专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US07294413B2 Substrate protected by superalloy bond coat system and microcracked thermal barrier coating 有权
标题翻译：基体由超合金粘结涂层体系和微裂纹热障涂层保护
公开(公告)号：US07294413B2
公开(公告)日：2007-11-13
申请号：US11073529
申请日：2005-03-07
申请人： Bangalore Aswatha Nagaraj , D. Keith Patrick , Thomas John Tomlinson , David Walter Parry
发明人： Bangalore Aswatha Nagaraj , D. Keith Patrick , Thomas John Tomlinson , David Walter Parry
IPC分类号： B32B15/04 , B32B15/20 , C23C14/00 , B05D1/02 , F01D5/28
CPC分类号： C23C4/08 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , Y02T50/67 , Y10T428/12611 , Y10T428/12618 , Y10T428/1275 , Y10T428/12944
摘要： A protected article includes a substrate having a surface, and a protective system overlying and contacting a first portion of the surface of the substrate. The protective system has a nickel-base superalloy bond coat, an aluminide layer overlying and contacting the bond coat, and a dense vertically microcracked ceramic thermal barrier coating overlying and contacting the aluminide layer.
摘要翻译：受保护制品包括具有表面的基底和覆盖和接触基底表面的第一部分的保护系统。保护系统具有镍基超合金粘合涂层，覆盖并接触粘合涂层的铝化物层，以及覆盖并接触铝化物层的致密的垂直微裂纹陶瓷热障涂层。

2. 发明授权

US07094450B2 Method for applying or repairing thermal barrier coatings 有权
标题翻译：涂覆或修复热障涂层的方法
公开(公告)号：US07094450B2
公开(公告)日：2006-08-22
申请号：US10426280
申请日：2003-04-30
申请人： Bangalore Aswatha Nagaraj , Eva Zielonka Lanman , Deborah Anne Schorr , Thomas John Tomlinson , Raymond William Heidorn , David Allen Kastrup , Craig Douglas Young
发明人： Bangalore Aswatha Nagaraj , Eva Zielonka Lanman , Deborah Anne Schorr , Thomas John Tomlinson , Raymond William Heidorn , David Allen Kastrup , Craig Douglas Young
IPC分类号： C23C4/06 , C23C4/10
CPC分类号： C23C4/00 , C23C4/02 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C28/36 , F01D5/005 , F01D5/288 , F05D2230/312 , Y10T29/49318 , Y10T428/12618 , Y10T428/12736
摘要： A method applying a thermal barrier coating to a metal substrate, or for repairing a thermal barrier coating previously applied by physical vapor deposition to an underlying aluminide diffusion coating that overlays the metal substrate. The aluminide diffusion coating is treated to make it more receptive to adherence of a plasma spray-applied overlay alloy bond coat layer. An overlay alloy bond coat material is then plasma sprayed on the treated aluminide diffusion coating to form an overlay alloy bond coat layer. A ceramic thermal barrier coating material is plasma sprayed on the overlay alloy bond coat layer to form the thermal barrier coating. In the repair embodiment of this method, the physical vapor deposition-applied thermal barrier coating is initially removed from the underlying aluminide diffusion coating.
摘要翻译：将热障涂层施加到金属基底上的方法，或者将先前通过物理气相沉积施加的热障涂层修复到覆盖金属基底的下面的铝化物扩散涂层。处理铝化物扩散涂层以使其更容易接受等离子体喷涂覆盖合金粘合涂层的粘附。然后将覆盖合金粘合涂层材料等离子体喷涂在经处理的铝化物扩散涂层上以形成覆盖合金粘合涂层。将陶瓷热障涂层材料等离子体喷涂在覆盖合金粘合涂层上以形成热障涂层。在该方法的修复实施例中，首先从下面的铝化物扩散涂层去除物理气相沉积涂覆的热障涂层。

