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1. 发明授权

US06729940B2 Apparatus for stripping coating 有权
标题翻译：剥离涂层的设备
公开(公告)号：US06729940B2
公开(公告)日：2004-05-04
申请号：US10369425
申请日：2003-02-19
申请人： Gilbert Farmer , Jeffrey Arnold Fehrenbach , William Lee Imhoff , David Allen Kastrup
发明人： Gilbert Farmer , Jeffrey Arnold Fehrenbach , William Lee Imhoff , David Allen Kastrup
IPC分类号： C23C1600
CPC分类号： B44D3/16 , B08B3/02
摘要： A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.
摘要翻译：从组分的涂覆表面的一部分剥离涂层的方法。该方法包括在邻近涂覆表面的部分的区域上将掩模片紧固到部件上。掩模片具有通常对应于部件表面轮廓的轮廓。在将掩模片固定到部件上之后，将高压流体射流从喷头喷射到涂覆表面的部分，以从表面的部分剥离涂层。在从表面的部分剥离涂层之后，将掩模片从部件上移除。

2. 发明授权

US06561872B2 Method and apparatus for stripping coating 有权
公开(公告)号：US06561872B2
公开(公告)日：2003-05-13
申请号：US09878847
申请日：2001-06-11
申请人： Gilbert Farmer , Jeffrey Arnold Fehrenbach , William Lee Imhoff , David Allen Kastrup
发明人： Gilbert Farmer , Jeffrey Arnold Fehrenbach , William Lee Imhoff , David Allen Kastrup
IPC分类号： B24B100
CPC分类号： B44D3/16 , B08B3/02
摘要： A method of stripping coating from a portion of a coated surface of a component. The method includes fastening a mask sheet to the component over a region adjacent the portion of the coated surface. The mask sheet has a contour generally corresponding to a contour of the surface of the component. A high pressure fluid jet is sprayed from a spray head toward the portion of the coated surface after the mask sheet is fastened to the component to strip the coating from the portion of the surface. After the coating is stripped from the portion of the surface, the mask sheet is removed from the component.

3. 发明授权

US06620457B2 Method for thermal barrier coating and a liner made using said method 有权
公开(公告)号：US06620457B2
公开(公告)日：2003-09-16
申请号：US09905798
申请日：2001-07-13
申请人： Gilbert Farmer , Thomas John Tomlinson , Raymond William Heidorn , Jeffrey Arnold Fehrenbach , William Lee Imhoff , Myron Edward Rutherford
发明人： Gilbert Farmer , Thomas John Tomlinson , Raymond William Heidorn , Jeffrey Arnold Fehrenbach , William Lee Imhoff , Myron Edward Rutherford
IPC分类号： B05D102
CPC分类号： C23C4/00 , B23P2700/06 , C23C4/02 , C23C4/18 , Y02T50/67
摘要： A method of applying a thermal barrier coating system to a metal piece having cooling holes angled in a first direction and cooling holes angled in a second direction. The method includes spraying a bond coat on a first surface of the piece at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the bond coat from entirely filling any of the holes. A thermal barrier coating is sprayed on the bond coat at angles with respect to the first and second directions and to a thickness selected in combination with the angles to prevent the thermal barrier coating from entirely filling any of the holes. The method also includes spraying a high pressure fluid jet from a nozzle assembly through each hole generally parallel to the respective cooling hole.

4. 发明授权

US06908657B2 Coated component with through-hole having improved surface finish 失效
标题翻译：具有通孔的涂层部件具有改进的表面光洁度
公开(公告)号：US06908657B2
公开(公告)日：2005-06-21
申请号：US10605241
申请日：2003-09-17
申请人： Gilbert Farmer , Jeffrey Arnold Fehrenbach
发明人： Gilbert Farmer , Jeffrey Arnold Fehrenbach
IPC分类号： B24C1/00 , B23P6/00 , B24C11/00 , C23C4/00 , F01D5/18 , F01D5/28 , B32B3/10 , F02G1/00
CPC分类号： B23P6/002 , B23P2700/06 , C23C4/00 , F01D5/186 , F01D5/288 , F05D2230/13 , F05D2260/607 , Y10T29/49318 , Y10T29/49339 , Y10T428/12361 , Y10T428/24273 , Y10T428/249953
摘要： A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.
摘要翻译：从空气冷却燃气涡轮发动机的冷却孔中除去金属结合层和陶瓷材料等成分的通孔的沉积物的工序。该方法特别有效地除去沉积在部件的冷却孔中的TBC材料，这是因为在组件的表面上沉积TBC材料的涂层，其中沉积物从冷却孔移除而不损坏冷却孔或TBC涂层，围绕组件的涂覆表面上的冷却孔。一个优选的特征是，包括在与涂覆表面相对的部件的表面处的孔的入口和围绕涂覆表面的孔的出口的涂层的冷却孔表现出改进的表面特性，其增加了如冷却孔的有效面积的增加所证明的。

