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1. 发明授权

US08845283B2 Compressor blade with flexible tip elements and process therefor 有权
标题翻译：具有柔性尖端元件的压缩机叶片及其工艺
公开(公告)号：US08845283B2
公开(公告)日：2014-09-30
申请号：US12955009
申请日：2010-11-29
申请人： Ronald Ralph Cairo , Warren Arthur Nelson
发明人： Ronald Ralph Cairo , Warren Arthur Nelson
IPC分类号： F04D29/08 , F04D29/32 , F04D29/16 , F04D29/02
CPC分类号： F04D29/164 , F01D5/005 , F01D5/20 , F01D11/16 , F04D29/023 , F04D29/324 , F05D2230/237 , F05D2230/90 , F05D2240/56 , F05D2300/501 , Y10T29/49243 , Y10T29/49336
摘要： A compressor blade and process for inhibiting rub encounters between a blade tip of the blade and an interior surface of a case that surrounds the rotating hardware within a compressor section of a turbomachine. The compressor blade includes a cap that defines the blade tip at a radially outermost end of the blade, and a plurality of flexible elements extending from a surface of the cap that defines the blade tip. The flexible elements extend from the surface in a span-wise direction of the blade, and are operable to become rigid due to centrifugal stiffening at compressor operating speeds and, optionally, cut a groove the interior surface of the case.
摘要翻译：一种压缩机叶片和用于抑制叶片的叶片尖端与围绕涡轮机的压缩机部分内的旋转硬件的壳体的内表面之间的摩擦碰撞的方法。压缩机叶片包括在叶片的径向最外端限定叶片尖端的帽以及从盖的限定叶片尖端的表面延伸的多个柔性元件。柔性元件在叶片的跨度方向上从表面延伸，并且由于在压缩机工作速度下的离心加强而可操作以变得刚性，并且可选地，在壳体的内表面上切割凹槽。

2. 发明申请

US20120134786A1 COMPRESSOR BLADE WITH FLEXIBLE TIP ELEMENTS AND PROCESS THEREFOR 有权
标题翻译：压缩机叶片具有灵活的提示元素及其过程
公开(公告)号：US20120134786A1
公开(公告)日：2012-05-31
申请号：US12955009
申请日：2010-11-29
申请人： Ronald Ralph Cairo , Warren Arthur Nelson
发明人： Ronald Ralph Cairo , Warren Arthur Nelson
IPC分类号： F01D5/20 , B23P15/04
CPC分类号： F04D29/164 , F01D5/005 , F01D5/20 , F01D11/16 , F04D29/023 , F04D29/324 , F05D2230/237 , F05D2230/90 , F05D2240/56 , F05D2300/501 , Y10T29/49243 , Y10T29/49336
摘要： A compressor blade and process for inhibiting rub encounters between a blade tip of the blade and an interior surface of a case that surrounds the rotating hardware within a compressor section of a turbomachine. The compressor blade includes a cap that defines the blade tip at a radially outermost end of the blade, and a plurality of flexible elements extending from a surface of the cap that defines the blade tip. The flexible elements extend from the surface in a span-wise direction of the blade, and are operable to become rigid due to centrifugal stiffening at compressor operating speeds and, optionally, cut a groove the interior surface of the case.
摘要翻译：一种压缩机叶片和用于抑制叶片的叶片尖端与围绕涡轮机的压缩机部分内的旋转硬件的壳体的内表面之间的摩擦碰撞的方法。压缩机叶片包括在叶片的径向最外端限定叶片尖端的帽以及从盖的限定叶片尖端的表面延伸的多个柔性元件。柔性元件在叶片的跨度方向上从表面延伸，并且由于在压缩机工作速度下的离心加强而可操作以变得刚性，并且可选地，在壳体的内表面上切割凹槽。

