REPAIR PROCEDURE FOR TURBINE MOTOR PARTS

LOCAL COATING FILM OF LOW-ACTIVITY ALUMINUM COMPOUND AND ITS PRODUCTION

PROBLEM TO BE SOLVED: To provide the coating film of an aluminum compd. capable of being easily applied on the selected part of a metallic article and highly resistant to oxidation and thermal fatigue. SOLUTION: The local coating film of a low-activity aluminum for a metallic article is formed by arranging a tape coating film material on a part of the article. The coating film material contains a binder, a halide activator, an aluminum source and an inert ceramic material. The coating film material and article are heated at 1800°F (982°C) to 2050°F (1121°C) for 4 to 7hr in an inert atmosphere. Consequently, the local coating film of a low-activity aluminum compd. having an aluminum coating film microstructure including two different regions, i.e., an inner diffusion region and an outer region contg. 20-28wt.% aluminum, is formed. COPYRIGHT: (C)1998,JPO ...

PROCEDURE FOR REPAIRING SINGLE CRYSTAL ARTICLES FROM SUPERALLOY ON NICKEL BASIS

REPARATURBESCHICHTUNG VON GEGENSTAENDEN AUS SUPERLEGIERUNGEN WIE GASTURBINENTRIEBWERKKOMPONENTEN

PROCEDURE FOR THE WELDING REPAIRING OF A COMPONENT FOR A TURBINE MOTOR WITH A REFRAKTÄREN METALLIC DOCUMENT MATERIAL

REPAIR PROCEDURE FOR SUPERALLOYS AND INSERTS

THERMAL TREATMENT AND PROCEDURE FOR REPAIRING A SUPERALLOY BODY ON COBALT BASIS

REFRACTORY METAL BACKING MATERIAL FOR WELD REPAIR

PURPOSE: A refractory metal backing material for weld repair is provided to obtain an improved method for repairing turbine engine components, obtain the method allowing welding over open cavities and not requiring extensive post welding blend processing or machining, and obtain method allowing re-establishment of internal cooling geometry. CONSTITUTION: A method for repairing a component comprises steps of placing a piece(16) of refractory metal material over an area of the component to be repaired, and depositing a repair filler metal material over the piece of refractory metal material in an amount sufficient to repair the component and subjecting the repair filler metal material to a welding treatment. The placing step comprises placing a piece of material formed from a material selected from the group comprising niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than the melting point of nickel, and alloys thereof over the area. © KIPO 2004 ...

Lokalisierte Aluminid-Beschichtung mit niedriger Aktivität

METHOD FOR REPAIRING SINGLE CRYSTAL NICKEL BASED SUPERALLOY MATERIAL

PURPOSE: A method for repairing a single crystal nickel based superalloy material is provided to minimize the degeneration of the mechanical property for components and maximize the boding strength of components formed from the single crystal nickel based superalloy material by rapidly cooling components and performing an aging treatment. CONSTITUTION: A method for repairing components formed from a single crystal nickel based superalloy is composed of steps of adhering a repairing alloy to at least one portion of components formed from the single crystal nickel based superalloy and heating components with the repairing alloy by the temperature which avoids the initial melting of the single crystal nickel based superalloy for recrystallization and repair areas. © KIPO 2003 ...

SUPERALLOY REPAIR METHODS AND INSERTS FOR MANUFACTURING, REMANUFACTURING, AND RESTORING NICKEL-BASED OR COBALT-BASED SUPERALLOY PARTS

PURPOSE: Methods for restoring and/or remanufacturing defective, worn, and/or damaged gas turbine engine components comprising a turbine and compressor blades and vanes, blade external air seals, and transition duct parts are provided. CONSTITUTION: A method for forming or remanufacturing a component to have an internal space comprises the steps of; forming a refractory metal based blocking element in situs such that at least a portion of the refractory metal based blocking element is formed within the internal space; allowing the blocking element to at least partially blocking inflow of a material into the internal space and add the material to the component by at least one of welding, laser cladding, and diffusion brazing; and removing the blocking element. A method for repairing an article comprises the steps of: performing diffusion repair using a melting point depressant; and using a sacrificial refractory metal-based paste as a sink for the melting point depressant. A method for adding ...

