燃气涡轮发动机部件上形成MCrAlY涂层。 MCrAlY粉末可以具有多种不同组合物中的任何一种。

公开(公告)号：US20110135952A1

公开(公告)日：2011-06-09

申请号：US12631285

申请日：2009-12-04

申请人： Mark C. Morris ,  Tom Strangman ,  Yiping Hu

发明人： Mark C. Morris ,  Tom Strangman ,  Yiping Hu

IPC分类号： B32B15/02 ,  B22F7/02

CPC分类号： B22F5/009 ,  B22F3/1055 ,  B22F7/08 ,  C30B13/00 ,  C30B29/52 ,  Y02P10/295 ,  Y10T428/12028

摘要： A method is provided that includes depositing metal powder over a seed crystal having a predetermined primary orientation, scanning an initial pattern into the metal powder to melt or sinter the deposited metal powder, and re-scanning the initial pattern to re-melt the scanned metal powder and form an initial layer having the predetermined primary orientation. The method further includes depositing additional metal powder over the initial layer, scanning an additional pattern into the additional metal powder to melt or sinter at least a portion of the additional metal powder, re-scanning the additional pattern to re-melt a portion of the initial layer and the scanned deposited additional metal powder to form a successive layer having the predetermined primary orientation, and repeating the steps of depositing additional metal powder, scanning the additional pattern, and re-scanning the additional pattern, until a final shape of the component is achieved.

摘要翻译： 提供了一种方法，其包括将金属粉末沉积在具有预定主要取向的晶种上，将初始图案扫描到金属粉末中以熔化或烧结沉积的金属粉末，并重新扫描初始图案以重新熔化扫描的金属 并形成具有预定主要取向的初始层。 该方法还包括在初始层上沉积额外的金属粉末，将另外的图案扫描到附加金属粉末中以熔化或烧结至少一部分附加金属粉末，重新扫描附加图案以重新熔化部分 初始层和扫描的沉积的另外的金属粉末以形成具有预定主要取向的连续层，并且重复沉积额外的金属粉末，扫描附加图案和重新扫描附加图案的步骤，直到组件的最终形状 已完成。

公开(公告)号：US07824510B2

公开(公告)日：2010-11-02

申请号：US12020917

申请日：2008-01-28

申请人： Yiping Hu ,  Timothy Hudson ,  Eric Reinholz ,  Calum Macintyre

发明人： Yiping Hu ,  Timothy Hudson ,  Eric Reinholz ,  Calum Macintyre

IPC分类号： B23K31/00

CPC分类号： B23K35/3033 ,  B23K2101/001 ,  B23K2103/26 ,  B23P6/007

摘要： Methods are provided for repairing an engine component. In an embodiment, a method includes forming at least one layer of a first braze alloy mixture including about 40% by weight of a first base alloy material and about 60% by weight of a first braze alloy material, over a structural feature of the component. The first braze alloy material includes chromium, cobalt, tungsten, tantalum, aluminum, hafnium, carbon, boron, and a balance of nickel. A second braze alloy mixture is disposed over the at least one layer of the first braze alloy mixture, the second braze alloy mixture including between about 50% and about 60% by weight of a second base alloy material, and between about 40% and about 50% by weight of a second braze alloy material. The component is then subjected to heat treatment, and may be further subjected to machining, coating and final inspection.

摘要翻译： 提供了修理发动机部件的方法。 在一个实施方案中，一种方法包括在该组分的结构特征上形成至少一层包含约40重量％的第一基础合金材料和约60重量％的第一钎焊合金材料的第一钎焊合金混合物 。 第一钎焊合金材料包括铬，钴，钨，钽，铝，铪，碳，硼和余量的镍。 第二钎焊合金混合物设置在第一钎焊合金混合物的至少一层上，第二钎焊合金混合物包含约50重量％至约60重量％的第二基础合金材料，以及约40重量％至约60重量％ 50重量％的第二钎焊合金材料。 然后对该部件进行热处理，并且可以进一步进行机械加工，涂覆和最终检查。

公开(公告)号：US20100266772A1

公开(公告)日：2010-10-21

申请号：US12426595

申请日：2009-04-20

申请人： Yiping Hu

发明人： Yiping Hu

IPC分类号： B05D3/02

CPC分类号： C23C26/00 ,  B23K20/02 ,  B23K20/233 ,  B23K2101/001 ,  C22C19/05 ,  C22C19/057 ,  C22F1/10 ,  C23C10/02 ,  C23C28/321 ,  C23C28/322 ,  C23C28/3455 ,  C23C28/36 ,  Y02T50/67 ,  Y02T50/6765

摘要： Methods are provided for forming coating systems on advanced single crystal superalloy turbine airfoils. A method includes applying a layer of an additive material onto a substrate, the additive material comprising a precious metal and the substrate comprising a nickel-based superalloy, diffusion heat treating the substrate to form an intermetallic coating which comprises γ-Ni and γ′-Ni3Al phases alloyed with the additive material and one or more reactive elements from the substrate including hafnium, yttrium, chromium, and silicon, and finally depositing a thermal barrier coating over the intermetallic coating to form the coating system.