3. 发明授权

US08727831B2 Method and system for machining a profile pattern in ceramic coating 有权
标题翻译：在陶瓷涂层中加工型材图案的方法和系统
公开(公告)号：US08727831B2
公开(公告)日：2014-05-20
申请号：US12140581
申请日：2008-06-17
申请人： Warren Arthur Nelson , Donald Joseph Baldwin , Lyle B. Spiegel , James Edward Viggiani
发明人： Warren Arthur Nelson , Donald Joseph Baldwin , Lyle B. Spiegel , James Edward Viggiani
IPC分类号： B24C1/04
CPC分类号： C23C4/18 , F05B2230/90
摘要： A method of machining a profile pattern in a ceramic coating of a turbine shroud is provided and includes applying the ceramic coating substantially uniformly onto the turbine shroud, positioning a machining tool proximate the ceramic coating, and removing material from the ceramic coating by activating the machining tool to machine the ceramic coating and by moving the machining tool across the ceramic coating in a movement pattern that generally corresponds to the profile pattern.
摘要翻译：提供了一种在涡轮机护罩的陶瓷涂层中加工轮廓图案的方法，包括将陶瓷涂层基本上均匀地涂覆到涡轮机护罩上，将加工工具定位在陶瓷涂层附近，以及通过激活加工从陶瓷涂层移除材料用于加工陶瓷涂层的工具，并且以通常对应于轮廓图案的移动图案移动加工工具穿过陶瓷涂层。

4. 发明授权

US07431566B2 Erosion resistant coatings and methods thereof 有权
标题翻译：耐腐蚀涂层及其方法
公开(公告)号：US07431566B2
公开(公告)日：2008-10-07
申请号：US11546861
申请日：2006-10-12
申请人： Dennis Michael Gray , Krishnamurthy Anand , Warren Arthur Nelson , Hans Aunemo , Alain Demers , Olav Rommetveit
发明人： Dennis Michael Gray , Krishnamurthy Anand , Warren Arthur Nelson , Hans Aunemo , Alain Demers , Olav Rommetveit
IPC分类号： F03B3/06
CPC分类号： C23C30/00 , C23C4/06 , C23C4/129 , C23C24/04 , Y10T428/25 , Y10T428/252 , Y10T428/263
摘要： Erosion resistant coating processes and material improvements for line-of-sight applications. The erosion resistant coating composition includes nanostructured grains of tungsten carbide (WC) and/or submicron sized grains of WC embedded into a cobalt chromium (CoCr) binder matrix. A high velocity air fuel thermal spray process (HVAF) is used to create thick coatings in excess of about 500 microns with high percentages of primary carbide for longer life better erosion resistant coatings. These materials and processes are especially suited for hydroelectric turbine components.
摘要翻译：防腐涂层工艺和视线应用的材料改进。抗侵蚀涂层组合物包括嵌入钴铬（CoCr）粘合剂基质中的碳化钨（WC）和/或亚微米尺寸的WC颗粒的纳米结晶颗粒。高速空气燃料热喷涂工艺（HVAF）用于产生超过约500微米的厚涂层，高百分比的一次碳化物可使更长寿命更好的抗侵蚀涂层。这些材料和工艺特别适用于水力发电机组件。

5. 发明申请

US20100081009A1 Spray Application of Liquid Precursors for CMAS Resistant Coatings 审中-公开
标题翻译：液体前体喷雾应用于CMAS耐腐蚀涂料
公开(公告)号：US20100081009A1
公开(公告)日：2010-04-01
申请号：US12239629
申请日：2008-09-26
申请人： Warren Arthur Nelson , David Vincent Bucci , David Forrest Dye , Anthony W. Reynolds
发明人： Warren Arthur Nelson , David Vincent Bucci , David Forrest Dye , Anthony W. Reynolds
IPC分类号： C23C4/10 , C23C4/18 , B32B9/00 , B05C5/00
CPC分类号： C23C8/02 , C23C4/123 , C23C4/18 , C23C26/00 , C23C28/042 , Y02T50/67 , Y02T50/6765
摘要： Methods and systems of applying a liquid precursor for a calcium-magnesium-aluminosilicate (CMAS) resistant coating to a turbine engine component are provided. In one embodiment, a method of manufacturing a turbine engine includes spraying a liquid compound, wherein the liquid component is stored with a carrier gas, applying the compound to a component of a turbine engine, such that the compound is disposed on a thermal barrier coating of the component, and forming an oxide layer on the thermal barrier coating of the component. In another embodiment, a system includes a turbine engine component and a sprayer containing a compound and a carrier gas, wherein the sprayer is configured to apply the compound to a thermal barrier coating of the component such that the compound forms an oxide on the thermal barrier coating.
摘要翻译：提供了将用于钙镁镁硅酸盐（CMAS）抗性涂层的液体前体施加到涡轮发动机部件的方法和系统。在一个实施例中，一种制造涡轮发动机的方法包括喷射液体化合物，其中液体组分与载气一起储存，将该化合物施加到涡轮发动机的部件上，使得化合物设置在热障涂层的组分，并在组件的热障涂层上形成氧化物层。在另一个实施方案中，系统包括涡轮发动机部件和含有化合物和载体气体的喷雾器，其中所述喷雾器被配置为将所述化合物施加到所述部件的热障涂层上，使得所述化合物在所述热障壁上形成氧化物涂层。

