公开(公告)号：US06434876B1

公开(公告)日：2002-08-20

申请号：US09670187

申请日：2000-09-26

申请人： Gary Eugene Wheat ,  Terri Kay Brown ,  Roger Dale Wustman

发明人： Gary Eugene Wheat ,  Terri Kay Brown ,  Roger Dale Wustman

IPC分类号： B05D136

CPC分类号： C23C26/00 ,  C23C10/52 ,  Y02T50/67

摘要： A turbine blade is coated by first applying a particle-entrapped tip coating to the tip of the airfoil. An aluminum-containing coating is thereafter applied to the airfoil, including to the tip of the airfoil overlying the particle-entrapped tip coating. The aluminum-containing coating is applied by providing a source of aluminum contacting the airfoil that deposits aluminum onto the airfoil at a coating temperature, and heating the airfoil to the coating temperature so that the aluminum-containing coating is deposited onto the airfoil, and so that the aluminum-containing coating and the particle-entrapped tip coating are diffused into the turbine blade substrate. The step of applying the aluminum-containing coating occurs without substantial prior interdiffusing of the particle-entrapped tip coating with the tip of the airfoil as a separate step.

摘要翻译： 通过首先将颗粒捕获的尖端涂层施加到翼型的尖端来涂覆涡轮叶片。 然后将含铝涂层施加到翼型件，包括覆盖颗粒捕获的尖端涂层的翼型的末端。 通过在涂覆温度下提供与铝箔接触而将铝沉积在翼型上的铝源，通过提供含铝涂层，并将翼型加热到涂层温度，使含铝涂层沉积在翼型上，等等 含铝涂层和颗粒捕获的尖端涂层扩散到涡轮叶片基板中。 作为单独的步骤，施加含铝涂层的步骤发生在与翼型件的尖端之间的颗粒捕获的尖端涂层没有实质的先前相互扩散的情况下。

公开(公告)号：US6146692A

公开(公告)日：2000-11-14

申请号：US210655

申请日：1998-12-14

申请人： D. Sangeeta ,  Howard John Farr ,  Roger Dale Wustman

发明人： D. Sangeeta ,  Howard John Farr ,  Roger Dale Wustman

IPC分类号： B08B3/08 ,  C23C4/02 ,  C23C10/02 ,  C23C16/00 ,  C23F1/00 ,  C23F1/40 ,  C23G1/14 ,  C23G1/20 ,  C23G3/00 ,  F01D5/00 ,  F01D5/28 ,  B05D3/10

CPC分类号： C23C10/02 ,  C23C4/02 ,  C23G1/20 ,  F01D5/005 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/671 ,  Y10T29/49318

摘要： An aqueous caustic process can be used for replacing a thermal barrier coating on a metal surface. In the process, the metal surface is contacted with a caustic solution to remove the thermal barrier coating. The processing conditions for contacting the caustic solution are selected to avoid the formation of a peel layer during a subsequent application of a replacement thermal barrier coating and heat treatment. A replacement thermal barrier coating is then reapplied to the metal surface.

摘要翻译： 可以使用苛性碱水处理来替代金属表面上的热障涂层。 在此过程中，金属表面与苛性碱溶液接触以除去热障涂层。 选择与苛性碱溶液接触的处理条件，以避免在随后施加置换热障涂层和热处理期间形成剥离层。 然后将替代的热障涂层重新施加到金属表面。

公开(公告)号：US20090162562A1

公开(公告)日：2009-06-25

申请号：US11963995

申请日：2007-12-24

申请人： Bangalore Aswatha Nagaraj ,  David John Wortman ,  Nicole Marie Polley ,  William Bryan Connor ,  Roger Dale Wustman

发明人： Bangalore Aswatha Nagaraj ,  David John Wortman ,  Nicole Marie Polley ,  William Bryan Connor ,  Roger Dale Wustman

IPC分类号： C23C16/00 ,  B05D3/02 ,  B05D1/36 ,  B05D1/38 ,  C23C4/08 ,  H05H1/24

CPC分类号： B32B15/017 ,  C22C19/056 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/325 ,  C23C28/3455 ,  Y02T50/67 ,  Y02T50/6765

摘要： Methods for coating a substrate includes depositing on the substrate, a inner bond coat layer of a bond coat composition comprising, 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 nickel (Ni) and incidental impurities, wherein the bond coat composition is substantially free of rhenium; forming an aluminum-containing layer overlying the inner bond coat layer; and, optionally, depositing a thermal barrier coating composition overlying the aluminum-containing layer.