5. 发明授权

US06663919B2 Process of removing a coating deposit from a through-hole in a component and component processed thereby 失效
标题翻译：从被处理的部件和部件中的通孔中去除涂层沉积物的过程
公开(公告)号：US06663919B2
公开(公告)日：2003-12-16
申请号：US10086266
申请日：2002-03-01
申请人： Gilbert Farmer , Jeffrey Arnold Fehrenbach
发明人： Gilbert Farmer , Jeffrey Arnold Fehrenbach
IPC分类号： C23C418
CPC分类号： B23P6/002 , B23P2700/06 , C23C4/00 , F01D5/186 , F01D5/288 , F05D2230/13 , F05D2260/607 , Y10T29/49318 , Y10T29/49339 , Y10T428/12361 , Y10T428/24273 , Y10T428/249953
摘要： A process of removing deposits from through-holes in a component, such as metallic bond coat and ceramic materials from cooling holes in an air-cooled gas turbine engine. The process is particularly effective in removing a TBC material deposited in a cooling hole of a component as a result of depositing a coating of the TBC material on a surface of the component, in which the deposit is removed from the cooling hole without damaging the cooling hole or the TBC coating surrounding the cooling hole on the coated surface of the component. A preferred feature is that the cooling hole, including the entrance to the hole at a surface of the component opposite the coated surface and the coating surrounding the exit of the hole at the coated surface, exhibits improved surface characteristics that increase the discharge coefficient of the cooling hole, as evidenced by an increase in the effective area of the cooling hole.
摘要翻译：从空气冷却燃气涡轮发动机的冷却孔中除去金属结合层和陶瓷材料等成分的通孔的沉积物的工序。该方法特别有效地除去沉积在部件的冷却孔中的TBC材料，这是因为在组件的表面上沉积TBC材料的涂层，其中沉积物从冷却孔移除而不损坏冷却孔或TBC涂层，围绕组件的涂覆表面上的冷却孔。一个优选的特征是，包括在与涂覆表面相对的部件的表面处的孔的入口和围绕涂覆表面的孔的出口的涂层的冷却孔表现出改进的表面特性，其增加了如冷却孔的有效面积的增加所证明的。

