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1. 发明授权

US06532657B1 Pre-service oxidation of gas turbine disks and seals 失效
标题翻译：燃气涡轮盘和密封件的预服务氧化
公开(公告)号：US06532657B1
公开(公告)日：2003-03-18
申请号：US09957844
申请日：2001-09-21
申请人： Michael James Weimer , Bangalore Aswatha Nagaraj , Jon Conrad Schaeffer , Joseph Aloysius Heaney, III
发明人： Michael James Weimer , Bangalore Aswatha Nagaraj , Jon Conrad Schaeffer , Joseph Aloysius Heaney, III
IPC分类号： B21K2500
CPC分类号： C23C28/044 , C23C8/02 , C23C8/14 , C23C8/80 , F01D5/288 , F05D2300/21 , Y10T29/49316 , Y10T29/4932 , Y10T29/49336
摘要： A gas turbine component, such as a turbine disk or a rotating seal, is fabricated by furnishing a substrate shaped as a gas turbine component made of a nickel-base superalloy, and oxidizing the substrate to produce an oxidized substrate having thereon a layer comprising an oxide and having a thickness of at least about 500 Angstroms. The step of oxidizing is performed prior to entry of the component into service and in an atmosphere that does not contain combustion gas. The oxidized gas turbine component is thereafter placed into service.
摘要翻译：燃气涡轮机部件，例如涡轮盘或旋转密封件，通过提供一种形状为由镍基超级合金制成的燃气涡轮机部件的基底而制造，并氧化该基底以产生氧化的基底，其上具有包含氧化物并且具有至少约500埃的厚度。氧化步骤在组分进入使用之前和在不含燃烧气体的气氛中进行。氧化燃气轮机组件此后投入使用。

2. 发明授权

US06926928B2 Protection of a gas turbine component by a vapor-deposited oxide coating 失效
标题翻译：通过气相沉积氧化物涂层保护燃气轮机部件
公开(公告)号：US06926928B2
公开(公告)日：2005-08-09
申请号：US10199185
申请日：2002-07-19
申请人： John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , James Andrew Hahn , Michael James Weimer , Jon Conrad Schaeffer , William Scott Walston
发明人： John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , James Andrew Hahn , Michael James Weimer , Jon Conrad Schaeffer , William Scott Walston
IPC分类号： C23C16/40 , F01D5/28 , C23C16/18
CPC分类号： F01D5/288 , C23C16/40 , F05D2230/314 , Y02T50/67
摘要： A gas turbine component, such as a turbine disk or a turbine seal element, is protected by depositing an oxide coating on the gas turbine component. The deposition is performed by a vapor deposition process such as metal-organic chemical vapor deposition (MOCVD) to a coating thickness of from about 0.2 to about 50 micrometers, preferably from about 0.5 to about 3 micrometers. The deposited oxide may be an oxide of aluminum, silicon, tantalum, titanium, and chromium.
摘要翻译：诸如涡轮盘或涡轮密封元件的燃气涡轮机部件通过在燃气涡轮机部件上沉积氧化物涂层来保护。沉积通过诸如金属 - 有机化学气相沉积（MOCVD）的气相沉积工艺进行，涂层厚度为约0.2至约50微米，优选约0.5至约3微米。沉积的氧化物可以是铝，硅，钽，钛和铬的氧化物。

3. 发明授权

US06921251B2 Aluminide or chromide coating of turbine engine rotor component 失效
标题翻译：涡轮发动机转子部件的铝酸盐或铬酸盐涂层
公开(公告)号：US06921251B2
公开(公告)日：2005-07-26
申请号：US10655835
申请日：2003-09-05
申请人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , Robert George Zimmerman, Jr. , Bangalore Aswatha Nagaraj , Brian Thomas Hazel , Nripendra Nath Das
发明人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , Robert George Zimmerman, Jr. , Bangalore Aswatha Nagaraj , Brian Thomas Hazel , Nripendra Nath Das
IPC分类号： C23C10/02 , C23C16/16 , C23C16/20 , F01D5/28 , F01D5/14
CPC分类号： F01D5/288 , C23C10/02 , C23C16/16 , C23C16/20 , F05D2230/90 , F05D2300/611 , Y02T50/67
摘要： A turbine engine rotor component, such as a compressor or turbine disk or seal element, is protected from corrosion by depositing an aluminum or chromium coating on the component. The deposition can be performed by a vapor deposition process, such as metal organic chemical vapor deposition (MOCVD), to a coating thickness of from about 0.2 to about 50 microns, typically from about 0.5 to about 3 microns. In one embodiment, the method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; and flowing a tri-alkyl aluminum or chromium carbonyl coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum or chromium coating on the surface of the component. The coated component is then heated in a nonoxidizing atmosphere to a specified temperature to form an aluminide or chromide coating on the surface. The coated component is typically then heated or maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the surface of the component.
摘要翻译：诸如压缩机或涡轮盘或密封元件的涡轮发动机转子部件通过在组件上沉积铝或铬涂层来防止腐蚀。沉积可以通过气相沉积工艺（例如金属有机化学气相沉积（MOCVD））进行，涂层厚度为约0.2至约50微米，通常为约0.5至约3微米。在一个实施方案中，该方法在具有中空内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与要涂覆的组分装载; 并在规定的温度，压力和时间下将三烷基铝或铬羰基涂覆气体流入装载的涂覆室，以在组件的表面上沉积铝或铬涂层。然后将涂覆的组分在非氧化气氛中加热至特定温度，以在表面上形成铝化物或铬酸盐涂层。然后通常在氧存在下将涂覆的组分加热或保持在升高的温度，以在组分的表面上形成氧化物涂层。