摘要翻译： 提供了用于在高级单晶超级合金涡轮机翼型上形成涂层系统的方法。 一种方法包括将一层添加剂材料施加到基底上，所述添加剂材料包含贵金属，所述基底包括镍基超合金，对所述基底进行扩散热处理以形成金属间涂层，其包括γ-Ni和γ'- 与添加剂材料合金化的Ni 3 Al相和来自基底的一种或多种反应性元素包括铪，钇，铬和硅，并最终在金属间涂层上沉积热障涂层以形成涂层体系。

公开(公告)号：US20090280023A1

公开(公告)日：2009-11-12

申请号：US12115888

申请日：2008-05-06

申请人： Yiping Hu

发明人： Yiping Hu

IPC分类号： C22C19/05 ,  B23K31/02

CPC分类号： B23K1/0018 ,  C22C19/056 ,  C22C19/058

摘要： Intermetallic braze alloys and methods of repairing an engine component are provided. In an embodiment, by way of example only, an intermetallic braze material includes between about 10% to about 15% chromium, by weight, between about 1% to about 3% aluminum, by weight, between about 0.1% to about 0.5% zirconium, by weight, between about 18% to about 25% hafnium, by weight, and a balance of nickel. In another embodiment, by way of example only, an intermetallic braze material includes between about 10% to about 15% chromium, by weight, between about 1% to about 3% aluminum, by weight, between about 10% to about 13% zirconium, by weight, between about 0.3% to about 0.7% hafnium, by weight, and a balance of nickel.

摘要翻译： 提供金属间钎焊合金和修理发动机部件的方法。 在一个实施方案中，仅作为示例，金属间钎焊材料包括约10％至约15％的铬，重量比，约1％至约3％的铝，重量百分比，约0.1％至约0.5％的锆 ，重量百分比为约18％至约25％的铪，余量为镍。 在另一个实施例中，仅作为示例，金属间钎焊材料包括约10％至约15％的铬，重量比，约1％至约3％的铝，重量比，约10％至约13％的锆 ，重量百分比为约0.3％至约0.7％的铪，余量为镍。

公开(公告)号：US20080131612A1

公开(公告)日：2008-06-05

申请号：US11606544

申请日：2006-11-30

申请人： Yiping Hu ,  Derek Raybould

发明人： Yiping Hu ,  Derek Raybould

IPC分类号： B05D1/36 ,  B05D3/02 ,  B05D3/12 ,  C23C14/30 ,  C23C4/10

CPC分类号： B24C1/10 ,  C23C4/134 ,  C23C14/024 ,  C23C14/30 ,  C23C14/5806 ,  C23C24/04 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  Y02T50/67 ,  Y02T50/6765

摘要： Methods are provided for forming a coating system on a gas turbine component. In one embodiment, and by way of example only, the method includes cold spraying a material onto the component surface to form an overlay coating, the material comprising MCrAlY, wherein M comprises a constituent selected from the group consisting of Ni, Co, or Fe, or combinations of Ni, Co, and Fe. Then, the overlay coating is heat treated. The overlay coating is then shot peened and vibro polished. A thermal barrier coating is then applied onto the overlay coating to form the coating system via air plasma spaying or electron beam physical vapor deposition technique.

摘要翻译： 提供了用于在燃气轮机部件上形成涂覆系统的方法。 在一个实施例中，仅作为示例，该方法包括将材料冷喷涂到部件表面上以形成覆盖涂层，该材料包含MCrAlY，其中M包含选自Ni，Co或Fe ，或Ni，Co和Fe的组合。 然后，对覆盖层进行热处理。 然后将覆盖涂层喷丸硬化并振动抛光。 然后将热障涂层施加到覆盖涂层上，以通过空气等离子体喷涂或电子束物理气相沉积技术形成涂层体系。

