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1. 发明申请

US20090000706A1 METHOD OF CONTROLLING AND REFINING FINAL GRAIN SIZE IN SUPERSOLVUS HEAT TREATED NICKEL-BASE SUPERALLOYS 审中-公开
标题翻译：超级热处理镍基超级合金中控制和精制最终粒度的方法
公开(公告)号：US20090000706A1
公开(公告)日：2009-01-01
申请号：US11770257
申请日：2007-06-28
申请人： Eric Scott Huron , Joseph Aloysius Heaney , David Paul Mourer , Jon Raymond Groh , Edward Lee Raymond , David Alan Utah , Michael James Weimer , Kenneth Rees Bain
发明人： Eric Scott Huron , Joseph Aloysius Heaney , David Paul Mourer , Jon Raymond Groh , Edward Lee Raymond , David Alan Utah , Michael James Weimer , Kenneth Rees Bain
IPC分类号： C22F1/10 , C22C19/05
CPC分类号： C22F1/10 , C22C19/056 , C22C19/057
摘要： A method of forming a component from a gamma prime precipitation-strengthened nickel-base superalloy. The method entails formulating the superalloy to have a sufficiently high carbon content and forging the superalloy at sufficiently high local strain rates so that, following a supersolvus heat treatment, the component is characterized by a fine and substantially uniform grain size distribution, preferably finer than ASTM 7 and more preferably in a range of about ASTM 8 to 10.
摘要翻译：一种由伽玛原淀粉强化的镍基超级合金形成组分的方法。该方法需要配制超级合金以具有足够高的碳含量并以足够高的局部应变速率锻造超合金，使得在超溶氧热处理之后，该组分的特征在于精细且基本均匀的晶粒尺寸分布，优选比ASTM 7，更优选在约8〜10℃的范围内。

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

US07546683B2 Touch-up of layer paint oxides for gas turbine disks and seals 有权
标题翻译：用于燃气轮机盘和密封件的层漆氧化物的接触
公开(公告)号：US07546683B2
公开(公告)日：2009-06-16
申请号：US10747458
申请日：2003-12-29
申请人： Brian Thomas Hazel , Eva Zielonka Lanman , Joseph Aloysius Heaney , Michael James Weimer
发明人： Brian Thomas Hazel , Eva Zielonka Lanman , Joseph Aloysius Heaney , Michael James Weimer
IPC分类号： B23P6/00 , B23D19/10 , B23K9/04
CPC分类号： F01D5/286 , C09D1/00 , C09D1/02 , C09D5/18 , F01D5/288 , F01D25/007 , F05D2230/80 , F05D2230/90 , F05D2300/2112 , F05D2300/611 , Y02T50/67 , Y10T29/49318 , Y10T29/49746 , Y10T29/49885
摘要： The present invention is a process for applying oxide paint as a touch-up paint for an oxide-based corrosion inhibiting coating with at least one imperfection region. Such oxide-based corrosion inhibiting coatings are applied on superalloy components used for moderately high temperature applications, such as the superalloy components found in the high-pressure turbine (HPT) section of a gas turbine engine, including turbine disks and seals. However, during the application of oxide-based corrosion inhibiting coatings, imperfection regions sometimes occur, exposing the superalloy substrate beneath the oxide-based corrosion inhibiting coating. Such imperfection regions can include a spalled region, a scratched region, a chipped region, an uncoated region, or combinations thereof. The process of the present invention is useful where aircraft engine components have been treated with a corrosion inhibiting three-layer paint oxide system comprising chromia and alumina, but where a small imperfection region or regions within the layer oxide system are present after initial manufacture, refurbishment, or repair of the component.
摘要翻译：本发明是一种将氧化物涂料用作具有至少一个不完美区域的氧化物基腐蚀抑制涂层的上涂料的方法。这种基于氧化物的腐蚀抑制涂层被应用于用于适度高温应用的超级合金部件上，例如在包括涡轮盘和密封件的燃气涡轮发动机的高压涡轮机（HPT）部分中发现的超级合金部件。然而，在施加氧化物基腐蚀抑制涂层期间，有时会出现缺陷区域，使超合金基底暴露在氧化物基腐蚀抑制涂层之下。这样的缺陷区域可以包括剥落区域，划痕区域，切屑区域，未涂覆区域或其组合。本发明的方法在飞机发动机部件已经被包括氧化铬和氧化铝的腐蚀抑制三层涂料氧化物体系处理但在初始制造，翻新之后存在于氧化层系中的小缺陷区域或区域的情况下是有用的，或修理组件。

4. 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。

5. 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℃

6. 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。

7. 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.

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