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11. 发明授权

US06890587B2 Method of repairing a ceramic coating 有权
标题翻译：修复陶瓷涂层的方法
公开(公告)号：US06890587B2
公开(公告)日：2005-05-10
申请号：US10120417
申请日：2002-04-12
申请人： Abdus S. Khan , John Fernihough , Maxim Konter
发明人： Abdus S. Khan , John Fernihough , Maxim Konter
IPC分类号： C23C30/00 , C04B41/50 , C04B41/87 , C23C24/08 , F01D5/28 , B05D3/12 , B05D7/14
CPC分类号： C04B41/009 , C04B41/5042 , C04B41/87 , C23C24/08 , F01D5/288 , F05D2230/80 , Y02T50/67 , C04B41/4535 , C04B41/455 , C04B41/4572 , C04B41/5031 , C04B41/53 , C04B35/48
摘要： It is a method of repairing a ceramic coating of an article after use of this article in a high temperature environment disclosed. The ceramic coating is removed locally at spalled areas, at the areas where the ceramic coating is removed locally a mixture including a powder of zirconia stabilized with one or a combination of yttria, calcia, scandia, magnesia, ceria and oxides of the rare earth group, and hydrated metallic halides as a binder is applied and the applied ceramic powder is dried.
摘要翻译：这是在所公开的高温环境下使用该制品后修复制品的陶瓷涂层的方法。陶瓷涂层在剥离区域局部去除，局部地除去陶瓷涂层的区域，包括用氧化钇，氧化钙，氧化钪，氧化镁，二氧化铈和稀土元素的氧化物中的一种或组合稳定的氧化锆粉末的混合物并且施加水合金属卤化物作为粘合剂，并将所施加的陶瓷粉末干燥。

12. 发明授权

US06588103B2 Tip material for a turbine blade and method of manufacturing or repairing a tip of a turbine blade 有权
标题翻译：用于涡轮叶片的尖端材料以及制造或修理涡轮叶片尖端的方法
公开(公告)号：US06588103B2
公开(公告)日：2003-07-08
申请号：US09821091
申请日：2001-03-30
申请人： John Fernihough , Maxim Konter , Andreas Bögli
发明人： John Fernihough , Maxim Konter , Andreas Bögli
IPC分类号： B23P1526
CPC分类号： B23P6/002 , C23C4/00 , F01D5/005 , F01D5/20 , F01D5/288 , F01D11/12 , Y10T29/49318 , Y10T29/49336 , Y10T29/49339 , Y10T29/4973 , Y10T29/49737 , Y10T29/49742
摘要： A tip material for a turbine blade or for repairing a damaged tip of a turbine blade having a metallic coating, the material used for the tip is equivalent in composition to the metallic coating material used for the turbine blade. Also disclosed is a method of manufacturing or repairing a tip of a turbine blade having a metallic coating by reforming the blade tip with a material equivalent in composition to the metallic coating material used for the turbine blade by bonding the material to the damaged tip.
摘要翻译：用于涡轮叶片的尖端材料或用于修复具有金属涂层的涡轮叶片的损坏的尖端，用于尖端的材料的组成与用于涡轮叶片的金属涂层材料相当。还公开了一种制造方法或修复具有金属涂层的涡轮机叶片的尖端，通过将材料与损坏的尖端接合而将用于涡轮叶片的金属涂层材料的组成相当的材料重新形成叶片尖端。

13. 发明授权

US06705383B2 Process for the rapid production of hollow components of flow machines for manufacturing development 有权
标题翻译：快速生产用于制造开发的流动机的中空部件的方法
公开(公告)号：US06705383B2
公开(公告)日：2004-03-16
申请号：US10002136
申请日：2001-12-05
申请人： Alexander Beeck , John Fernihough
发明人： Alexander Beeck , John Fernihough
IPC分类号： B22D2300
CPC分类号： B23P15/04 , B33Y80/00 , F01D5/147 , F01D5/18 , F05D2230/13 , F05D2230/21 , F05D2230/23 , F05D2230/90 , Y10T29/49339 , Y10T29/49796
摘要： A process for the rapid production of hollow components of flow machines, in particular turbine blades, for manufacturing development. In the process, the turbine blade to be produced is divided into two or more portions such that none of the portions has a cavity. The two or more portions are individually cast by means of a Rapid Prototype process, and are then joined together to form the hollow component. The process makes possible the simple and cost-effective production of turbine blades for manufacturing development, in particular for the development of the cooling systems.
摘要翻译：用于快速生产用于制造开发的流动机器，特别是涡轮叶片的中空部件的方法。在此过程中，待生产的涡轮机叶片被分成两部分或更多部分，使得没有一个部分具有空腔。两个或更多个部分通过快速原型工艺单独浇铸，然后连接在一起以形成中空部件。该过程使制造开发中的涡轮叶片的简单和成本有效的生产成为可能，特别是用于冷却系统的开发。