4. 发明授权

US06905730B2 Aluminide coating of turbine engine component 失效
公开(公告)号：US06905730B2
公开(公告)日：2005-06-14
申请号：US10615094
申请日：2003-07-08
申请人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , William Scott Walston , Bangalore Aswatha Nagaraj
发明人： John Frederick Ackerman , Michael James Weimer , Joseph Aloysius Heaney , William Scott Walston , Bangalore Aswatha Nagaraj
IPC分类号： C23C10/08 , C23C16/04 , C23C16/20 , C23C16/56
CPC分类号： C23C16/56 , C23C10/08 , C23C16/045 , C23C16/20 , Y02T50/67
摘要： A method for forming an aluminide coating on a turbine engine component having an external surface and an internal cavity defined by an internal surface that is connected to the external surface by at least one hole. The method is conducted in a vapor coating container having a hollow interior coating chamber, and includes the steps of loading the coating chamber with the component to be coated; flowing a tri-alkyl aluminum coating gas into the loaded coating chamber at a specified temperature, pressure, and time to deposit an aluminum coating on the external and internal surfaces of the component; and heating the component in a nonoxidizing atmosphere at a specified temperature and time to form an aluminide coating on the external and internal surfaces. The coated component is typically then maintained at an elevated temperature in the presence of oxygen to form an oxide coating on the external and internal surfaces of the component. In one embodiment, the turbine engine component is a turbine engine blade having an external surface and an internal cooling cavity having an internal surface that is connected to the external surface by cooling holes.

5. 发明授权

US06607789B1 Plasma sprayed thermal bond coat system 有权
标题翻译：等离子喷涂热粘涂层系统
公开(公告)号：US06607789B1
公开(公告)日：2003-08-19
申请号：US09842503
申请日：2001-04-26
申请人： Joseph David Rigney , Michael James Weimer , Bangalore Aswatha Nagaraj , Yuk-Chiu Lau
发明人： Joseph David Rigney , Michael James Weimer , Bangalore Aswatha Nagaraj , Yuk-Chiu Lau
IPC分类号： C23C404
CPC分类号： C23C28/3455 , C23C4/02 , C23C28/321 , C23C28/345 , Y10T428/12611 , Y10T428/12944
摘要： A method for forming a thermal barrier coating system on an article subjected to a hostile thermal environment, such as the hot gas path components of a gas turbine engine. The coating system is generally comprised of a ceramic layer and an environmentally resistant beta phase nickel aluminum intermetallic (&bgr;-NiAl) bond coat that adheres the ceramic layer to the component surface. A thin aluminum oxide scale forms on the surface of the &bgr;-NiAl during heat treatment. The &bgr;-NiAl may contain alloying elements in addition to nickel and aluminum in order to increase the environmental resistance of the &bgr;-NiAl. The &bgr;-NiAl powder having a size in the range of 20-50 microns is applied using air plasma spray techniques to produce a surface having a roughness of 400 microinches or rougher. The ceramic top coat can be applied using inexpensive thermal spray techniques to greater thicknesses than achievable otherwise because of the rough surface finish of the underlying &bgr;-NiAl bond coat.
摘要翻译：一种用于在遭受恶劣热环境的制品（例如燃气涡轮发动机的热气路径部件）上形成热障涂层系统的方法。涂层系统通常包括陶瓷层和环境友好的β相镍铝金属间化合物（β-NiAl）粘合涂层，其将陶瓷层粘附到组件表面。在热处理期间，在β-NiAl的表面上形成薄的氧化铝垢。除了镍和铝之外，β-NiAl还可以含有合金元素，以增加β-NiAl的耐环境性。使用空气等离子喷涂技术施加尺寸在20-50微米范围内的β-NiAl粉末，以产生粗糙度为400微英寸或更粗糙的表面。陶瓷面漆可以使用廉价的热喷涂技术应用于厚度大于其它可能的厚度，因为底层β-NiAl粘合涂层的粗糙表面光洁度。