3. 发明授权

US09023486B2 Thermal barrier coating systems and processes therefor 有权
标题翻译：热障涂层系统及其工艺
公开(公告)号：US09023486B2
公开(公告)日：2015-05-05
申请号：US13341247
申请日：2011-12-30
申请人： Bangalore Aswatha Nagaraj , Thomas John Tomlinson
发明人： Bangalore Aswatha Nagaraj , Thomas John Tomlinson
IPC分类号： B32B18/00 , C23C4/18 , C23C4/04 , B32B15/04 , C23C4/12 , C23C4/10 , C04B35/486 , C04B35/505 , C23C4/02 , C23C28/00
CPC分类号： C23C4/105 , C04B35/486 , C04B35/505 , C04B2235/3225 , C04B2235/3244 , C04B2235/76 , C23C4/02 , C23C4/11 , C23C4/18 , C23C28/3215 , C23C28/3455 , Y10T428/12549 , Y10T428/12618 , Y10T428/2495
摘要： Coating systems and processes by which the coating systems can be deposited to be resistant to contaminants, and particularly resistant to infiltration and damage caused by CMAS. The coating systems include inner and outer ceramic layers, each having a microstructure characterized by splats and horizontal porosity. The inner ceramic layer consists essentially of zirconia stabilized by about 6 to about 9 weight percent yttria. The outer ceramic layer overlies and contacts the inner ceramic layer to define the outermost surface of the coating system. The outer ceramic layer consists essentially of zirconia stabilized by about 25 to about 75 weight percent yttria, has a thickness that is less than the thickness of the inner ceramic layer, and has a porosity level that is lower than that of the inner ceramic layer.
摘要翻译：可以将涂层系统沉积以抵抗污染物，特别是对由CMAS引起的渗透和损害的涂层系统和工艺。涂覆系统包括内部和外部陶瓷层，每个具有由splats和水平孔隙度表征的微观结构。内部陶瓷层主要由由约6至约9重量％的氧化钇稳定的氧化锆组成。外陶瓷层覆盖并接触内陶瓷层以限定涂层系统的最外表面。外部陶瓷层主要由由约25至约75重量％的氧化钇稳定的氧化锆组成，其厚度小于内部陶瓷层的厚度，并且具有低于内部陶瓷层的厚度的孔隙率水平。

4. 发明申请

US20130095344A1 THERMAL BARRIER COATING SYSTEMS AND PROCESSES THEREFOR 有权
标题翻译：热障涂层系统及其工艺
公开(公告)号：US20130095344A1
公开(公告)日：2013-04-18
申请号：US13341247
申请日：2011-12-30
申请人： Bangalore Aswatha Nagaraj , Thomas John Tomlinson
发明人： Bangalore Aswatha Nagaraj , Thomas John Tomlinson
IPC分类号： B32B18/00 , C23C4/18 , C23C4/04 , B32B15/04 , C23C4/12
CPC分类号： C23C4/105 , C04B35/486 , C04B35/505 , C04B2235/3225 , C04B2235/3244 , C04B2235/76 , C23C4/02 , C23C4/11 , C23C4/18 , C23C28/3215 , C23C28/3455 , Y10T428/12549 , Y10T428/12618 , Y10T428/2495
摘要： Coating systems and processes by which the coating systems can be deposited to be resistant to contaminants, and particularly resistant to infiltration and damage caused by CMAS. The coating systems include inner and outer ceramic layers, each having a microstructure characterized by splats and horizontal porosity. The inner ceramic layer consists essentially of zirconia stabilized by about 6 to about 9 weight percent yttria. The outer ceramic layer overlies and contacts the inner ceramic layer to define the outermost surface of the coating system. The outer ceramic layer consists essentially of zirconia stabilized by about 25 to about 75 weight percent yttria, has a thickness that is less than the thickness of the inner ceramic layer, and has a porosity level that is lower than that of the inner ceramic layer.
摘要翻译：可以将涂层系统沉积以抵抗污染物，特别是对由CMAS引起的渗透和损害的涂层系统和工艺。涂覆系统包括内部和外部陶瓷层，每个具有由splats和水平孔隙度表征的微观结构。内部陶瓷层主要由由约6至约9重量％的氧化钇稳定的氧化锆组成。外陶瓷层覆盖并接触内陶瓷层以限定涂层系统的最外表面。外部陶瓷层主要由由约25至约75重量％的氧化钇稳定的氧化锆组成，其厚度小于内部陶瓷层的厚度，并且具有低于内部陶瓷层的厚度的孔隙率水平。