14. 发明授权

US06568456B1 Method for manufacture of a directionally solidified columnar grained article 有权
标题翻译：定向凝固柱状颗粒制品的制造方法
公开(公告)号：US06568456B1
公开(公告)日：2003-05-27
申请号：US09382630
申请日：1999-08-25
申请人： John Fernihough
发明人： John Fernihough
IPC分类号： B22D2704
CPC分类号： C30B11/00 , C30B29/52
摘要： A method and an apparatus for manufacturing a directionally solidified columnar grained article with a reduced amount of secondary misorientation of the columnar grains. The method employs a casting assembly comprising a mold with a cavity, a selector section at a lower end of the mold, a heating chamber and a cooling chamber. The mold is fed with a liquid metal and then removed from the heating chamber to the cooling chamber where the columnar grained article is solidified. The article is solidified with at least two dendrites or grains emerging from the selector section and entering the main cavity of the shell mold. Further, the selector section is configured so that no dendrite or grain grows from the bottom of the selector section into the shell mold cavity along a continuous path of purely vertical growth.
摘要翻译：用于制造定向凝固的柱状晶粒物品的方法和装置，其具有减少的柱状晶粒的二次取向偏差。该方法采用铸造组件，其包括具有空腔的模具，在模具下端的选择器部分，加热室和冷却室。模具被供给液态金属，然后从加热室移至冷却室，柱状颗粒物品被固化。物品由至少两个从选择器部分出现并进入壳模的主腔的枝晶或晶粒固化。此外，选择器部分被构造成使得沿着纯垂直生长的连续路径，不会从选择器部分的底部生长树枝晶或晶粒进入壳模腔。

15. 发明授权

US07225857B2 Apparatus for manufacture of directionally solidified columnar grained article thereof 有权
标题翻译：用于制造定向凝固的柱状颗粒物品的装置
公开(公告)号：US07225857B2
公开(公告)日：2007-06-05
申请号：US10929692
申请日：2004-08-31
申请人： John Fernihough
发明人： John Fernihough
IPC分类号： B23C9/04
CPC分类号： C30B11/00 , C30B29/52
摘要： An apparatus for manufacturing a directionally solidified columnar grained article with a reduced amount of secondary misorientation of the columnar grains. The apparatus includes a casting assembly comprising a mold with a cavity, a selector section at a lower end of the mold, a heating chamber and a cooling chamber. The mold is fed with a liquid metal and then moved from the heating chamber to the cooling chamber where the columnar grained article is solidified. The article is solidified with at least two dendrites (or grains) emerging from the selector section and entering the main cavity of the shell mold. Further, the selector section is configured so that no dendrite or grain grows from the bottom of the selector section into the shell mold cavity along a continuous path of purely vertical growth.
摘要翻译：一种用于制造具有减少的柱状颗粒的二次取向偏向量的定向凝固的柱状颗粒物品的设备。该装置包括铸造组件，其包括具有空腔的模具，在模具下端的选择器部分，加热室和冷却室。模具被供给液态金属，然后从加热室移动到柱状颗粒物品固化的冷却室。该制品由从选择器部分出现并进入壳模的主腔的至少两个枝晶（或晶粒）固化。此外，选择器部分被构造成使得沿着纯垂直生长的连续路径，不会从选择器部分的底部生长树枝晶或晶粒进入壳模腔。

