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1.发明授权公开(公告)号：US06534975B2
公开(公告)日：2003-03-18
申请号：US09754188
申请日：2001-01-05
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。
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公开(公告)号：US20060266285A1
公开(公告)日：2006-11-30
申请号：US11501749
申请日：2006-08-10
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。
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公开(公告)号：US20050191422A1
公开(公告)日：2005-09-01
申请号：US10950640
申请日：2004-09-28
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）。
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公开(公告)号：US20050100672A1
公开(公告)日：2005-05-12
申请号：US10631846
申请日：2003-08-01
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）。
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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
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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公开(公告)号：US07772314B2
公开(公告)日：2010-08-10
申请号：US11501749
申请日：2006-08-10
IPC分类号： B05D1/32 , B23P6/00 , B29C35/08 , C08K3/08 , C08K3/20 , C08K3/22 , C08K3/34 , C08K7/02 , C08K7/08 , C08K7/10 , C09K3/00 , C09K3/10
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。
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公开(公告)号：US07192622B2
公开(公告)日：2007-03-20
申请号：US10995489
申请日：2004-11-24
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。
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公开(公告)号：US07147899B2
公开(公告)日：2006-12-12
申请号：US10950640
申请日：2004-09-28
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）。
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公开(公告)号：US07083824B2
公开(公告)日：2006-08-01
申请号：US10631846
申请日：2003-08-01
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）。
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公开(公告)号：US20050215686A1
公开(公告)日：2005-09-29
申请号：US10995489
申请日：2004-11-24
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。
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