公开(公告)号：US20060219330A1

公开(公告)日：2006-10-05

申请号：US11093583

申请日：2005-03-29

申请人： Yiping Hu ,  Richard Bye

发明人： Yiping Hu ,  Richard Bye

IPC分类号： C22C19/05 ,  C22F1/10

CPC分类号： C22C19/057

摘要： A nickel-based superalloy includes, in terms of weight, in terms of weight, about 0.08% to about 0.12% carbon, about 6.0% to about 6.4% aluminum, about 5.8% to about 6.3% tantalum, about 6.5% to about 7.0% chromium, about 9.3% to about 9.8% cobalt, about 1.3% to about 1.7% molybdenum, about 2.4% to about 2.8% rhenium, about 3.8% to about 4.3% tungsten, about 0.9% to about 1.3% hafnium, about 0.01% to about 0.03% zirconium, up to about 0.10% silicon, and nickel. A method for repairing a surface of a turbine component includes the step of applying the nickel-based superalloy to a damaged area of the component surface, and post-deposition processes.

摘要翻译： 镍基超级合金以重量计，包括约0.08％至约0.12％的碳，约6.0％至约6.4％的铝，约5.8％至约6.3％的钽，约6.5％至约7.0的重量， 约9.3％至约9.8％的钴，约1.3％至约1.7％的钼，约2.4％至约2.8％的铼，约3.8％至约4.3％的钨，约0.9％至约1.3％的铪，约0.01 ％至约0.03％的锆，至多约0.10％的硅和镍。 用于修复涡轮机部件的表面的方法包括将镍基超级合金施加到部件表面的损坏区域和后沉积工艺的步骤。

公开(公告)号：US20060219329A1

公开(公告)日：2006-10-05

申请号：US11093350

申请日：2005-03-29

申请人： Yiping Hu ,  Richard Bye

发明人： Yiping Hu ,  Richard Bye

IPC分类号： C22C19/05 ,  C22F1/10

CPC分类号： C22F1/10

摘要： A nickel-based superalloy includes, in terms of weight, about 0.06% to about 0.10% carbon, about 6.0% to about 6.4% aluminum, about 5.8% to about 6.3% tantalum, about 6.5% to about 7.0% chromium, about 8.8% to about 9.3% cobalt, about 0.6% to about 1.0% molybdenum, about 2.4% to about 2.8% rhenium, about 4.8% to about 5.3% tungsten, about 0.3% to about 0.80% hafnium, about 0.01% to about 0.03% zirconium, about 0.10% to about 0.18% silicon, and nickel. A method for repairing a surface of a turbine component includes the step of applying the nickel-based superalloy to a damaged area of the component surface. Post-deposition processes are also performed as necessary.

摘要翻译： 镍基超级合金的重量计包括约0.06％至约0.10％的碳，约6.0％至约6.4％的铝，约5.8％至约6.3％的钽，约6.5％至约7.0％的铬，约8.8 约9.3％至约0.98％的钴，约0.6％至约1.0％的钼，约2.4％至约2.8％的铼，约4.8％至约5.3％的钨，约0.3％至约0.80％的铪，约0.01％至约0.03％ 锆，约0.10％至约0.18％的硅和镍。 用于修复涡轮机部件的表面的方法包括将镍基超级合金应用于部件表面的损坏区域的步骤。 还需要进行沉积后处理。

公开(公告)号：US20060045785A1

公开(公告)日：2006-03-02

申请号：US10930506

申请日：2004-08-30

申请人： Yiping Hu ,  Federico Renteria ,  Christopher Cahoon ,  Margaret Floyd

发明人： Yiping Hu ,  Federico Renteria ,  Christopher Cahoon ,  Margaret Floyd

IPC分类号： B22F7/04

CPC分类号： B23P6/007 ,  C23C24/04 ,  F01D5/005 ,  Y10T29/49318

摘要： A method for repairing a titanium alloy surface of a turbine component includes the step of cold gas-dynamic spraying a powder material comprising at least one titanium alloy directly on the titanium alloy surface. The method may further include the steps of hot isostatic pressing the cold gas-dynamic sprayed turbine component, and performing a separate heat treating step after the hot isostatic pressing. Thus, the cold gas-dynamic spray process and post-spray processing can be employed to effectively repair degraded areas on compressor turbine components.

摘要翻译： 一种用于修复涡轮机部件的钛合金表面的方法包括将包含至少一种钛合金的粉末材料直接在钛合金表面上进行冷气动态喷射的步骤。 该方法可以进一步包括热等静压式冷气动喷射涡轮机部件的步骤，以及在热等静压之后执行单独的热处理步骤。 因此，可以采用冷气体动态喷雾处理和后喷雾处理来有效地修复压缩机涡轮机部件的退化区域。