16. 发明授权

US06534975B2 NONDESTRUCTIVE METHOD FOR DETERMINING THE THICKNESS OF A METALLIC PROTECTIVE LAYER ON A METALLIC BASE MATERIAL VIA A DIFFERENT TYPE OF LAYER BETWEEN THE METALLIC PROTECTIVE LAYER AND THE METALLIC BASE MATERIAL 有权
标题翻译：用于通过金属保护层和金属基材之间的不同类型的金属基材料确定金属保护层的厚度的非结合方法
公开(公告)号：US06534975B2
公开(公告)日：2003-03-18
申请号：US09754188
申请日：2001-01-05
申请人： Alexander Beeck , Andreas Boegli , John Fernihough , Klaus Schneider
发明人： Alexander Beeck , Andreas Boegli , John Fernihough , Klaus Schneider
IPC分类号： G01B706
CPC分类号： G01B21/085 , C23C4/12 , F01D5/288 , G01B1/00 , G01B7/105 , G01B17/025
摘要： A nondestructive method for determining the thickness of a metallic protective layer determined by detection of a different type of intervening layer which is situated between the metallic protective layer and the metallic base material, by ultrasound, eddy-current or (pulsed) thermography. The intervening layer may comprise a nonmetallic layer of oxides or carbides, a metallic layer of pure nickel or a layer with depleted Al and Ti content in that region of the base material which is close to the surface. This method can be used for turbine blades in order to determine the layer thickness, for example during the test phase of coating, and to avoid the known destruction of the turbine blade, which is labor- and cost-intensive.
摘要翻译：通过超声，涡流或（脉冲）热成像法检测位于金属保护层和金属基材之间的不同类型的中间层确定金属保护层的厚度的非破坏性方法。中间层可以包括氧化物或碳化物的非金属层，纯镍的金属层或在靠近表面的基材的区域中具有贫化的Al和Ti含量的层。为了确定层厚度，例如在涂层的测试阶段，这种方法可以用于涡轮叶片，并且避免已经破坏涡轮叶片，这是劳力和成本密集型的。

17. 发明申请

US20060266285A1 Masking material for holes of a component 有权
标题翻译：组件孔洞的掩模材料
公开(公告)号：US20060266285A1
公开(公告)日：2006-11-30
申请号：US11501749
申请日：2006-08-10
申请人： John Fernihough , Andreas Boegli , Alexander Stankowski
发明人： John Fernihough , Andreas Boegli , Alexander Stankowski
IPC分类号： B05C11/00
CPC分类号： C23C16/042 , B05B12/26 , B23P2700/06 , C23C4/01 , C23C8/04 , C23C10/04 , C23C14/042 , Y10T29/49318 , Y10T29/49341
摘要： Process of masking cooling holes of a gas turbine component with an external surface, comprising a cavity and a plurality of cooling holes before coating the gas turbine component, comprising the steps of first applying a mask material to the cooling holes so that the cooling holes are filled at least closest to the external surface, whereby the mask material contains a substance which fluoresces under ultraviolet light and a filler material. Then the mask material within the cooling holes is thickening. An inspection using ultraviolet light to locate any unwanted residual mask material on the external surface is carried out and unwanted residual mask material is removed before the coating is applied to the external surface of the component and the masked cooling holes. In the end the mask material is removed from the cooling holes.
摘要翻译：具有外表面的燃气轮机部件的冷却孔的处理，包括在涂覆燃气轮机部件之前的空腔和多个冷却孔，包括以下步骤：首先将掩模材料施加到冷却孔，使得冷却孔为填充至少最接近外表面，由此掩模材料含有在紫外光下发荧光的物质和填充材料。然后冷却孔内的面罩材料变厚。进行使用紫外光的检查以在外表面上定位任何不需要的残留掩模材料，并且在将涂层施加到部件的外表面和掩蔽的冷却孔之前，去除不需要的残留掩模材料。最后，将掩模材料从冷却孔中移出。

