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公开(公告)号：US08561298B2
公开(公告)日：2013-10-22
申请号：US12039966
申请日：2008-02-29
Applicant: James A. Morin , Lucian Iordache , Ovidiu Timotin , Sooyeum Oh
Inventor： James A. Morin , Lucian Iordache , Ovidiu Timotin , Sooyeum Oh
CPC classification number: C22F1/10 , B23K2101/001 , Y10T29/49316 , Y10T29/49318 , Y10T29/4932 , Y10T29/49321 , Y10T29/49336
Abstract: A method for welding superalloy components at ambient temperature conditions while reducing the propensity of the superalloy material to crack as a result of the weld. A root pass region of the weld is formed using a filler material that exhibits ductility that is higher than that of the base superalloy material. The ductile material mitigates stress in the root region, thereby preventing the formation of cracks. A remaining portion of the weld is formed using a filler material that essentially matches the base superalloy material. The method may utilize a pre-weld heat treatment to grow a gamma prime precipitate phase in the superalloy material, a chill fixture to remove heat during welding, a relief cut to reduce stress in the root region, and a conventional post-weld heat treatment.
Abstract translation: 一种用于在环境温度条件下焊接超合金部件的方法，同时降低由于焊接而导致的超合金材料的裂纹倾向。 使用表现出高于基础超级合金材料的延展性的填充材料形成焊缝的根部通过区域。 延性材料减轻了根部的应力，从而防止了裂纹的形成。 使用基本上与基底超合金材料相匹配的填充材料形成焊缝的剩余部分。 该方法可以利用预焊接热处理来在超级合金材料中生长γ'沉淀相，在焊接期间除去热量的冷却夹具，减小根部区域中的应力的浮雕切割以及常规的后焊接热处理 。
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公开(公告)号：US06376801B1
公开(公告)日：2002-04-23
申请号：US09686900
申请日：2000-10-12
Applicant: Brian Harlow Farrell , Aaron Todd Frost , James A. Morin , Thaddeus Jan Strusinski
Inventor： Brian Harlow Farrell , Aaron Todd Frost , James A. Morin , Thaddeus Jan Strusinski
IPC: B23K912
CPC classification number: B23P6/007 , B23K9/1274 , B23K10/006 , B23K10/02 , B23K10/027 , B23K2101/001 , F01D5/005 , F05D2200/261 , F05D2230/23
Abstract: A gas turbine component can be refurbished and/or repaired with an arc welding process that is used in conjunction with a 6-axis robot, a camera and a robot controller/vision processor. Applied to a wire fed plasma welding process, the vision system identifies the part, constructs a weld path based on the part's individual contour, and calculates a trajectory (with or without sinusoidal oscillation) for the robot arm to follow.
Abstract translation: 燃气轮机部件可以用与6轴机器人，照相机和机器人控制器/视觉处理器结合使用的电弧焊接过程进行翻新和/或修理。 应用于馈线等离子体焊接工艺，视觉系统识别零件，根据零件的各个轮廓构建焊接路径，并计算机器人手臂遵循的轨迹（有或没有正弦振荡）。
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Patent Agency Ranking
公开(公告)号：US09186757B2
公开(公告)日：2015-11-17
申请号：US13467298
申请日：2012-05-09
Applicant: Mrinal Munshi , Ching-Pang Lee , Benjamin P. Swanson , Petya M. Georgieva , James A. Morin
Inventor： Mrinal Munshi , Ching-Pang Lee , Benjamin P. Swanson , Petya M. Georgieva , James A. Morin
CPC classification number: B23P6/002 , F01D5/005 , F01D5/18 , F01D5/186 , F01D5/187 , F01D5/20 , F01D11/14 , Y10T29/49318
Abstract: A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion.
Abstract translation: 一种修复具有限定内腔宽度的径向延伸的外壁和叶片尖端的涡轮叶片的方法。 该方法包括去除叶片尖端的至少一部分以形成修复表面并且提供具有径向外侧的顶端帽，其外部宽度可以小于内部空腔宽度，并且具有径向内侧，内侧具有内部 宽度基本上等于或大于内腔宽度。 顶盖位于修复表面，并且使用延性焊接材料将尖端焊接到修复表面。 通过围绕尖端盖进行堆积焊接而形成盖周边部分，并且通过在盖周边部分上堆积焊接形成尖叫部分。
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公开(公告)号：US20080210347A1
公开(公告)日：2008-09-04
申请号：US12039966
申请日：2008-02-29
Applicant: James A. Morin , Lucian Iordache , Ovidiu Timotin , Sooyeun Oh
Inventor： James A. Morin , Lucian Iordache , Ovidiu Timotin , Sooyeun Oh
CPC classification number: C22F1/10 , B23K2101/001 , Y10T29/49316 , Y10T29/49318 , Y10T29/4932 , Y10T29/49321 , Y10T29/49336
Abstract: A method for welding superalloy components at ambient temperature conditions while reducing the propensity of the superalloy material to crack as a result of the weld. A root pass region of the weld is formed using a filler material that exhibits ductility that is higher than that of the base superalloy material. The ductile material mitigates stress in the root region, thereby preventing the formation of cracks. A remaining portion of the weld is formed using a filler material that essentially matches the base superalloy material. The method may utilize a pre-weld heat treatment to grow a gamma prime precipitate phase in the superalloy material, a chill fixture to remove heat during welding, a relief cut to reduce stress in the root region, and a conventional post-weld heat treatment.