METHODE ZUR REPARATUR DER STRÖMUNGSLEITFLÄCHEN VON TURBINENLEITSCHAUFELN

REPAIRING METHOD OF TURBINE ENGINE PART

(57)【要約】 【課題】 タービンエンジン部品の修理方法を提供す る。 【解決手段】 エアフォイルを有したベーンやブレード などのタービンエンジン部品の本発明の修理方法、断熱 コーティングの破砕あるいは酸化による損傷を示す部品 の各部分から酸化堆積物を除去すること、部品からセラ ミック断熱層を除去すること、欠けキズやへこみ、ある いは割れが見られる部品の表面をブレンディングするこ とを有してなる。部品が劣化したアルミニウム領域を有 する場合、劣化した領域は除去、あるいは補充される。 更に部品の先端部は、損傷している場合には修復され、 先端部に研摩が施されて部品のカッティング能力が回復 される。その後、セラミックコーティングが部品に施さ れる。

NICKEL-BASED ALLOY FOR REPAIR, AND METHOD FOR REPAIRING CRACK IN NICKEL-BASED ALLOY COMPONENT

PROBLEM TO BE SOLVED: To provide a repair material which can be used for repairing a crack wider than approx. 0.010 inches (0.025 cm). SOLUTION: The invented nickel-based alloy contains a mixture of approx. 40-60 wt.% nickel-based alloy for first brazing containing boron, approx. 15-35 wt.% first nickel-based filler material, and a blend of second nickel-based filler material and low-melting-point eutectic nickel-based alloy for brazing as the balance. COPYRIGHT: (C)2008,JPO&INPIT ...

Reparaturverfahren für Superlegierungen und Inserts

REPAIRING METHOD OF TURBINE ENGINE PART

PURPOSE: A method for repairing parts of a turbine engine is provided to repair the hardware components of the turbine engine such as a vane and a blade efficiently and effectively. CONSTITUTION: A repairing method of a turbine engine part such as a vane and a blade having the airfoil comprises steps to remove the oxide deposit from respective portions of a part indicating damage by crushing or oxidation of heat insulating coating, to remove a ceramic heat insulating layer from the part, and to blend a surface of the part generating nicks, dents and cracks. When the part has a deteriorated aluminum area, the deteriorated area is removed or replenished. A tip part of the part is also recovered when the part is damaged, and the cutting capacity of the part is restored by applying the polishing agent to the tip part. Afterwards, ceramic coating is applied to the part. © KIPO 2004 ...

METHODE ZUR REPARATUR DER STRÖMUNGSLEITFLÄCHEN VON TURBINENLEITSCHAUFELN

Nickel alloy for repairs

A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.

Repair of single crystal nickel based superalloy article

The present invention relates to a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment.

Nickel alloy for repairs

A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.

Nickel Alloy For Repairs

A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy. 116-. (canceled)17. A material for repairing a crack in a nickel based alloy component consisting essentially of about 7.0 to 10.0 wt % chromium , about 4.0 to 7.0 wt % tungsten , about 3.0 to 6.0 wt % aluminum , about 1.0 to 5.0 wt % tantalum , about 0.5 to 3.0 wt % boron , about 9.0 to 11.0 wt % cobalt , about 0.5 to 2.0 wt % molybdenum , up to about 2.5 wt % rhenium , about 0.5 to 2.5 wt % hafnium , up to 1.0 wt % titanium , up to 0.03 wt % yttrium , and the balance nickel.18. The material according to claim 17 , wherein said chromium content is about 8.5 to 9.5 wt %.19. The material according to claim 17 , wherein said tungsten content is about 5.0 to 6.2 wt %.20. The material according to claim 17 , wherein said aluminum content is about 4.0 to 5.0 wt %.21. The material according to claim 17 , wherein said titanium content is about 0.15 to 0.4 wt %.22. The material according to claim 17 , wherein said tantalum content is about 3.0 to 4.0 wt %.23. The material according to claim 17 , wherein said boron content is about 1.0 to 1.5 wt %.24. The material according to claim 17 , wherein said cobalt content is about 10 wt % to 11 wt %.25. The material according to claim 17 , wherein said molybdenum content is about 0.9 to 1.3 wt %.26. The material according to claim 17 , wherein said rhenium content is about 1.0 to 2.0 wt %.27. The material according to claim 17 , wherein said hafnium content is about 1.0 to 1.3 wt %.28. The material according to claim 17 , wherein said yttrium content is about 0.01 to 0.02 wt %. (1) Field of the InventionThe present invention relates to a nickel base repair alloy which may be used to repair workpieces, such as turbine ...

Verfahren zum Schweissreparieren einer Komponente für einen Turbinenmotor mit einem refraktären metallischen Unterlagenmaterial

REPARATURBESCHICHTUNG VON GEGENSTAENDEN AUS SUPERLEGIERUNGEN WIE GASTURBINENTRIEBWERKKOMPONENTEN

Low temperature diffusion braze repair of single crystal components

The present invention is directed to a process for repairing cracks in a turbine engine component. The process comprises the steps of providing a component, preferably formed from a single crystal nickel based material, with at least one crack, applying a repair alloy composition containing a single crystal nickel based alloy, a first nickel based braze alloy and a second nickel based braze alloy to the crack(s), and subjecting the component with the applied repair alloy composition to a thermal cycle to diffuse the repair alloy composition into the crack(s).