6. 发明授权

US06616978B1 Protecting a substrate with a multilayer oxide/phosphate coating having a temperature-stepped cure 有权
标题翻译：用具有温度阶梯式固化的多层氧化物/磷酸盐涂层保护基材
公开(公告)号：US06616978B1
公开(公告)日：2003-09-09
申请号：US10147172
申请日：2002-05-09
申请人： Michael James Weimer , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , James Andrew Hahn
发明人： Michael James Weimer , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , James Andrew Hahn
IPC分类号： B05D136
CPC分类号： C23C22/74 , C04B28/34 , C04B2111/00482 , C23C18/1216 , C23C18/1225 , C23C18/1283 , C23C22/82 , C23C26/00 , C23C28/044 , F01D5/288 , F05D2230/90 , F05D2300/611 , C04B40/0263
摘要： A substrate is protected by a multilayer protective coating having an oxide layer, and a phosphate/organic binder layer initially overlying the oxide layer. The multilayer protective coating is cured by first degassing the multilayer protective coating in a pre-cure degassing temperature range of from about 250° F. to about 500° F. for a time of at least about 30 minutes. The multilayer protective coating is thereafter heated to a curing temperature range of from about 1200° F. to about 1400° F. for a time of at least about 30 minutes.
摘要翻译：基底由具有氧化物层的多层保护涂层和最初覆盖氧化物层的磷酸盐/有机粘合剂层保护。通过在约250°F至约500°F的预固化脱气温度范围内首先将多层保护涂层脱气至少约30分钟来固化多层保护涂层。然后将多层保护涂层加热至约1200°F至约1400°F的固化温度范围至少约30分钟。

7. 发明申请

US20080080978A1 Coated turbine engine components and methods for making the same 审中-公开
标题翻译：涂层涡轮发动机部件及其制造方法
公开(公告)号：US20080080978A1
公开(公告)日：2008-04-03
申请号：US11542444
申请日：2006-10-03
申请人： Robert George Zimmerman , John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , Michael James Weimer
发明人： Robert George Zimmerman , John Frederick Ackerman , Joseph Aloysius Heaney , Bangalore Aswatha Nagaraj , Michael James Weimer
IPC分类号： F03B3/12
CPC分类号： C25D5/34 , C25D3/50 , C25D5/50 , F01D5/00 , F05D2230/313 , F05D2230/314 , F05D2230/40 , F05D2230/90 , F05D2300/143 , Y02T50/67
摘要： Methods for coating a turbine engine rotor component involving depositing at least one platinum group metal selected from platinum, palladium, rhodium, ruthenium, iridium and osmium on the rotor component, and heating the rotor component to a temperature of from about 500° C. to about 800° C.
摘要翻译：用于涂覆涡轮发动机转子部件的方法包括将选自铂，钯，铑，钌，铱和锇中的至少一种铂族金属沉积在转子部件上，以及将转子部件加热至约500℃至约800℃

8. 发明授权

US09034479B2 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：US09034479B2
公开(公告)日：2015-05-19
申请号：US13542057
申请日：2012-07-05
申请人： Bangalore Aswatha Nagaraj , Douglas Gerard Konitzer , Julie Marie Chapman , Venkat Subramaniam Venkataramani
发明人： Bangalore Aswatha Nagaraj , Douglas Gerard Konitzer , Julie Marie Chapman , Venkat Subramaniam Venkataramani
IPC分类号： F01D25/00 , C04B35/48 , F01D5/28 , C23C4/10 , C23C4/18 , C23C30/00
CPC分类号： F01D25/007 , C04B35/48 , C23C4/11 , C23C4/18 , C23C28/3215 , C23C28/3455 , C23C28/347 , C23C30/00 , F01D5/284 , F01D5/288 , Y10T428/12549 , Y10T428/12618 , Y10T428/2495 , Y10T428/24967
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. The inner ceramic layer consists essentially of zirconia stabilized by about 6 to about 9 weight percent yttria and optionally contains greater than 0.5 to 10 weight percent hafnium oxide. 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 further contains greater than 0.5 to 10 weight percent hafnium oxide and optionally 1 to 10 weight percent tantalum oxide. The outer ceramic layer 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。涂层系统包括内部和外部陶瓷层。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，并且任选地包含大于0.5至10重量％的氧化铪。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。外部陶瓷层基本上由约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，并且还包含大于0.5至10重量％的氧化铪和任选的1至10个重量百分比的氧化钽。外陶瓷层的孔隙率水平低于内陶瓷层的孔隙度。

