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公开(公告)号：WO1996000840A1
公开(公告)日：1996-01-11
申请号：PCT/US1995008316
申请日：1995-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： UNITED TECHNOLOGIES CORPORATION , ROWE, Jon, G. , PIETRUSKA, Norman , PAWLACZYK, Richard, J. , WILCOX, Gilbert, B.
IPC: F01D05/00
CPC classification number: B23P6/005 , F01D5/005 , Y10T29/49318 , Y10T29/4973 , Y10T29/49737
Abstract: The present invention relates to a method for refurbishing or restoring a turbine vane or other airfoil to restore a desired flow area. The method in one embodiment comprises the steps of: providing a plate to be used to restore the flow area on the airfoil; cutting the plate into a desired shape; machining a series of tapers into the cut plate so that the cut plate has a single region with a substantially uniform thickness; overlaying a surface of the airfoil with the pre-cut, pre-shaped plate so that the substantially uniform thickness region is positioned over that part of the airfoil where the flow area is to be restored; and attaching the pre-cut, pre-shaped plate to the airfoil. The refurbishment or restoration method further comprises heat treating the pre-cut, pre-shaped plate so that the plate softens and conforms to the shape of the airfoil surface.
Abstract translation: 本发明涉及一种用于翻新或恢复涡轮叶片或其它翼型件以恢复所需流动面积的方法。 在一个实施例中的方法包括以下步骤：提供用于恢复翼面上的流动面积的板; 将板切割成所需的形状; 将一系列锥形加工到切割板中，使得切割板具有基本均匀厚度的单个区域; 用预切割的预成形板将翼型件的表面覆盖，使得基本上均匀的厚度区域位于要恢复流动区域的翼型的该部分上方; 并将预切割的预制板连接到翼型件。 翻新或恢复方法还包括对预切割的预制板进行热处理，使得板软化并符合翼型表面的形状。
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公开(公告)号：WO1995021042A3
公开(公告)日：1995-08-10
申请号：PCT/US1995001310
申请日：1995-01-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： UNITED TECHNOLOGIES CORPORATION , DRAGHI, Peter, J. , PIETRUSKA, Norman , ARMSTRONG, Wayne, F.
IPC: B23K35/30
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公开(公告)号：WO1993022097A1
公开(公告)日：1993-11-11
申请号：PCT/US1993004326
申请日：1993-05-06
Applicant: UNITED TECHNOLOGIES CORPORATION
IPC: B23K35/30
CPC classification number: B23P6/002 , B23K35/3046 , B23P6/007 , C22F1/10 , F01D5/005
Abstract: An improved method is described for repairing Co-base superalloy gas turbine engine components by applying a mixture of base alloy powder and base alloy powder with a melting point depressant to the surface of the component and heating at 2250-2300 DEG F to diffuse the melting point depressant isothermally into the base alloy. A protective coating is then applied, during which a heating cycle which ages the base material is used. The resultant component has high temperature creep properties which are significantly better than achieved using the prior art process. The same temperature cycle is also useful in the initial heat treatment of Co-base superalloys, and can also be used for rejuvenation of components which have experienced extensive exposure to engine operating conditions.
Abstract translation: 描述了一种改进的方法，用于通过将基础合金粉末和基底合金粉末与熔点低于组分表面的基础合金粉末混合并在2250-2300°F加热来扩散熔融物来修复Co基超合金燃气轮机发动机部件 点状抑制剂等温进入基体合金。 然后施加保护涂层，在此期间使用使基材老化的加热循环。 所得组分具有高温蠕变性能，其明显优于使用现有技术方法的实施。 相同的温度循环在共碱基超级合金的初始热处理中也是有用的，并且还可以用于经历大量暴露于发动机操作条件的部件的复原。
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公开(公告)号：EP0767867B1
公开(公告)日：1999-09-08
申请号：EP95925433.5
申请日：1995-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROWE, Jon, G. , PIETRUSKA, Norman , PAWLACZYK, Richard, J. , WILCOX, Gilbert, B.
CPC classification number: B23P6/005 , F01D5/005 , Y10T29/49318 , Y10T29/4973 , Y10T29/49737
Abstract: The present invention relates to a method for refurbishing or restoring a turbine vane or other airfoil to restore a desired flow area. The method in one embodiment comprises the steps of: providing a plate to be used to restore the flow area on the airfoil; cutting the plate into a desired shape; machining a series of tapers into the cut plate so that the cut plate has a single region with a substantially uniform thickness; overlaying a surface of the airfoil with the pre-cut, pre-shaped plate so that the substantially uniform thickness region is positioned over that part of the airfoil where the flow area is to be restored; and attaching the pre-cut, pre-shaped plate to the airfoil. The refurbishment or restoration method further comprises heat treating the pre-cut, pre-shaped plate so that the plate softens and conforms to the shape of the airfoil surface.
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Patent Agency Ranking5.发明公开REPAIR COATING FOR SUPERALLOY ARTICLES, SUCH AS GAS TURBINE ENGINE COMPONENTS 失效AS燃气轮机部件修复涂层超耐热合金制品
公开(公告)号：EP0751849A1
公开(公告)日：1997-01-08
申请号：EP95908770.0
申请日：1995-01-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： DRAGHI, Peter, J. , PIETRUSKA, Norman , ARMSTRONG, Wayne, F.