Lokalisierte Aluminid-Beschichtung mit niedriger Aktivität

Verfahren zum Reparieren von Einkristallgegenständen aus Superlegierung auf Nickelbasis

Method for repairing superalloy components using inserts

A method for forming or remanufacturing a component to have an internal space. A refractory metal blocking element is formed, in situ, with at least a portion to be within the internal space. A material is added by at least one of welding, laser cladding, and diffusion brazing, the blocking element at least partially blocking entry of the material to the internal space. The blocking element is removed.

Repair and reclassification of superalloy components

Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 weight percent of a low melting point alloy and about 81.1-95 weight percent of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 weight percent of a low melting point alloy and about 70-85 weight percent of a base material. These materials can be used to repair surface defects and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These materials create robust repaired components having a dense, isothermally solidified structure having minimal borides and a high re-melt temperature.

WÄRMEBEHANDLUNG UND VERFAHREN ZUM REPARIEREN EINES SUPERLEGIERUNGSKÖRPERS AUF KOBALT-BASIS

WÄRMEBEHANDLUNG UND VERFAHREN ZUM REPARIEREN EINES SUPERLEGIERUNGSKÖRPERS AUF KOBALT-BASIS

Verfahren zum Reparieren von Einkristallgegenständen aus Superlegierung auf Nickelbasis

Instandsetzungsverfahren für Turbinenmotorenteilen

Refractory metal backing material for weld repair

The present invention relates to a method for repairing components such as blades used in turbine engines. The method comprises the steps of placing a piece of refractory metal material over an area of the component to be repaired and depositing a repair filler metal material over the piece of refractory material in an amount sufficient to repair the component and welding the repair filler metal material in place. The refractory metal material may be selected from the group consisting of niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than the melting point of nickel, and alloys thereof and may be uncoated or coated.

REPAIR AND RECLASSIFICATION OF SUPERALLOY COMPONENT

PROBLEM TO BE SOLVED: To provide a repairing method of a gas turbine engine component to be replaced simultaneously with repair and reclassification, and a material used for the component. SOLUTION: Novel materials and methods for repairing/reclassifying superalloy components are described herein. These materials are non-traditional blends of materials having a much higher base material content than traditional repair/reclassification materials. In embodiments used to repair/reclassify nickel-based components, these materials may comprise about 5-18.9 wt.% of a low melting point alloy and about 81.1-95 wt.% of a base material. In embodiments used to repair/reclassify cobalt-based components, these materials may comprise about 15-30 wt.% of a low melting point alloy and about 70-85 wt.% of a base material. These materials can be used to repair surface defects of a component and/or build up worn or eroded areas of a component to meet precise dimensional and metallurgical requirements. These ...

COMPOSITION FOR CRACK REPAIR AND CRACK REPAIR METHOD

PROBLEM TO BE SOLVED: To provide a crack repair method of a turbine engine component without adversely affecting material characteristics. SOLUTION: In the crack repair method of a turbine engine component, the component is preferably composed of a single-crystal nickel material and has at least one crack. An alloy composition for repair, which contains a single-crystal nickel alloy, a first nickel brazing alloy and a second nickel brazing alloy, is applied to the crack, and the component to which the alloy composition for repair has been applied is exposed to a heat cycle to enhance diffusion of the alloy composition for repair into the crack. COPYRIGHT: (C)2007,JPO&INPIT ...

Low temperature diffusion braze repair of single crystal components

The present invention is directed to a process for repairing cracks in a turbine engine component. The process comprises the steps of providing a component, preferably formed from a single crystal nickel based material, with at least one crack, applying a repair alloy composition containing a single crystal nickel based alloy, a first nickel based braze alloy and a second nickel based braze alloy to the crack(s), and subjecting the component with the applied repair alloy composition to a thermal cycle to diffuse the repair alloy composition into the crack(s).

Method for repairing turbine engine components

The present invention relates to a method for repairing turbine engine components, such as vanes and blades, which have airfoils. The method broadly comprises removing oxidation debris from portions of the component by blending areas exhibiting thermal barrier coating spall and/or oxidation damage, removing a ceramic insulating layer from the component, and blending surfaces of the component where nicks, dents, and/or cracks are located. If the component has a depleted aluminum zone, the depleted zone is either removed or replenished. Further, a tip portion of the component, if damaged, is restored and tip abrasives are applied to restore the component's cutting ability. Thereafter, a ceramic coating is applied to the component.

