| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | METHODS AND SYSTEMS FOR JOINING MATERIALS | US13631162 | 2012-09-28 | US20140093657A1 | 2014-04-03 | Qi Zhao; Robert John Zabala; Laurent Cretegny; Jeffrey Jon Schoonover; Mark Kevin Meyer; Keith Anthony Lauria; William R. Catlin |
| A method is provided for joining a filler material to a substrate material. The method includes melting the filler material within a melting chamber of a crucible such that the filler material is molten. The crucible has an outlet fluidly connected to the melting chamber. The method also includes holding the filler material within the melting chamber of the crucible by applying a first pressure differential across the outlet of the crucible, and releasing the filler material from the melting chamber of the crucible by applying a second pressure differential across the outlet of the crucible to deliver the filler material to a target site of the substrate material. The second pressure differential has a different value than the first pressure differential. | ||||||
| 82 | Method for casting a component | US13267181 | 2011-10-06 | US08485243B2 | 2013-07-16 | Christopher A. Kinney |
| A cast component having localized areas of improved physical properties is disclosed. The component may initially be produced having a void portion in a predetermined area requiring improved physical properties. A second molten material may be added to the void portion such that it chemically bonds to the void portion. The component may then be finished such to a final shape with a localized area of improved physical properties. | ||||||
| 83 | ISOTHERMAL STRUCTURAL REPAIR OF SUPERALLOY COMPONENTS INCLUDING TURBINE BLADES | US13414751 | 2012-03-08 | US20130115092A1 | 2013-05-09 | Kazim Ozbaysal |
| Structural repair of cracks and other defects in superalloy components, such as steam or gas turbine blades in stationary or aero gas turbines, are performed by heating the blade substrate to an isothermal hold temperature below the substrate's incipient melting point and filling the crack with molten superalloy filler material. The molten filler solidifies into a casting and bonds with the component substrate at the isothermal hold temperature. Heat treatment processes are completed, so that the former crack is filled with cast superalloy material having identical or similar structural properties as the adjoining substrate superalloy material. The casting repair method may be utilized universally for all types of superalloy component defects, including those previously repaired by cosmetic, lower strength welding or brazing methods. | ||||||
| 84 | Stirrer organ in composite construction | US12928875 | 2010-12-22 | US20120163118A1 | 2012-06-28 | Frank Hoffmann |
| The invention relates to a stirrer organ (1) in composite construction comprised of a metallic part (4) and a hybrid casting (9), with the hybrid casting (9) being fixed to the metallic part (4) by means of at least one anchoring element which forms at least one back-cutting in the hybrid casting (9). Furthermore, the present invention relates to a method for rehabilitating a damaged metallic stirrer organ which when applied provides a rehabilitated stirrer organ (1) in composite construction. The invention tackles the task of creating a stirrer organ (1) in hybrid construction which features a largest possible metallic part (4) because higher strength can hereby be achieved. This task is inventively solved in that the anchoring element is provided with a perforated plate (5) which is spot-wise fastened to the metallic part (4) and which is arranged at least partly at a small distance to the surface of the metallic part (4) so as to configure the at least one back-cutting. | ||||||
| 85 | Elimination of Shrinkage Cavity in Cast Ingots | US13333469 | 2011-12-21 | US20120160442A1 | 2012-06-28 | Mark Anderson; Todd F. Bischoff; James Boorman; Wayne J. Fenton; David Sinden; John Steven Tingey; Robert Bruce Wagstaff |
| An exemplary embodiment provides a method of eliminating a shrinkage cavity in a metal ingot cast by direct chill casting. The method involves casting an upright ingot having an upper surface at an intended height. Upon completion of the casting, the lower tip of the spout is maintained below the molten metal near the center of the upper surface. The metal flow through the spout is terminated and a partial shrinkage cavity is allowed to form as metal of the ingot shrinks and contracts. Before the partial cavity exposes the lower tip of the spout, the cavity is preferably over-filled with molten metal, while avoiding spillage of molten metal, and then the flow of metal through the spout is terminated. These steps are repeated until no further contraction of the metal causes any part of the upper surface to contract below the intended ingot height. | ||||||
| 86 | METAL MOLD REPAIR METHOD AND METAL MOLD REPAIR PASTE AGENT | US13040115 | 2011-03-03 | US20120058004A1 | 2012-03-08 | Michiharu HASEGAWA; Noriyuki Miyazaki; Masafumi Nakamura; Naoji Yamamoto; Kazuo Ueda |
| Providing a metal mold repair method and a metal mold repair paste agent which are capable of repairing cracks with simple work.A repair paste agent containing components that become an alloy is directly applied to a surface of a metal mold having a crack so as to cover the crack part, subsequently a surface of the repair paste agent is coated with an oxidation inhibitor and the repair paste agent is made to penetrate the inside of the crack by heating and becomes an alloy, thereby filling up the crack. | ||||||