5. 发明申请

US20070248457A1 RUB COATING FOR GAS TURBINE ENGINE COMPRESSORS 审中-公开
标题翻译：用于气体涡轮发动机压缩机的RUB涂层
公开(公告)号：US20070248457A1
公开(公告)日：2007-10-25
申请号：US11553111
申请日：2006-10-26
申请人： Albert S. Dodd , Thomas John Tomlinson , William R. Rossey
发明人： Albert S. Dodd , Thomas John Tomlinson , William R. Rossey
IPC分类号： F01D5/20
CPC分类号： F01D11/122 , B23P6/007 , C23C4/073 , C23C30/00 , F01D5/005 , F01D5/286 , F01D5/288 , F05C2201/0466 , F05D2230/80 , F05D2230/90 , F05D2260/95 , F05D2300/15 , F05D2300/611 , Y02T50/67 , Y02T50/673 , Y10T29/49318
摘要： Rub coatings, and methods for applying rub coatings, are provided for compressor assemblies of gas turbine engine assemblies. The coating may be applied as an initial coating to a new surface of a component, as well as a repair and replacement corrosion resistant rub coating for applying to a previously coated component of a gas turbine engine assembly such as a compressor casing. The method includes the steps of providing a component of a gas turbine engine assembly, the component having predetermined dimensions and specifications for operational use in an engine assembly. The component has a surface having a damaged rub coating thereon, the damaged rub coating not in compliance with the predetermined dimensions and specifications. The method includes removing the non-compliant damaged rub coating to expose the surface. Next, a repair corrosion resistant rub coating comprising MCrAlX is applied to the surface. Finally, the repair corrosion resistant rub coating comprising MCrAlX is machined to restore the coated component to comply with the predetermined dimensions and specifications.
摘要翻译：提供了用于燃气涡轮发动机组件的压缩机组件的摩擦涂层和用于涂覆摩擦涂层的方法。涂层可以作为初始涂层施加到部件的新表面，以及用于施加到诸如压缩机壳体的燃气涡轮发动机组件的预先涂覆的部件的修复和替换耐腐蚀摩擦涂层。该方法包括提供燃气涡轮发动机组件的部件的步骤，该部件具有用于发动机组件中的操作使用的预定尺寸和规格。该组件具有在其上具有损坏的摩擦涂层的表面，损坏的擦拭涂层不符合预定的尺寸和规格。该方法包括去除不顺应损坏的摩擦涂层以暴露表面。接下来，将包含MCrAlX的修复耐腐蚀的摩擦涂层施加到表面。最后，加工包含MCrAlX的修复耐腐蚀的摩擦涂层，以恢复涂覆的部件以符合预定的尺寸和规格。

6. 发明申请

US20090108134A1 ICING PROTECTION SYSTEM AND METHOD FOR ENHANCING HEAT TRANSFER 审中-公开
标题翻译：保护系统及其加热方法
公开(公告)号：US20090108134A1
公开(公告)日：2009-04-30
申请号：US11923753
申请日：2007-10-25
申请人： Joseph Albert Thodiyil , Daniel Jean-Louis Laborie , Andrew Jay Skoog , Thomas John Tomlinson
发明人： Joseph Albert Thodiyil , Daniel Jean-Louis Laborie , Andrew Jay Skoog , Thomas John Tomlinson
IPC分类号： B64D15/02 , B64D15/04
CPC分类号： B64D15/04 , B64D2033/0233 , C23C4/073 , C23C4/131 , F28F13/185 , F28F2265/14
摘要： An icing protection system and method for enhancing heat transfer includes a substrate having an inner wall, an outer wall and a thickness separating the inner wall and the outer wall. A metallic layer deposited on the inner wall of the substrate by an electric arc thermal spray deposition process using at least one metallic wire has a thickness between about 0.203 mm (0.008 inches) and about 0.432 mm (0.017 inches), a surface roughness greater than about 12.7 microns (500 micro-inches) Ra, and a heat transfer augmentation of at least about 1.1. The metallic layer is formed on the inner wall from an M-Cr—Al alloy where M is selected from Fe, Co and Ni. The metallic layer defines a plurality of turbulators that act as micro-fins to enhance heat transfer from a heated gas in flow communication with the metallic layer through the substrate to prevent the formation of ice on the outer wall.
摘要翻译：用于增强热传递的结冰保护系统和方法包括具有分隔内壁和外壁的内壁，外壁和厚度的基板。通过使用至少一根金属线的电弧热喷涂沉积方法沉积在基板的内壁上的金属层具有约0.203mm（0.008英寸）和约0.432mm（0.017英寸）之间的厚度，表面粗糙度大于约12.7微米（500微英寸）Ra，和传热增加至少约1.1。金属层由M-Cr-Al合金形成在内壁上，其中M选自Fe，Co和Ni。金属层限定多个湍流器，其作为微翅片，以增强与金属层通过基底流动连通的加热气体的热传递，以防止在外壁上形成冰。

