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1. 发明授权

US07056555B2 Method for coating an internal surface of an article with an aluminum-containing coating 失效
标题翻译：用含铝涂层涂覆制品的内表面的方法
公开(公告)号：US07056555B2
公开(公告)日：2006-06-06
申请号：US10318761
申请日：2002-12-13
申请人： Steven Earl Bauer , Gary Eugene Wheat , Matthew David Saylor , Jeffrey Allan Pfaendtner , Atul Natwerlal Shah
发明人： Steven Earl Bauer , Gary Eugene Wheat , Matthew David Saylor , Jeffrey Allan Pfaendtner , Atul Natwerlal Shah
IPC分类号： B05D7/22 , B05D3/02 , B05D3/12
CPC分类号： C23C10/28 , C23C10/18 , Y02T50/67
摘要： An article having an internal passage therein and an internal article surface is coated by providing a coating slurry that is a mixture of a deposition source including a source of aluminum, a halide activator, and a flowable carrier comprising a flowable compound selected from the group consisting of a flowable organic compound and a flowable inorganic compound. There is no oxide dispersant in the coating slurry. The coating slurry is introduced into the internal passage and dried to remove at least a portion of the carrier therefrom and leave a dried coating material. The article surface in gaseous communication with the dried coating material is heated to form an aluminum-containing coating bonded to the article surface. Any residual dried coating material is removed by blowing compressed air through the internal passage.
摘要翻译：通过提供作为包括铝源，卤化物活化剂和可流动载体的沉积源的混合物的涂料浆料涂覆其中具有内部通道的物品和内部物品表面，所述沉积源包括可流动化合物，所述可流动化合物选自的可流动有机化合物和可流动的无机化合物。涂层浆料中没有氧化物分散剂。将涂料浆料引入内部通道中并干燥以从其中除去至少一部分载体，并留下干燥的涂料。与干燥的涂料材料气相连的制品表面被加热以形成结合到制品表面的含铝涂层。通过内部通道吹入压缩空气来除去任何残留的干燥涂层材料。

2. 发明授权

US07632541B2 Method and device to prevent coating a dovetail of a turbine airfoil 有权
标题翻译：防止涂覆涡轮机翼型的燕尾的方法和装置
公开(公告)号：US07632541B2
公开(公告)日：2009-12-15
申请号：US11276745
申请日：2006-03-13
申请人： Matthew David Saylor , Jackie Lee King
发明人： Matthew David Saylor , Jackie Lee King
IPC分类号： C23C16/00
CPC分类号： F01D5/288 , C23C10/04 , F01D5/005 , F05D2230/90 , F05D2300/611
摘要： A method and masking assembly for masking a dovetail portion of a turbine blade during coating of an airfoil portion of the blade. The masking assembly comprises at least two masking members, each having an exterior surface and an oppositely-disposed undulatory surface complementary to one of oppositely-disposed undulatory surfaces of the dovetail portion. By mating the masking members, the undulatory surfaces thereof define an interior cavity within the masking assembly that accommodates the dovetail portion, and the undulatory surfaces of the masking members contact the undulatory surfaces of the dovetail portion to entrap the dovetail portion within the interior cavity of the masking assembly.
摘要翻译：一种用于在涂覆叶片的翼型部分期间遮蔽涡轮叶片的燕尾部分的方法和掩模组件。掩模组件包括至少两个掩蔽构件，每个遮蔽构件具有与燕尾部分的相对布置的波浪面中的一个互补的外表面和相对布置的波浪表面。通过配合掩蔽构件，其波浪表面限定掩蔽组件内的容纳燕尾部分的内腔，并且遮蔽构件的波浪表面接触燕尾部分的波浪表面，以将燕尾部分捕获在内腔内掩模组件。

3. 发明授权

US06929825B2 Method for aluminide coating of gas turbine engine blade 有权
标题翻译：燃气轮机发动机叶片铝化物涂层方法
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。