18. 发明申请

US20050191422A1 Process of masking cooling holes of a gas turbine component 有权
标题翻译：掩蔽燃气轮机部件的冷却孔的过程
公开(公告)号：US20050191422A1
公开(公告)日：2005-09-01
申请号：US10950640
申请日：2004-09-28
申请人： John Fernihough , Andreas Boegli , Alexander Stankowski
发明人： John Fernihough , Andreas Boegli , Alexander Stankowski
IPC分类号： F01D5/18 , C23C4/00 , C23C14/04 , C23C16/04 , C23C16/455 , C25D5/02 , C25D7/00 , F01D5/00 , F01D5/28 , F01D25/00 , F02C7/00 , F04D29/38 , F04D29/58 , B05D5/00
CPC分类号： F01D5/288 , B23P2700/06 , C23C4/01 , C23C14/042 , C23C16/042 , C25D5/022 , C25D7/00 , F01D5/005 , F05D2230/80 , F05D2230/90 , F05D2260/202
摘要： A process of masking cooling holes (4) of a gas turbine component (1) with an external surface (6), including a cavity (2) and a plurality of cooling holes (4) before coating the gas turbine component (1), includes first applying a mask material (5) to the cooling holes (4) so that the cooling holes are filled at least closest to the external surface (6), whereby the mask material (5) contains a filler material. Then the mask material (5) within the cooling holes (4) is thickening and the coating (8) is applied to the external surface (6) of the component (1) and the masked cooling holes (4). In the end remaining thickened mask material (5a) is removed from the cooling holes (4).
摘要翻译：在涂覆燃气轮机部件（1）之前，将包括空腔（2）和多个冷却孔（4）的外表面（6）的燃气轮机部件（1）的冷却孔（4）包括首先向所述冷却孔（4）施加掩模材料（5），使得所述冷却孔至少与所述外表面（6）最接近，由此所述掩模材料（5）含有填充材料。然后，冷却孔（4）内的掩模材料（5）变厚，将涂层（8）施加到部件（1）的外表面（6）和掩蔽冷却孔（4）上。最后，从冷却孔（4）移除剩余的增厚的掩模材料（5a）。

19. 发明申请

US20050100672A1 Method of protecting a local area of a component 有权
标题翻译：保护组件局部区域的方法
公开(公告)号：US20050100672A1
公开(公告)日：2005-05-12
申请号：US10631846
申请日：2003-08-01
申请人： Alexander Stankowski , Andreas Boegli , John Fernihough
发明人： Alexander Stankowski , Andreas Boegli , John Fernihough
IPC分类号： B23K26/36 , C23C4/00 , F01D5/00 , F01D5/28 , B05D1/32
CPC分类号： F01D5/28 , B23K26/364 , C23C4/01 , F01D5/00
摘要： It is disclosed a method of protecting a local area of components (1) from the effects of thermochemical or mechanical processes carried out on the surface (6) of the component. A masking material (5) containing at least one filler material is applied to the local area so that the local area is protected by the masking material (5). This is at least partially polymerized on the local area. Subsequently the thermochemical or physical processes on the surface (6) of the component (1) are carried out after which the polymerized masking material (5) is removed from the local area of the component (1).
摘要翻译：公开了一种保护组件（1）的局部区域免受在组件的表面（6）上进行的热化学或机械过程的影响的方法。将包含至少一种填充材料的掩模材料（5）施加到局部区域，使得局部区域被掩蔽材料（5）保护。这在局部区域至少部分聚合。随后，在组分（1）的表面（6）上进行热化学或物理过程，然后从组分（1）的局部区域除去聚合的掩蔽材料（5）。

20. 发明申请

US20050067466A1 Crack repair method 审中-公开
标题翻译：破裂修复方法
公开(公告)号：US20050067466A1
公开(公告)日：2005-03-31
申请号：US10495881
申请日：2002-11-08
申请人： Andreas Boegli , John Fernihough , Oliver Ullmann
发明人： Andreas Boegli , John Fernihough , Oliver Ullmann
IPC分类号： B23K9/04 , B23K10/02 , B23K26/34 , B23P6/00 , B23K31/00
CPC分类号： B23P6/007 , B23K9/04 , B23K10/027 , B23K26/32 , B23K26/34 , B23K26/342 , B23K2101/001 , B23K2103/08 , B23K2103/26 , B23P6/045
摘要： A method of repairing cracks on a surface of a component such as gas turbine components includes the steps of repairing the cracks of the component by brazing, detecting remaining cracks on the surface or below the surface, which were not properly filled with braze material during the repair brazing operation, and repairing the crack zones with a focussed low-heat input welding method using an appropriate weld filler materials.
摘要翻译：修复燃气轮机部件等部件的表面上的裂纹的方法包括以下步骤：通过钎焊修复部件的裂纹，检测表面上的剩余裂纹，或者在修复钎焊操作，并使用适当的焊接填充材料以聚焦的低热输入焊接方法修复裂纹区。

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