CPC classification number: B23P6/007 , B23K35/025 , B23K35/3033 , B23K35/3046 , B23K2201/001 , C23G5/00
Abstract: A repair coating for superalloy articles, such as gas turbine engine components, includes a volatile organic carrier or water-based carrier, a fluxing agent, a thickening agent, balance a filler mix. The filler mix consists of at least two distinct particulate components. The mix includes a first particulate component having a composition which approximates that of the article being repaired. The mix also includes a second particulate component having a composition approximating that of the article and a melting point depressant, such as boron. This melting point depressant is substantially in excess of that in the article and sufficient to provide melting of a portion of the mix at a processing temperature below the melting temperature of the article. The above filler mix is blended with the other constituents to form the repair coating which is applied to an article.
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公开(公告)号：EP0593736B1
公开(公告)日：2001-03-14
申请号：EP93911137.3
申请日：1993-05-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： PIETRUSKA, Norman , KURPASKA, Michael, S.
CPC classification number: B23P6/002 , B23K35/3046 , B23P6/007 , C22F1/10 , F01D5/005
Abstract: An improved method is described for repairing Co-base superalloy gas turbine engine components by applying a mixture of base alloy powder and base alloy powder with a melting point depressant to the surface of the component and heating at 2250-2300 °F to diffuse the melting point depressant isothermally into the base alloy. A protective coating is then applied, during which a heating cycle which ages the base material is used. The resultant component has high temperature creep properties which are significantly better than achieved using the prior art process. The same temperature cycle is also useful in the initial heat treatment of Co-base superalloys, and can also be used for rejuvenation of components which have experienced extensive exposure to engine operating conditions.
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7.发明授权REPAIR COATING FOR SUPERALLOY ARTICLES, SUCH AS GAS TURBINE ENGINE COMPONENTS 失效AS燃气轮机部件修复涂层超耐热合金制品
公开(公告)号：EP0751849B1
公开(公告)日：1999-04-14
申请号：EP95908770.1
申请日：1995-01-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： DRAGHI, Peter, J. , PIETRUSKA, Norman , ARMSTRONG, Wayne, F.
CPC classification number: B23P6/007 , B23K35/025 , B23K35/3033 , B23K35/3046 , B23K2201/001 , C23G5/00
Abstract: A repair coating for superalloy articles, such as gas turbine engine components, includes a volatile organic carrier or water-based carrier, a fluxing agent, a thickening agent, balance a filler mix. The filler mix consists of at least two distinct particulate components. The mix includes a first particulate component having a composition which approximates that of the article being repaired. The mix also includes a second particulate component having a composition approximating that of the article and a melting point depressant, such as boron. This melting point depressant is substantially in excess of that in the article and sufficient to provide melting of a portion of the mix at a processing temperature below the melting temperature of the article. The above filler mix is blended with the other constituents to form the repair coating which is applied to an article.
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公开(公告)号：EP0767867A1
公开(公告)日：1997-04-16
申请号：EP95925433.0
申请日：1995-06-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ROWE, Jon, G. , PIETRUSKA, Norman , PAWLACZYK, Richard, J. , WILCOX, Gilbert, B.
CPC classification number: B23P6/005 , F01D5/005 , Y10T29/49318 , Y10T29/4973 , Y10T29/49737
Abstract: The present invention relates to a method for refurbishing or restoring a turbine vane or other airfoil to restore a desired flow area. The method in one embodiment comprises the steps of: providing a plate to be used to restore the flow area on the airfoil; cutting the plate into a desired shape; machining a series of tapers into the cut plate so that the cut plate has a single region with a substantially uniform thickness; overlaying a surface of the airfoil with the pre-cut, pre-shaped plate so that the substantially uniform thickness region is positioned over that part of the airfoil where the flow area is to be restored; and attaching the pre-cut, pre-shaped plate to the airfoil. The refurbishment or restoration method further comprises heat treating the pre-cut, pre-shaped plate so that the plate softens and conforms to the shape of the airfoil surface.
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公开(公告)号：EP0593736A1
公开(公告)日：1994-04-27
申请号：EP93911137.0
申请日：1993-05-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： PIETRUSKA, Norman , KURPASKA, Michael, S.
CPC classification number: B23P6/002 , B23K35/3046 , B23P6/007 , C22F1/10 , F01D5/005
Abstract: L'invention concerne un procédé amélioré de réparation de constituants de moteur à turbine à gaz en superalliage à base de cobalt, consistant à appliquer un mélange d'une poudre d'alliage de base et d'une poudre d'alliage de base additionnée d'un agent d'abaissement du point de fusion sur la surface du constituant, puis à chauffer entre 2250 et 2300 °F afin de diffuser l'agent d'abaissement du point de fusion isothermiquement dans l'alliage de base. Ensuite on procède à une étape d'application d'un revêtement protecteur pendant laquelle on utilise un cycle de chauffage faisant vieillir le matériau de base. Le constituant obtenu présente des propriétés de fluage à haute température sensiblement supérieures à celles obtenues par le procédé de l'art antérieur. Le même cycle de température est également utile dans le traitement thermique initial de superalliage à base de cobalt, et on peut également l'utiliser dans la régénération de constituants ayant subi une exposition prolongée aux conditions de service du moteur.
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