4. 发明申请

US20090252872A1 METHOD AND DEVICE TO PREVENT COATING A DOVETAIL OF A TURBINE AIRFOIL 有权
标题翻译：用于防止涡轮机空气的涂层的方法和装置
公开(公告)号：US20090252872A1
公开(公告)日：2009-10-08
申请号：US11276745
申请日：2006-03-13
申请人： Matthew David Saylor , Jackie Lee King
发明人： Matthew David Saylor , Jackie Lee King
IPC分类号： C23C16/04
CPC分类号： F01D5/288 , C23C10/04 , F01D5/005 , F05D2230/90 , F05D2300/611
摘要： A method and masking assembly for masking a dovetail portion of a turbine blade during coating of an airfoil portion of the blade. The masking assembly comprises at least two masking members, each having an exterior surface and an oppositely-disposed undulatory surface complementary to one of oppositely-disposed undulatory surfaces of the dovetail portion. By mating the masking members, the undulatory surfaces thereof define an interior cavity within the masking assembly that accommodates the dovetail portion, and the undulatory surfaces of the masking members contact the undulatory surfaces of the dovetail portion to entrap the dovetail portion within the interior cavity of the masking assembly.
摘要翻译：一种用于在涂覆叶片的翼型部分期间遮蔽涡轮叶片的燕尾部分的方法和掩模组件。掩模组件包括至少两个掩蔽构件，每个遮蔽构件具有与燕尾部分的相对布置的波浪面中的一个互补的外表面和相对布置的波浪表面。通过配合掩蔽构件，其波浪表面限定掩蔽组件内的容纳燕尾部分的内腔，并且遮蔽构件的波浪表面接触燕尾部分的波浪表面，以将燕尾部分捕获在内腔内掩模组件。

5. 发明申请

US20100000468A1 METHOD AND DEVICE TO PREVENT COATING A DOVETAIL OF A TURBINE AIRFOIL 审中-公开
标题翻译：用于防止涡轮机空气的涂层的方法和装置
公开(公告)号：US20100000468A1
公开(公告)日：2010-01-07
申请号：US12510315
申请日：2009-07-28
申请人： Matthew David Saylor , Jackie Lee King
发明人： Matthew David Saylor , Jackie Lee King
IPC分类号： B05C11/00
CPC分类号： F01D5/288 , C23C10/04 , F01D5/005 , F05D2230/90 , F05D2300/611
摘要： A method and masking assembly for masking a dovetail portion of a turbine blade during coating of an airfoil portion of the blade. The masking assembly comprises at least two masking members, each having an exterior surface and an oppositely-disposed undulatory surface complementary to one of oppositely-disposed undulatory surfaces of the dovetail portion. By mating the masking members, the undulatory surfaces thereof define an interior cavity within the masking assembly that accommodates the dovetail portion, and the undulatory surfaces of the masking members contact the undulatory surfaces of the dovetail portion to entrap the dovetail portion within the interior cavity of the masking assembly.
摘要翻译：一种用于在涂覆叶片的翼型部分期间遮蔽涡轮叶片的燕尾部分的方法和掩模组件。掩模组件包括至少两个掩蔽构件，每个遮蔽构件具有与燕尾部分的相对布置的波浪面中的一个互补的外表面和相对布置的波浪表面。通过配合掩蔽构件，其波浪表面限定掩蔽组件内的容纳燕尾部分的内腔，并且遮蔽构件的波浪表面接触燕尾部分的波浪表面，以将燕尾部分捕获在内腔内掩模组件。