6. 发明申请

US20090311416A1 METHOD AND SYSTEM FOR MACHINING A PROFILE PATTERN IN CERAMIC COATING 有权
标题翻译：用于加工陶瓷涂层中的型材图案的方法和系统
公开(公告)号：US20090311416A1
公开(公告)日：2009-12-17
申请号：US12140581
申请日：2008-06-17
申请人： Warren Arthur Nelson , Lyle B. Spiegel
发明人： Warren Arthur Nelson , Lyle B. Spiegel
IPC分类号： B05D7/00 , B05D3/00 , B05C21/00 , B05D1/08
CPC分类号： C23C4/18 , F05B2230/90
摘要： A method of machining a profile pattern in a ceramic coating of a turbine shroud is provided and includes applying the ceramic coating substantially uniformly onto the turbine shroud, positioning a machining tool proximate the ceramic coating, and removing material from the ceramic coating by activating the machining tool to machine the ceramic coating and by moving the machining tool across the ceramic coating in a movement pattern that generally corresponds to the profile pattern.
摘要翻译：提供了一种在涡轮机护罩的陶瓷涂层中加工轮廓图案的方法，包括将陶瓷涂层基本上均匀地涂覆到涡轮机护罩上，将加工工具定位在陶瓷涂层附近，以及通过激活加工从陶瓷涂层移除材料用于加工陶瓷涂层的工具，并且以通常对应于轮廓图案的移动图案移动加工工具穿过陶瓷涂层。

7. 发明授权

US07150921B2 Bi-layer HVOF coating with controlled porosity for use in thermal barrier coatings 失效
标题翻译：双层HVOF涂层，具有受控孔隙度，用于热障涂层
公开(公告)号：US07150921B2
公开(公告)日：2006-12-19
申请号：US10847357
申请日：2004-05-18
申请人： Warren Arthur Nelson , Jon Conrad Schaeffer , Sharon Trombly Swede , David Vincent Bucci , Joseph Debarro , Terry Howard Strout , Tyrone Robert Mortensen
发明人： Warren Arthur Nelson , Jon Conrad Schaeffer , Sharon Trombly Swede , David Vincent Bucci , Joseph Debarro , Terry Howard Strout , Tyrone Robert Mortensen
IPC分类号： B32B15/04 , B32B15/09 , B32B15/20 , C23C4/06 , C23C4/18
CPC分类号： C23C28/325 , C23C4/18 , C23C26/00 , C23C28/3215 , C23C28/3455 , Y02T50/67 , Y10T428/12479 , Y10T428/12569 , Y10T428/12611 , Y10T428/12736 , Y10T428/12847 , Y10T428/26 , Y10T428/263 , Y10T428/31681
摘要： A bi-layer bond coating for use on metal alloy components exposed to hostile thermal and chemical environment, such as a gas turbine engine, and the method for applying such coatings. The preferred coatings include a bi-layer bond coat applied to the metal substrate using high velocity oxy-fuel (HVOF) thermal spraying. Bi-layer bond coatings in accordance with the invention consist of a dense first inner layer (such as iron, nickel or cobalt-based alloys) that provides oxidation protection to the metal substrate, and a second outer layer having controlled porosity that tends to promote roughness, mechanical compliance, and promotes adherence of the thermal barrier coating (TBC). Preferably, the outer, less dense layer of the bi-layer bond coat is formed from a mixture of metallic powder and polyester to adjust and control the porosity, but without sacrificing mechanical compliance.
摘要翻译：用于暴露于恶劣的热和化学环境的金属合金组分（例如燃气涡轮发动机）上的双层粘合涂层以及用于涂覆这种涂层的方法。优选的涂层包括使用高速氧 - 燃料（HVOF）热喷涂施加到金属基底的双层粘合涂层。根据本发明的双层粘合涂层由致密的第一内层（例如铁，镍或钴基合金）组成，其向金属基底提供氧化保护，以及具有趋向促进的受控孔隙率的第二外层粗糙度，机械柔顺性，并促进热障涂层（TBC）的粘附。优选地，双层粘合涂层的外部，较不致密的层由金属粉末和聚酯的混合物形成，以调节和控制孔隙率，但不牺牲机械顺应性。

