公开(公告)号：US20050191516A1

公开(公告)日：2005-09-01

申请号：US11113197

申请日：2005-04-25

申请人： Bangalore Nagaraj ,  Eva Lanman ,  Deborah Schorr ,  Thomas Tomlinson ,  Raymond Heidorn ,  David Kastrup ,  Craig Young

发明人： Bangalore Nagaraj ,  Eva Lanman ,  Deborah Schorr ,  Thomas Tomlinson ,  Raymond Heidorn ,  David Kastrup ,  Craig Young

IPC分类号： C23C4/10 ,  C23C4/00 ,  C23C4/02 ,  C23C28/00 ,  B32B15/10

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。

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。

公开(公告)号：US20050051527A1

公开(公告)日：2005-03-10

申请号：US10655284

申请日：2003-09-04

申请人： Thomas Kelly ,  Samuel Mastrorocco ,  Earl Helder ,  Eva Lanman ,  Vallerie McGee

发明人： Thomas Kelly ,  Samuel Mastrorocco ,  Earl Helder ,  Eva Lanman ,  Vallerie McGee

IPC分类号： B23K9/23 ,  B23K9/00 ,  B23K9/167 ,  B23K9/235 ,  B23K31/00 ,  B23K103/04 ,  C21D9/50 ,  C23C8/10 ,  C23C8/80

CPC分类号： B23K9/167 ,  B23K2103/02 ,  C21D9/50 ,  C23C8/10 ,  C23C8/80

摘要： A method for welding iron-based or nickel-based superalloy assemblies into a unitary article. First, the assemblies are heated in an air atmosphere, at a rate suitable to minimize geometric distortion, to a temperature in the range of about 1400 F (760 C) to about 2000° F. (1090° C.) to form an oxide layer on the surface of the assemblies and optionally as a pre-weld solution heat treat. The temperature of the assemblies are then held in a range of about 1400 F (760 C) to about 2000° F. (1090° C.) for a time sufficient to form an oxide layer of sufficient thickness on the surface of the assemblies and optionally to solution the assemblies. The assemblies are then cooled to ambient temperature at a rate sufficient to avoid precipitation of unwanted metal phases at a rate sufficient to maintain dimensional stability. The oxide layer is then removed from at least the faying surfaces of the assemblies, but not from the face side of the assemblies. The faying surfaces of the assemblies are then cleaned. The assemblies are then welded using a GTA welding procedure to form a unitary article. The article is then resolutioned at an appropriate temperature for an appropriate period of time, both of which are dependent on the type of superalloy(s) that is present in the welded article and the desired properties. The article is then optionally age heat treated at an appropriate temperature for an appropriate period of time, both of which are dependent on the type of superalloy(s) that is present in the welded unitary article.

摘要翻译： 将铁基或镍基超级合金组件焊接成整体制品的方法。 首先，将组件以适合于将几何变形最小化的速率在空气气氛中加热至约1400°F（760℃）至约2000°F（1090℃）的温度以形成氧化物 在组件的表面上并且可选地作为预焊接溶液热处理。 然后将组件的温度保持在约1400°F（760℃）至约2000°F（1090℃）的范围内足以在组件的表面上形成足够厚度的氧化物层的时间，以及 可选地解决组件。 然后将组件以足以避免不必要的金属相以足以维持尺寸稳定性的速率沉淀的速率冷却至环境温度。 然后从组件的至少拼接表面除去氧化层，而不是从组件的表面侧去除氧化层。 然后清洁组件的接合表面。 然后使用GTA焊接程序焊接组件以形成整体制品。 然后将物品在合适的温度下分解合适的时间，这两个时间段都取决于焊接制品中存在的超级合金的类型和所需的性能。 然后将制品任意地在合适的温度下对其进行老化热处理适当的时间，这两个时间取决于焊接的整体制品中存在的超级合金的类型。