9. 发明授权

US07807231B2 Process for forming thermal barrier coating resistant to infiltration 有权
标题翻译：形成防渗涂层的方法
公开(公告)号：US07807231B2
公开(公告)日：2010-10-05
申请号：US11164615
申请日：2005-11-30
申请人： Mark Daniel Gorman , Bangalore Aswatha Nagaraj , Robert Edward Schafrik
发明人： Mark Daniel Gorman , Bangalore Aswatha Nagaraj , Robert Edward Schafrik
IPC分类号： H05H1/24 , B05D3/06 , B05D5/00 , B05D3/04 , B05D3/02 , B05D3/14
CPC分类号： C23C4/18 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/345 , C23C28/3455 , F01D5/288 , F05D2230/40
摘要： A process for protecting a thermal barrier coating (TBC) on a component used in a high-temperature environment, such as the hot section of a gas turbine engine. The process applies a protective film on the surface of the TBC to resist infiltration of contaminants such as CMAS that can melt and infiltrate the TBC to cause spallation. The process generally entails applying to the TBC surface a metal composition containing at least one metal whose oxide resists infiltration of CMAS into the TBC. The metal composition is applied so as to form a metal film on the TBC surface and optionally to infiltrate porosity within the TBC beneath its surface. The metal composition is then converted to form an oxide film, with at least a portion of the oxide film forming a surface deposit on the TBC surface.
摘要翻译：一种用于在诸如燃气涡轮发动机的热部分的高温环境中使用的部件上保护热障涂层（TBC）的方法。该方法在TBC的表面上施加保护膜以防止可能熔化和渗透TBC的污染物诸如CMAS的污染物渗透以引起剥落。该方法通常需要向TBC表面施加含有至少一种金属的金属组合物，该金属的氧化物抵抗CMAS渗透到TBC中。施加金属组合物以在TBC表面上形成金属膜，并且任选地在其表面下方的TBC内渗透孔隙。然后将金属组合物转化成氧化物膜，其中至少一部分氧化膜在TBC表面上形成表面沉积物。

10. 发明申请

US20090162690A1 THERMAL BARRIER COATING SYSTEMS 审中-公开
标题翻译：热障涂层系统
公开(公告)号：US20090162690A1
公开(公告)日：2009-06-25
申请号：US11963976
申请日：2007-12-24
申请人： Bangalore Aswatha Nagaraj , David John Wortman , Michael Patrick Maly
发明人： Bangalore Aswatha Nagaraj , David John Wortman , Michael Patrick Maly
IPC分类号： B32B15/04
CPC分类号： C22C19/056 , C23C28/321 , C23C28/3215 , C23C28/325 , C23C28/3455 , Y02T50/67 , Y02T50/6765 , Y10T428/12549
摘要： Coating system for a metallic substrate includes a strengthened bond coat including a bond coat inner layer and an aluminum-containing layer overlying the bond coat inner layer. The bond coat inner layer is formed by deposition of a bond coat composition including, in weight percent, 14-20% Cr, 5-8% Al, 8-12% Co, 3-7% Ta, 0.1-0.6% Hf, 0.1-0.5% Y, up to about 1% Si, 0.005-0.020% Zr, 0.04-0.08% C, 0.01-0.02% B, with a remainder including Ni and incidental impurities, wherein the bond coat composition is substantially free of rhenium. The coating system includes an optional thermal barrier coating which may be a yttria-stabilized zirconia.
摘要翻译：用于金属基材的涂布系统包括包含粘合涂层内层和覆盖在粘合涂层内层上的含铝层的强化粘合涂层。粘结涂层内层通过沉积粘结涂层组合物形成，该组合物包含重量百分比为14-20％的Cr，5-8％的Al，8-12％的Co，3-7％的Ta，0.1-0.6％的Hf， 0.1-0.5％Y，至多约1％Si，0.005-0.020％Zr，0.04-0.08％C，0.01-0.02％B，余量包括Ni和杂质，其中粘合涂层组合物基本上不含铼。涂层系统包括可选的热障涂层，其可以是氧化钇稳定的氧化锆。

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