8. 发明授权

US06306517B1 Thermal barrier coatings having an improved columnar microstructure 失效
标题翻译：具有改进的柱状微观结构的热障涂层
公开(公告)号：US06306517B1
公开(公告)日：2001-10-23
申请号：US09632354
申请日：2000-08-03
申请人： Dennis Michael Gray , Yuk-Chiu Lau , Curtis Alan Johnson , Marcus Preston Borom , Warren Arthur Nelson
发明人： Dennis Michael Gray , Yuk-Chiu Lau , Curtis Alan Johnson , Marcus Preston Borom , Warren Arthur Nelson
IPC分类号： B32B900
CPC分类号： C23C4/12 , C23C4/02 , C23C4/134
摘要： An article having a spallation resistant TBC comprises a metal substrate, such as a high temperature superalloy, and a TBC, such as a coating of yttria stabilized zirconia. The TBC comprises a plurality of plasma-sprayed layers. The TBC has a coherent, continuous columnar grain microstructure, wherein at least one layer has a plurality of continuous columnar grains which have been extended by directional solidification into an adjacent layer.
摘要翻译：具有抗剥落TBC的制品包括金属基底，例如高温超合金，以及TBC，例如氧化钇稳定的氧化锆的涂层。 TBC包括多个等离子体喷涂层。 TBC具有连续的连续的柱状晶粒微观结构，其中至少一层具有多个通过定向凝固延伸到相邻层中的连续柱状晶粒。

9. 发明授权

US06294261B1 Method for smoothing the surface of a protective coating 失效
标题翻译：保护涂层表面光滑的方法
公开(公告)号：US06294261B1
公开(公告)日：2001-09-25
申请号：US09409878
申请日：1999-10-01
申请人： D. Sangeeta , Curtis Alan Johnson , Warren Arthur Nelson
发明人： D. Sangeeta , Curtis Alan Johnson , Warren Arthur Nelson
IPC分类号： B32B900
CPC分类号： C23C26/00 , C23C4/18 , C23C10/18 , C23C24/10 , C23C28/3215 , C23C28/324 , C23C28/3455 , C23C28/36 , F05B2250/62 , Y02T50/67
摘要： A method for smoothing the surface of a ceramic-based protective coating which exhibits roughness is disclosed. The method includes the steps of applying a ceramic-based slurry or gel coating to the protective coating surface; heating the slurry/gel coating to remove volatile material; and then further heating the slurry/gel coating to cure the coating and bond it to the underlying protective coating. The slurry/gel coating is often based on yttria-stabilized zirconia, and precursors of an oxide matrix. Related articles of manufacture are also described.
摘要翻译：公开了一种平滑表面粗糙度的陶瓷基保护涂层表面的方法。该方法包括以下步骤：将陶瓷基浆料或凝胶涂层施加到保护涂层表面; 加热浆料/凝胶涂层以除去挥发性物质; 然后进一步加热浆料/凝胶涂层以固化涂层并将其粘合到下面的保护涂层上。浆料/凝胶涂层通常基于氧化钇稳定的氧化锆和氧化物基质的前体。还描述了相关的制造方法。

10. 发明授权

US07614847B2 Pattern for the surface of a turbine shroud 有权
标题翻译：涡轮机护罩表面的图案
公开(公告)号：US07614847B2
公开(公告)日：2009-11-10
申请号：US10996878
申请日：2004-11-24
申请人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter Mcgovern
发明人： Warren Arthur Nelson , Brian Peter Arness , Paul Thomas Marks , Raymond Edward Chupp , Tara Easter Mcgovern
IPC分类号： F01D11/12
CPC分类号： F01D11/12 , F01D11/122
摘要： A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.
摘要翻译：用于改善涡轮机的空气动力学性能的模式包括在涡轮机护罩的基面处以图案设置的材料，使得该材料能够与涡轮机桶的尖端部分磨损接触。该图案包括设置在基部表面处的第一多个脊，使得对应于涡轮机桶的后部的第一多个脊的第一部分相对于涡轮叶片的旋转轴线以第一角度定向。第一多个脊中的每个脊具有第一侧壁和具有第一端和第二端的第二侧壁。第一和第二侧壁的第一端从基面延伸。第一和第二侧壁彼此相对倾斜，具有基本上相等但相反的斜面，直到在相应的第一和第二侧壁的第二端处共同限定脊的中心线和顶部。

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