摘要翻译： 用于涂覆基材的方法包括在基材上沉积粘合涂层组合物的内粘合涂层，其包含重量百分比为14-20％的Cr，5-8％的Al，8-12％的Co，3-7％的Ta ，0.1-0.6％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，余量包括镍（Ni）和附带杂质， 其中所述粘合涂层组合物基本上不含铼; 形成覆盖在内粘合涂层上的含铝层; 以及任选地沉积覆盖在含铝层上的热障涂层组合物。

公开(公告)号：US07270764B2

公开(公告)日：2007-09-18

申请号：US11171686

申请日：2005-06-30

申请人： Roger Dale Wustman ,  Mark Alan Rosenzweig ,  William Clarke Brooks ,  Brian H. Pilsner ,  James Douglas Risbeck ,  Richard Roy Worthing, Jr.

发明人： Roger Dale Wustman ,  Mark Alan Rosenzweig ,  William Clarke Brooks ,  Brian H. Pilsner ,  James Douglas Risbeck ,  Richard Roy Worthing, Jr.

IPC分类号： B44C1/22 ,  C03C15/00 ,  C03C25/68 ,  C23F1/00 ,  B23P6/00

CPC分类号： C23F1/44 ,  F01D5/005 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/671 ,  Y10T29/49318

摘要： A method for selectively removing an aluminide coating from at least one surface of a metal-based substrate by: (a) contacting the surface of the substrate with at least one stripping composition comprising nitric acid at a temperature less than about 20° C. to degrade the coating without damaging the substrate; and (b) removing the degraded coating without damaging the substrate. Also disclosed is a method for replacing a worn or damaged aluminide coating on at least one surface of a metal-based substrate by selectively removing the coating using the above steps, and then applying a new aluminide coating to the surface of the substrate. Turbine engine parts, such as high-pressure turbine blades, treated using the above methods are also disclosed.

摘要翻译： 一种用于通过以下步骤从金属基底材的至少一个表面选择性去除铝化物涂层的方法：（a）使基底的表面与至少一种包含硝酸的汽提组合物在小于约20℃的温度下接触至 降低涂层而不损坏基材; 和（b）除去降解的涂层而不损坏基材。 还公开了一种用于通过使用上述步骤选择性地除去涂层来替代金属基底材的至少一个表面上的磨损或损坏的铝化物涂层的方法，然后将新的铝化物涂层施加到衬底的表面。 还公开了使用上述方法处理的涡轮发动机部件，例如高压涡轮机叶片。

公开(公告)号：US07008553B2

公开(公告)日：2006-03-07

申请号：US10339475

申请日：2003-01-09

申请人： Roger Dale Wustman ,  Mark Alan Rosenzweig ,  William Clarke Brooks ,  Brian H. Pilsner ,  James Douglas Risbeck ,  Richard Roy Worthing, Jr.

发明人： Roger Dale Wustman ,  Mark Alan Rosenzweig ,  William Clarke Brooks ,  Brian H. Pilsner ,  James Douglas Risbeck ,  Richard Roy Worthing, Jr.

IPC分类号： B44C1/22 ,  C03C15/00 ,  C03C25/68 ,  C23F1/00 ,  C23F3/00

CPC分类号： C23F1/44 ,  F01D5/005 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/671 ,  Y10T29/49318

摘要： A method for selectively removing an aluminide coating from at least one surface of a metal-based substrate by: (a) contacting the surface of the substrate with at least one stripping composition comprising nitric acid at a temperature less than about 20° C. to degrade the coating without damaging the substrate; and (b) removing the degraded coating without damaging the substrate. Also disclosed is a method for replacing a worn or damaged aluminide coating on at least one surface of a metal-based substrate by selectively removing the coating using the above steps, and then applying a new aluminide coating to the surface of the substrate. Turbine engine parts, such as high-pressure turbine blades, treated using the above methods are also disclosed.