6. 发明授权

US07163718B2 Method of selective region vapor phase aluminizing 有权
标题翻译：选择性区域气相镀铝的方法
公开(公告)号：US07163718B2
公开(公告)日：2007-01-16
申请号：US10685637
申请日：2003-10-15
申请人： Nripendra Nath Das , Joseph David Rigney , Jeffrey Allan Pfaendtner , Matthew David Saylor
发明人： Nripendra Nath Das , Joseph David Rigney , Jeffrey Allan Pfaendtner , Matthew David Saylor
IPC分类号： C23C16/00
CPC分类号： C23C10/06 , C23C10/02 , C23C10/14 , Y02T50/67 , Y10T428/12736
摘要： A process for forming diffusion aluminide coatings on an uncoated surface of a substrate, without interdiffusing a sufficient amount of aluminum into a coating layer to adversely affect the coating growth potential and mechanical properties of said coating layer. A metal substrate is provided comprising an external surface and an internal passage therein defined by an internal surface, at least a portion of the external surface of the substrate being coated with a coating layer selected from the group consisting of β-NiAl-base, MCrAlX, a line-of-sight diffusion aluminide, a non-line-of-sight diffusion aluminide, a pack diffusion aluminide, and a slurry diffusion aluminide on said substrate. The metal substrate is subjected to an aluminum vapor phase deposition process.
摘要翻译：在基底的未涂覆表面上形成扩散铝化物涂层的方法，而不会将足够量的铝相互扩散到涂层中，从而不利地影响涂层生长电位和所述涂层的机械性能。提供了一种金属基底，其包括由内表面限定的外表面和内部通道，所述基底的外表面的至少一部分被涂覆有选自β-NiAl基，MCrAlX ，视线扩散铝化物，非视线扩散铝化物，包层扩散铝化物和在所述衬底上的浆料扩散铝化物。金属基板经受铝气相沉积工艺。

7. 发明授权

US06933012B2 Method for protecting a surface with a silicon-containing diffusion coating 失效
标题翻译：用含硅扩散涂层保护表面的方法
公开(公告)号：US06933012B2
公开(公告)日：2005-08-23
申请号：US10318762
申请日：2002-12-13
申请人： Nripendra Nath Das , Bangalore Aswatha Nagaraj , Matthew David Saylor , Jackie Lee King
发明人： Nripendra Nath Das , Bangalore Aswatha Nagaraj , Matthew David Saylor , Jackie Lee King
IPC分类号： C23C10/08 , C23C10/46 , B05D1/00
CPC分类号： C23C10/46 , C23C10/08 , Y10T428/12458 , Y10T428/12674
摘要： A surface of an article is protected by coating the surface with a silicon-containing coating by preparing a coating mixture of silicon, a halide activator, and an oxide powder, positioning the surface of the article in gaseous communication with the coating mixture, and heating the surface of the article and the coating mixture to a coating temperature of from about 1150° F. to about 1500° F. The article is preferably a component of a gas turbine engine made of a nickel-base superalloy.
摘要翻译：通过制备硅，卤化物活化剂和氧化物粉末的涂料混合物，通过用含硅涂层涂覆表面来保护制品的表面，将制品的表面与涂料混合物气态连通并加热制品的表面和涂料混合物的涂覆温度为约1150°F至约1500°F。制品优选为由镍基超级合金制成的燃气涡轮发动机的部件。