7. 发明申请

US20110302781A1 METHOD FOR PROVIDING RUB COATINGS FOR GAS TURBINE ENGINE COMPRESSORS 审中-公开
标题翻译：用于燃气涡轮发动机压缩机的润滑油涂层的方法
公开(公告)号：US20110302781A1
公开(公告)日：2011-12-15
申请号：US13214842
申请日：2011-08-22
申请人： Albert S. DODD, IV , Thomas John Tomlinson , William R. Rossey, JR.
发明人： Albert S. DODD, IV , Thomas John Tomlinson , William R. Rossey, JR.
IPC分类号： B23P6/00
CPC分类号： F01D11/122 , B23P6/007 , C23C4/073 , C23C30/00 , F01D5/005 , F01D5/286 , F01D5/288 , F05C2201/0466 , F05D2230/80 , F05D2230/90 , F05D2260/95 , F05D2300/15 , F05D2300/611 , Y02T50/67 , Y02T50/673 , Y10T29/49318
摘要： Rub coatings, and methods for applying rub coatings, are provided for compressor assemblies of gas turbine engine assemblies. The coating may be applied as an initial coating to a new surface of a component, as well as a repair and replacement corrosion resistant rub coating for applying to a previously coated component of a gas turbine engine assembly such as a compressor casing. The method includes the steps of providing a component of a gas turbine engine assembly, the component having predetermined dimensions and specifications for operational use in an engine assembly. The component has a surface having a damaged rub coating thereon, the damaged rub coating not in compliance with the predetermined dimensions and specifications. The method includes removing the non-compliant damaged rub coating to expose the surface. Next, a repair corrosion resistant rub coating comprising MCrAlX is applied to the surface. Finally, the repair corrosion resistant rub coating comprising MCrAlX is machined to restore the coated component to comply with the predetermined dimensions and specifications.
摘要翻译：提供了用于燃气涡轮发动机组件的压缩机组件的摩擦涂层和用于涂覆摩擦涂层的方法。涂层可以作为初始涂层施加到部件的新表面，以及用于施加到诸如压缩机壳体的燃气涡轮发动机组件的预先涂覆的部件的修复和替换耐腐蚀摩擦涂层。该方法包括提供燃气涡轮发动机组件的部件的步骤，该部件具有用于发动机组件中的操作使用的预定尺寸和规格。该组件具有在其上具有损坏的摩擦涂层的表面，损坏的擦拭涂层不符合预定的尺寸和规格。该方法包括去除不顺应损坏的摩擦涂层以暴露表面。接下来，将包含MCrAlX的修复耐腐蚀的摩擦涂层施加到表面。最后，加工包含MCrAlX的修复耐腐蚀的摩擦涂层，以恢复涂覆的部件以符合预定的尺寸和规格。