6. 发明授权

US06329015B1 Method for forming shaped holes 有权
标题翻译：形成孔的方法
公开(公告)号：US06329015B1
公开(公告)日：2001-12-11
申请号：US09576921
申请日：2000-05-23
申请人： Jeffrey Arnold Fehrenbach , John Howard Starkweather , Michael Beverley
发明人： Jeffrey Arnold Fehrenbach , John Howard Starkweather , Michael Beverley
IPC分类号： B41N124
CPC分类号： B41C1/141 , B23K26/389 , B23P2700/06 , B24C1/045
摘要： A method of forming a shaped hole in a substrate, including substrates protected by coatings, as is the case where an air-cooled component has a thermal barrier coating for protection from a hostile thermal environment, such as the turbine, combustor and augmentor sections of a gas turbine engine. In particular, cooling holes are formed in an air-cooled component after a ceramic layer has been deposited on the surface of the component without damaging or spalling the ceramic layer. Processing steps generally include forming a hole through the ceramic layer and a substrate protected by the ceramic layer, thereby defining an opening at the surface of the ceramic layer. The diameter of the hole is less than the final size required for the cooling hole. A high-pressure abrasive fluid stream is then directed into the hole to enlarge the cross-section of the hole and impart a noncircular shape to the opening by removing portions of the substrate and ceramic layer without removing the ceramic layer surrounding the resulting noncircular-shaped opening. In a preferred embodiment, the abrasive fluid stream is traversed across the surface of the ceramic through a series of nested patterns that are not concentric with the central axis of the hole. Preferably, the hole acquires the desired noncircular shape in the ceramic layer, but retains a circular shape in the substrate.
摘要翻译：一种在衬底中形成成形孔的方法，包括由涂层保护的衬底，如空气冷却部件具有用于防止恶劣热环境的热障涂层（例如涡轮机，燃烧器和增压器部分）的情况燃气涡轮发动机。特别地，在陶瓷层已经沉积在部件的表面上而不损坏或剥落陶瓷层之后，在空气冷却部件中形成冷却孔。加工步骤通常包括通过陶瓷层形成孔和由陶瓷层保护的衬底，由此在陶瓷层的表面上限定开口。孔的直径小于冷却孔所需的最终尺寸。然后将高压磨料流体引导到孔中以扩大孔的横截面，并通过去除基底和陶瓷层的部分而赋予开口的非圆形形状，而不去除围绕所得非圆形的陶瓷层开放在优选实施例中，磨料流体通过与孔的中心轴线不同心的一系列嵌套图案横穿陶瓷的表面。优选地，该孔在陶瓷层中获得所需的非圆形形状，但在基板中保持圆形。

7. 发明授权

US06368060B1 Shaped cooling hole for an airfoil 失效
标题翻译：翼型形状的冷却孔
公开(公告)号：US06368060B1
公开(公告)日：2002-04-09
申请号：US09576287
申请日：2000-05-23
申请人： Jeffrey Arnold Fehrenbach , John Howard Starkweather , Michael Beverley
发明人： Jeffrey Arnold Fehrenbach , John Howard Starkweather , Michael Beverley
IPC分类号： F04D2958
CPC分类号： F04D29/023 , B23P2700/06 , F01D5/186 , F01D5/288 , F04D29/584 , F05D2230/31 , F05D2300/2118 , F05D2300/611
摘要： A cooling hole configuration for an air-cooled component, such as a gas turbine engine airfoil. The cooling hole is configured to have cross-sectional variations and a noncircular-shaped diffuser-type opening that significantly improve the cooling film distribution across the external surface of an airfoil, with the result that heat transfer from the surrounding environment to the airfoil is reduced. The cooling hole is configured to have its central axis at an acute angle to the exterior surface of the airfoil, and defines a noncircular-shaped opening at the airfoil surface. The cooling hole generally has a first region adjacent the airfoil surface and a second region interior to the airfoil. The cooling hole is configured such that the second region has an oblong or oval-shaped cross-section, with a major diameter approximately equal to the major diameter of the first region and a minor diameter less than the major diameter of the first region, with a smooth transition existing between the first and second regions. The oblong shape of the second region is preferably the result of a recess being present in the wall of the cooling hole opposite the direction in which the cooling hole extends toward the airfoil surface, causing the central axis of the cooling hole to have an arcuate shape in which the central axis is disposed at a lesser angle to the airfoil surface in the first region than the angle in the second region. The cooling hole can be generated using a water jet technique.
摘要翻译：用于空气冷却部件（例如燃气涡轮发动机翼型）的冷却孔构造。冷却孔被构造成具有横截面变化和非圆形扩散型开口，其显着地改善了跨越翼型的外表面的冷却膜分布，结果是从周围环境到翼型的热传递减少。冷却孔被构造成使其中心轴线与翼型件的外表面成锐角，并且在翼型表面处限定非圆形的开口。冷却孔通常具有与翼面表面相邻的第一区域和在翼面内部的第二区域。冷却孔构造成使得第二区域具有长圆形或椭圆形的横截面，其大直径近似等于第一区域的长度直径，小于第一区域的主直径，在第一和第二区域之间存在平滑过渡。第二区域的长方形优选是与冷却孔朝向翼型面延伸的方向相反的冷却孔的壁上存在凹部的结果，使得冷却孔的中心轴线具有弓形其中中心轴以与第二区域中的角度相比在第一区域中的翼型表面设置成较小的角度。可以使用喷水技术产生冷却孔。

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