摘要翻译： 一种用于通过以下步骤从金属基底材的至少一个表面选择性去除铝化物涂层的方法：（a）使基底的表面与至少一种包含硝酸的汽提组合物在小于约20℃的温度下接触至 降低涂层而不损坏基材; 和（b）除去降解的涂层而不损坏基材。 还公开了一种用于通过使用上述步骤选择性地除去涂层来替代金属基底材的至少一个表面上的磨损或损坏的铝化物涂层的方法，然后将新的铝化物涂层施加到衬底的表面。 还公开了使用上述方法处理的涡轮发动机部件，例如高压涡轮机叶片。

公开(公告)号：US06929825B2

公开(公告)日：2005-08-16

申请号：US10357987

申请日：2003-02-04

申请人： Roger Dale Wustman ,  William Scott Walston ,  Matthew David Saylor ,  Brian Harvey Pilsner ,  Jeffrey Allan Pfaendtner

发明人： Roger Dale Wustman ,  William Scott Walston ,  Matthew David Saylor ,  Brian Harvey Pilsner ,  Jeffrey Allan Pfaendtner

IPC分类号： C23C10/08 ,  C23C16/44 ,  F01D5/28 ,  C23C16/06

CPC分类号： F01D5/288 ,  C23C10/08 ,  Y02T50/67

摘要： A method for applying an aluminide coating on a gas 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. 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 blade to be coated; providing an aluminide coating gas in the loaded coating chamber; flowing an inert carrier gas into the loaded coating chamber comprising the aluminide coating gas at a specified gas flow rate and time to move the aluminide coating gas through the cooling holes and internal cooling cavity and deposit an aluminide coating on the internal surface of the blade; and then flowing an inert carrier gas into the loaded coating chamber comprising the aluminide coating gas at a specified higher temperature and time to deposit an aluminide coating on the external surface of the blade.

摘要翻译： 一种在具有外表面的燃气涡轮发动机叶片上施加铝化物涂层的方法和具有通过冷却孔连接到外表面的内表面的内部冷却腔。 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刀片装载; 在装载的涂覆室中提供铝化物涂覆气体; 将惰性载气以特定的气体流量和时间流动到包含铝化物涂层气体的负载涂层室中，以移动铝化物涂层气体通过冷却孔和内部冷却腔，并将铝化物涂层沉积在刀片的内表面上; 然后使惰性载气在特定的较高温度和时间下流入包含铝化物涂层气体的装载的涂覆室中，以将铝化物涂层沉积在刮板的外表面上。

公开(公告)号：US06485262B1

公开(公告)日：2002-11-26

申请号：US09900326

申请日：2001-07-06

申请人： John Peter Heyward ,  Roger Dale Wustman ,  Timothy Lane Norris ,  Richard Clay Haubert ,  Paul John Fink

发明人： John Peter Heyward ,  Roger Dale Wustman ,  Timothy Lane Norris ,  Richard Clay Haubert ,  Paul John Fink

IPC分类号： F01D518

CPC分类号： F01D5/288 ,  C23C10/06 ,  C23C30/00 ,  F01D5/187 ,  F01D25/007

摘要： A gas turbine engine includes a blade including a leading edge, a trailing edge, a first sidewall extending in radial span between a blade root and blade tip, and a second sidewall connected to the first sidewall at the leading edge and at the trailing edge. The first and second sidewalls each include an outer surface and an inner surface. A cooling cavity is defined by the first sidewall inner surface and the second sidewall inner surface. At least a portion of the cooling cavity is coated with an oxidation resistant environmental coating that has a thickness less than 0.0015 inches.

摘要翻译： 燃气涡轮发动机包括叶片，其包括前缘，后缘，在叶片根部和叶片尖端之间以径向跨度延伸的第一侧壁和在前缘和后缘处连接到第一侧壁的第二侧壁。 第一和第二侧壁各自包括外表面和内表面。 冷却腔由第一侧壁内表面和第二侧壁内表面限定。 冷却腔的至少一部分涂覆有厚度小于0.0015英寸的抗氧化环境涂层。