8. 发明授权

US06847004B2 Process of removing a ceramic coating deposit in a surface hole of a component 有权
标题翻译：在组件的表面孔中去除陶瓷涂层沉积物的过程
公开(公告)号：US06847004B2
公开(公告)日：2005-01-25
申请号：US10248343
申请日：2003-01-10
申请人： Nripendra Nath Das , Mark Samuel Bailey , Clarence Albert Ash , Thomas John Tomlinson
发明人： Nripendra Nath Das , Mark Samuel Bailey , Clarence Albert Ash , Thomas John Tomlinson
IPC分类号： F01D5/28 , B23K26/00 , B23K26/38 , F01D9/02 , F01D25/00 , F02C7/00 , F23R3/42
CPC分类号： B23K26/0622 , B23K26/382 , B23K26/389 , B23K26/40 , B23K2101/001 , B23K2101/34 , B23K2103/50 , B23K2103/52 , B23P2700/06
摘要： A process of removing ceramic deposits from a surface hole in a component, a particular example being portions of a ceramic coating deposited on a surface of a component equipped with cooling holes. The process makes use of a pulsed Nd:YAG laser operated with parameters that avoid delamination, cracking or otherwise damaging a ceramic coating surrounding a cooling hole. The laser is operated to generate a laser beam that removes some of the ceramic deposit from the hole while a residual portion of the ceramic deposit remains surrounding the hole to define a surface opening.
摘要翻译：从组件的表面孔中去除陶瓷沉积物的过程，具体实例是沉积在装有冷却孔的部件的表面上的陶瓷涂层的部分。该方法利用脉冲Nd：YAG激光器，其操作具有避免分层，破裂或以其他方式损坏围绕冷却孔的陶瓷涂层的参数。操作激光器以产生从孔中去除一些陶瓷沉积物的激光束，而陶瓷沉积物的残余部分保留围绕孔以限定表面开口。

9. 发明授权

US07216485B2 Adjusting airflow in turbine component by depositing overlay metallic coating 有权
标题翻译：通过沉积覆盖金属涂层来调节涡轮机部件中的气流
公开(公告)号：US07216485B2
公开(公告)日：2007-05-15
申请号：US10934172
申请日：2004-09-03
申请人： James Michael Caldwell , Thomas John Tomlinson , Robert George Zimmerman, Jr. , Raymond William Heidorn , Gilbert Farmer
发明人： James Michael Caldwell , Thomas John Tomlinson , Robert George Zimmerman, Jr. , Raymond William Heidorn , Gilbert Farmer
IPC分类号： F02C1/00
CPC分类号： F23R3/06 , B23P2700/06 , F23R2900/03042 , Y10T29/49341
摘要： A method for adjusting the airflow in a turbine component having a plurality of airflow holes. The method comprises the step of depositing an overlay metallic coating on the surface of the turbine component in a manner such that at least some of the airflow holes are partially filled such that the volume of the partially filled airflow holes is changed so as to adjust the airflow through the turbine component. Also provided is a turbine component having a plurality of airflow holes, at least some of the airflow holes being partially filled with the overlay metallic coating to change the volume thereof so as to adjust the airflow through the turbine component.
摘要翻译：一种用于调节具有多个气流孔的涡轮机部件中的气流的方法。该方法包括以下方式沉积覆盖金属涂层的步骤：使得至少一些气流孔部分地被填充，使得部分填充的气流孔的体积被改变，以便调节气流通过涡轮机组件。还提供了具有多个气流孔的涡轮机部件，至少一些气流孔部分地被覆盖金属涂层填充以改变其体积，以便调节通过涡轮机部件的气流。

10. 发明授权

US06620457B2 Method for thermal barrier coating and a liner made using said method 有权
公开(公告)号：US06620457B2
公开(公告)日：2003-09-16
申请号：US09905798
申请日：2001-07-13
申请人： Gilbert Farmer , Thomas John Tomlinson , Raymond William Heidorn , Jeffrey Arnold Fehrenbach , William Lee Imhoff , Myron Edward Rutherford
发明人： Gilbert Farmer , Thomas John Tomlinson , Raymond William Heidorn , Jeffrey Arnold Fehrenbach , William Lee Imhoff , Myron Edward Rutherford
IPC分类号： B05D102
CPC分类号： C23C4/00 , B23P2700/06 , C23C4/02 , C23C4/18 , Y02T50/67
摘要： A method of applying a thermal barrier coating system to a metal piece having cooling holes angled in a first direction and cooling holes angled in a second direction. The method includes spraying a bond coat on a first surface of the piece at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the bond coat from entirely filling any of the holes. A thermal barrier coating is sprayed on the bond coat at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the thermal barrier coating from entirely filling any of the holes. The method also includes spraying a high pressure fluid jet from a nozzle assembly through each hole generally parallel to the respective cooling hole.

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式