8. 发明授权

US06485792B1 Endurance of NiA1 coatings by controlling thermal spray processing variables 失效
标题翻译：通过控制热喷涂处理变量，NiAl涂层的耐久性
公开(公告)号：US06485792B1
公开(公告)日：2002-11-26
申请号：US09644491
申请日：2000-08-23
申请人： Richard John Grylls , Joseph David Rigney , Matthew David Saylor , Theodore Robert Grossman , Yuk-Chiu Lau
发明人： Richard John Grylls , Joseph David Rigney , Matthew David Saylor , Theodore Robert Grossman , Yuk-Chiu Lau
IPC分类号： C23C406
CPC分类号： C23C4/18 , C23C4/08 , Y02T50/67
摘要： A method for applying substantially stoichiometric NiAl to the surface of a superalloy substrate. These coatings are applied to substrates subjected to high temperatures and thermal cycling by providing a powder of the substantially stoichiometric material with the desired minor additions of rare earth elements, Cr or Zr. The coatings are applied by a thermal spray process utilizing hydrogen as a fuel while generating a highly reducing flame. The thermal spray method melts the powder and directs it onto the surface of the turbine component that is to be coated. The powder size is carefully controlled to prevent oxidation of the powder while providing a controlled surface finish. The surface roughness of the bond coat is further mechanically worked to a predetermined surface finish prior to application of the ceramic thermal barrier layer by a PVD method. Thermal barrier systems applied using these carefully controlled predetermined parameters provide outstanding resistance to TBC spallation under conditions of high cyclic stresses.
摘要翻译：将基本上化学计量的NiAl施加到超级合金基底的表面上的方法。通过提供具有理想化学计量的材料的粉末和所需的稀土元素Cr或Zr的少量添加，将这些涂层施加到经受高温和热循环的基底上。通过使用氢作为燃料的热喷涂方法施加涂层，同时产生高度还原的火焰。热喷雾法将粉末熔化并将其引导到待涂覆的涡轮机部件的表面上。仔细控制粉末尺寸以防止粉末氧化，同时提供受控的表面光洁度。在通过PVD方法施加陶瓷热障层之前，将粘合涂层的表面粗糙度进一步机械加工至预定的表面光洁度。使用这些仔细控制的预定参数应用的热障系统在高循环应力的条件下提供了出色的耐TBC剥落性能。

9. 发明申请

US20080138533A1 MICROWAVE PROCESS FOR FORMING A COATING 审中-公开
标题翻译：用于形成涂料的微波工艺
公开(公告)号：US20080138533A1
公开(公告)日：2008-06-12
申请号：US11609473
申请日：2006-12-12
申请人： Karl Lee Borneman , Matthew David Saylor
发明人： Karl Lee Borneman , Matthew David Saylor
IPC分类号： B05D3/06
CPC分类号： C23C24/08 , B23K3/0623 , B23K2101/001 , C23C24/10 , C23C24/103 , F01D5/288 , F01D5/3092 , F05D2230/90
摘要： A process for forming a coating on a surface of a substrate, in which the heating source for the coating process is microwave radiation so that heating of the coating material is selective and sufficient to melt and bond the coating material to the substrate without excessively heating the substrate. The process entails forming a coating material containing powder particles that are sufficiently small to be highly susceptible to microwave radiation. The coating material is applied to a surface of the substrate and subjected to microwave radiation so that the powder particles within the coating material couple with the microwave radiation and sufficiently melt to form a coating on the substrate surface. The microwave radiation is then interrupted to allow the coating to cool, solidify, and mechanically bond to the substrate.
摘要翻译：一种在基板表面上形成涂层的方法，其中用于涂布工艺的加热源是微波辐射，使得涂层材料的加热是选择性的并且足以熔化并将涂料粘合到基材上而不过度加热基质。该方法需要形成含有粉末颗粒的涂层材料，该粉末颗粒足够小以致对微波辐射非常敏感。将涂层材料施加到基底的表面并进行微波辐射，使得涂层材料内的粉末颗粒与微波辐射耦合并充分熔化以在基底表面上形成涂层。然后中断微波辐射以允许涂层冷却，固化并机械地结合到基底。

10. 发明授权

US07026011B2 Aluminide coating of gas turbine engine blade 失效
标题翻译：燃气轮机发动机叶片的铝酸盐涂层
公开(公告)号：US07026011B2
公开(公告)日：2006-04-11
申请号：US10357972
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： C23C16/08
CPC分类号： C23C10/08 , F01D5/288 , F05D2230/313 , Y02T50/67 , Y02T50/671
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; maintaining the loaded coating chamber comprising the aluminide coating gas at a specified temperature and time to deposit an aluminide coating on the external surface of the blade; and then 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.
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; 将包含铝化物涂层气体的装载涂层室保持在规定温度和时间，以将铝化物涂层沉积在叶片的外表面上; 然后使惰性载体气体以特定的气体流速和时间流入包含铝化物涂层气体的装载的涂覆室中，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。

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