METHOD FOR REPAIRING SUPERALLOY ARTICLE, AND INSERT MEMBER

PROBLEM TO BE SOLVED: To provide a method for forming or regenerating parts such as components of a gas turbine engine so as to have internal spaces. SOLUTION: Insert material 70 is disposed in an internal space as the blocking element and fixed with paste beads 82. After that, supplementary member 90 is piled up by laser cladding or diffusion brazing etc. COPYRIGHT: (C)2007,JPO&INPIT ...

REPAIR OF SINGLE CRYSTAL NICKEL BASED SUPERALLOY ARTICLE

PROBLEM TO BE SOLVED: To provide an improved method of repairing a single crystal nickel based superalloy article so that the deterioration of mechanical characteristic is minimized. SOLUTION: This is a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment. COPYRIGHT: (C)2003,JPO ...

METHOD FOR REPAIRING COMPONENTS

PROBLEM TO BE SOLVED: To provide an improved method for repairing components of a turbine engine. SOLUTION: The method for repairing the components such as blades used in the turbine engine comprises the steps of: placing a piece 16 of a refractory metal material over an area 12 of the component to be repaired; depositing a repair filler metal material 20 over the piece 16 of a refractory metal material in an amount sufficient to repair the component; and welding the repair filler metal material 20 in place. The refractory metal material may be selected from the group consisting of niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than that of nickel, and alloys thereof and may be uncoated or coated. COPYRIGHT: (C)2004,JPO ...

Nickel alloy for repairs

A nickel base repair alloy comprises a blend of about 40 to 60 wt% of a first nickel based braze alloy containing boron, about 15 to 35 wt% of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy.

Superalloy repair methods and inserts

A method for forming or remanufacturing a component to have an internal space. A refractory metal blocking element is formed, in situ, with at least a portion to be within the internal space. A material is added by at least one of welding, laser cladding, and diffusion brazing, the blocking element at least partially blocking entry of the material to the internal space. The blocking element is removed.

Heat treatment and repair of cobalt-base superalloy articles

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.

Low activity localized aluminide coating

The invention includes a low activity localized aluminide coating for a metallic article made by positioning a coating material, preferably in the form of a tape, on a portion of the article. The coating material comprises a binder, a halide activator, an aluminum source, and an inert ceramic material. The coating material and the article are heated in an inert atmosphere between about 1800° F. (982° C.) and about 2050° F. (1121° C.) for between about four and about seven hours thereby producing a low activity localized aluminide coating having an outward diffusion aluminide coating microstructure characterized by two distinct zones, an inner diffusion zone and an outer zone including between about 20-28 percent, by weight, aluminum.

Turbine vane flow area restoration method

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.

Method of weld repairing a component with a refractory metal backing material

The present invention relates to a method for repairing components such as blades used in turbine engines. The method comprises the steps of placing a piece of refractory metal material (16) over an area of the component to be repaired (12) and depositing a repair filler metal material (20) over the piece of refractory material (16) in an amount sufficient to repair the component and welding the repair filler metal material (20) in place. The refractory metal material (16) may be selected from the group consisting of niobium, tantalum, molybdenum, tungsten, a metal having a melting point higher than the melting point of nickel, and alloys thereof and may be uncoated or coated.

Low temperature diffusion braze repair of single crystal components

The present invention is directed to a process for repairing cracks in a turbine engine component. The process comprises the steps of providing a component, preferably formed from a single crystal nickel based material, with at least one crack, applying a repair alloy composition containing a single crystal nickel based alloy, a first nickel based braze alloy and a second nickel based braze alloy to the crack(s), and subjecting the component with the applied repair alloy composition to a thermal cycle to diffuse the repair alloy composition into the crack(s).

Repair of single crystal nickel based superalloy article

The present invention relates to a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment.

Repair of a single crystal nickel based superalloy article

The present invention relates to a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment.

Reparaturverfahren für superlegierungen und inserts

Instandsetzungsverfahren für turbinenmotorenteilen

Repair and reclassification of superalloy components

Repair of a single crystal nickel based superalloy article

The present invention relates to a method for repairing components formed from a single crystal nickel based superalloy. The method comprises the steps of applying a repair alloy to at least one portion of a component formed from the single crystal nickel based superalloy and heating the component with the repair alloy thereon to a temperature that avoids recrystallization and repair zone incipient melting of the single crystal nickel based superalloy. Following the heating step, the component is preferably rapidly cooled and subjected to an aging treatment.

Verfahren zum reparieren von einkristallgegenständen aus superlegierung auf nickelbasis