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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：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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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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