Abstract translation: 一种用于在环境温度条件下焊接超合金部件的方法，同时降低由于焊接而导致的超合金材料的裂纹倾向。 使用表现出高于基础超级合金材料的延展性的填充材料形成焊缝的根部通过区域。 延性材料减轻了根部的应力，从而防止了裂纹的形成。 使用基本上与基底超合金材料相匹配的填充材料形成焊缝的剩余部分。 该方法可以利用预焊接热处理来在超级合金材料中生长γ'沉淀相，在焊接期间除去热量的冷却夹具，减小根部区域中的应力的浮雕切割以及常规的后焊接热处理 。
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公开(公告)号：US20130298400A1
公开(公告)日：2013-11-14
申请号：US13467298
申请日：2012-05-09
Applicant: Mrinal Munshi , Ching-Pang Lee , Benjamin P. Swanson , Petya M. Georgieva , James A. Morin
Inventor： Mrinal Munshi , Ching-Pang Lee , Benjamin P. Swanson , Petya M. Georgieva , James A. Morin
IPC: B23P6/00
CPC classification number: B23P6/002 , F01D5/005 , F01D5/18 , F01D5/186 , F01D5/187 , F01D5/20 , F01D11/14 , Y10T29/49318
Abstract: A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion.
Abstract translation: 一种修复具有限定内腔宽度的径向延伸的外壁和叶片尖端的涡轮叶片的方法。 该方法包括去除叶片尖端的至少一部分以形成修复表面并且提供具有径向外侧的顶端帽，其外部宽度可以小于内部空腔宽度，并且具有径向内侧，内侧具有内部 宽度基本上等于或大于内腔宽度。 顶盖位于修复表面，并且使用延性焊接材料将尖端焊接到修复表面。 通过围绕尖端盖进行堆积焊接而形成盖周边部分，并且通过在盖周边部分上堆积焊接形成尖叫部分。
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公开(公告)号：US07653995B2
公开(公告)日：2010-02-02
申请号：US11497113
申请日：2006-08-01
Applicant: James A. Morin
Inventor： James A. Morin
CPC classification number: B23K31/02 , B23K35/304 , B23K2101/001 , B23P6/002 , C21D1/09 , C21D9/00 , C22F1/10 , Y10T29/49318 , Y10T29/49723 , Y10T29/49732 , Y10T29/49742
Abstract: A method of weld repairing a superalloy material at ambient temperature without causing cracking of the base material. A superalloy material such as CM-247 LC, as is commonly used in gas turbine blade applications, is subjected to an overage pre-weld heat treatment in order to grow the volume percentage of gamma prime precipitate in the material to a level sufficient to permit ambient temperature welding without cracking. CM-247 LC material is heated in a vacuum furnace at a rate of about 0.5° C. per minute to an intermediate temperature of about 885° C. The material is then gas fan quenched to a temperature of about 52° C. to grow the gamma prime precipitate percentage to about 55%. A fusion repair weld may then be performed on the material at an ambient temperature using a filler material having a chemistry matching a chemistry of the base material.
Abstract translation: 在环境温度下焊接修复超合金材料的方法，而不会引起基体材料的开裂。 在燃气轮机叶片应用中通常使用的诸如CM-247LC的超级合金材料经受过度预焊接热处理，以将材料中的γ'沉淀物的体积百分比增加至足以允许 环境温度焊接无裂纹。 CM-247 LC材料在真空炉中以约0.5℃/分钟的速率加热至约885℃的中间温度。然后将材料淬火至约52℃的温度以生长 γ'沉淀百分比至约55％。 然后可以使用具有与基材的化学性质匹配的化学物质的填充材料在环境温度下对材料进行熔融修补焊缝。
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公开(公告)号：US20090320966A1
公开(公告)日：2009-12-31
申请号：US11497113
申请日：2006-08-01
Applicant: James A. Morin
Inventor： James A. Morin
CPC classification number: B23K31/02 , B23K35/304 , B23K2101/001 , B23P6/002 , C21D1/09 , C21D9/00 , C22F1/10 , Y10T29/49318 , Y10T29/49723 , Y10T29/49732 , Y10T29/49742
Abstract: A method of weld repairing a superalloy material at ambient temperatures without causing cracking of the base material. A superalloy material such as CM-247 LC, as is commonly used in gas turbine blade applications, is subjected to an overage pre-weld heat treatment in order to grow the volume percentage of gamma prime precipitate in the material to a level sufficient to permit ambient temperature welding without cracking. CM-247 LC material is heated in a vacuum furnace at a rate of about 0.5° C. per minute to an intermediate temperature of about 885° C. The material is then gas fan quenched to a temperature of about 52° C. to grow the gamma prime precipitate percentage to about 55%. A fusion repair weld may then be performed on the material at an ambient temperature using a filler material having a chemistry matching a chemistry of the base material.
Abstract translation: 在环境温度下焊接修复超合金材料而不引起基体材料破裂的方法。 在燃气轮机叶片应用中通常使用的诸如CM-247LC的超级合金材料经受过度预焊接热处理，以将材料中的γ'沉淀物的体积百分比增加至足以允许 环境温度焊接无裂纹。 CM-247 LC材料在真空炉中以约0.5℃/分钟的速率加热至约885℃的中间温度。然后将材料淬火至约52℃的温度以生长 γ'沉淀百分比至约55％。 然后可以使用具有与基材的化学性质匹配的化学物质的填充材料在环境温度下对材料进行熔融修补焊缝。
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