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1. 发明申请

US20050053467A1 Aluminide or chromide coating of turbine engine rotor component 失效
公开(公告)号：US20050053467A1
公开(公告)日：2005-03-10
申请号：US10655835
申请日：2003-09-05
申请人： John Ackerman , Michael Weimer , Joseph Heaney , Robert Zimmerman , Bangalore Nagaraj , Brian Hazel , Nripendra Das
发明人： John Ackerman , Michael Weimer , Joseph Heaney , Robert Zimmerman , Bangalore Nagaraj , Brian Hazel , Nripendra 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.

2. 发明申请

US20050008780A1 Aluminide coating of turbine engine component 失效
标题翻译：涡轮发动机部件的铝酸盐涂层
公开(公告)号：US20050008780A1
公开(公告)日：2005-01-13
申请号：US10615094
申请日：2003-07-08
申请人： John Ackerman , Michael Weimer , Joseph Heaney , William Walston , Bangalore Nagaraj
发明人： John Ackerman , Michael Weimer , Joseph Heaney , William Walston , Bangalore Nagaraj
IPC分类号： C23C10/08 , C23C16/04 , C23C16/20 , C23C16/56 , C23C16/00
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.
摘要翻译：一种用于在涡轮发动机部件上形成铝化物涂层的方法，所述方法具有外表面和由内表面限定的内腔，所述内表面通过至少一个孔连接到所述外表面。该方法在具有中空的内部涂覆室的蒸气涂覆容器中进行，并且包括以下步骤：将涂覆室与待涂覆的部件装载; 在特定温度，压力和时间下将三烷基铝涂层气体流入装载的涂覆室中，以将铝涂层沉积在部件的外表面和内表面上; 并在特定温度和时间下在非氧化气氛中加热组分，以在外表面和内表面上形成铝化物涂层。然后将涂覆的组分在氧的存在下保持在升高的温度，以在组件的外表面和内表面上形成氧化物涂层。在一个实施例中，涡轮发动机部件是具有外表面和内部冷却腔的涡轮发动机叶片，其具有通过冷却孔连接到外表面的内表面。

3. 发明申请

US20050138805A1 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：US20050138805A1
公开(公告)日：2005-06-30
申请号：US10747458
申请日：2003-12-29
申请人： Brian Hazel , Eva Lanman , Joseph Heaney , Michael Weimer
发明人： Brian Hazel , Eva Lanman , Joseph Heaney , Michael Weimer
IPC分类号： C09D1/00 , C09D1/02 , C09D4/00 , C09D5/18 , F01D5/28 , F01D25/00 , B23P6/00 , 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，使超合金基底暴露于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。

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