| 87 | Method For Casting Component | US13267181 | 2011-10-06 | US20120024491A1 | 2012-02-02 | Christopher A. Kinney |
| A cast component having localized areas of improved physical properties is disclosed. The component may initially be produced having a void portion in a predetermined area requiring improved physical properties. A second molten material may be added to the void portion such that it chemically bonds to the void portion. The component may then be finished such to a final shape with a localized area of improved physical properties. | ||||||
| 88 | Restoration process for porosity defects in high pressure die cast engine blocks | US10358480 | 2003-02-05 | US07188416B1 | 2007-03-13 | Douglas M. Woehlke; Raymond J. Donahue; Kevin R. Anderson |
| A restoration process for restoring surface porosity defects in engine blocks cast using a high pressure die cast method. The areas of an engine block having surface porosity defects are identified and the areas not containing surface porosity defects are masked using an adhesive, reusable, rubberized mask. The masked surface is subsequently cleaned and a metal spray is applied to the surface porosity defects. The mask is removed and the restored surface porosity defects are hand finished to create an engine block having less than 0.05% surface porosity. | ||||||
| 89 | Methods for repairing turbine engine components | US11184154 | 2005-07-19 | US20070039175A1 | 2007-02-22 | Michael Rucker; Bhupendra Gupta; Nripendra Das; David Budinger |
| A method for repairing a turbine component includes identifying a crack in a surface of the component and applying a fluoride mixture to the surface of the component containing the crack. The method also includes exposing the portion of the component including the fluoride mixture to a controlled atmosphere and returning the repaired surface of the component to predetermined dimensions. | ||||||
| 90 | Method of removing casting defects | US10923023 | 2004-08-23 | US07169242B2 | 2007-01-30 | John Fernihough; Matthias Hoebel; Maxim Konter |
| A method for removing casting defects (5) from an article (1) with an oriented microstructure can include locating at least one casting defect (5) and melting the casting defect (5) locally by a heat source (7) to a depth at least as great as the casting defect (5) itself. The molten material can then be solidified epitaxially with respect to the surrounding oriented microstructure of the article (1) in a way that the resulting solidified area is substantially free of any defect. | ||||||
| 91 | Method of removing casting defects | US10923023 | 2004-08-23 | US20050067065A1 | 2005-03-31 | John Fernihough; Matthias Hoebel; Maxim Konter |
| A method for removing casting defects (5) from an article (1) with an oriented microstructure can include locating at least one casting defect (5) and melting the casting defect (5) locally by a heat source (7) to a depth at least as great as the casting defect (5) itself. The molten material can then be solidified epitaxially with respect to the surrounding oriented microstructure of the article (1) in a way that the resulting solidified area is substantially free of any defect. | ||||||
| 92 | System and method for repairing cast articles | US09725738 | 2000-11-29 | US06615470B2 | 2003-09-09 | Reed Roeder Corderman; Shyh-Chin Huang; Thomas Robert Raber; Don Mark Lipkin; Raymond Alan White; Sidney Perham Young; Melvin Robert Jackson; Peter William Schilke |
| A system and method for repairing defects such as bumper holes, cracks, freckles and inclusions, in a cast article, such as a turbine component. The system comprises a device for locating a defect in a cast article, a repair material that is disposable at a defect site, at least one heat source capable of heating the repair material and a portion of the cast article to a molten state. The method of using the system comprises locating a defect in the cast article, providing a repair material to the defect site, melting the repair material and cast article at the defect site, and cooling the molten repair material and portion of the casting article such that they resolidify and fuse together. The method may further comprise removing a portion of the cast article at the defect site, removal of excess repair material and inspecting the cast article following repair of the defect. | ||||||
| 93 | Methods of making wear resistant tooling systems to be used in high temperature casting and molding | US10278374 | 2002-10-23 | US20030106198A1 | 2003-06-12 | James E. Kowalczyk; Rick J. Bolyea |
| A method of making or reconstituting a steel tooling used in the processing of high temperature molten material includes machining an undercut surface in the tooling which provides an inset edge trapping receiving surface with an end marginal wall. The undercut is prepared for the reception of a barrier layer which fills the undercut and merges with the tooling surface bordering the undercut. Then a chemical barrier providing wear resisting coating surface which is thermally expansively and contractibly compatible with the tooling surface to avoid fracturing stresses due to differential rates of thermal expansion and contraction at elevated temperatures is fused to the receiving surface. | ||||||
| 94 | Solidification of an article extension from a melt using a ceramic mold | US588587 | 1996-01-18 | US5904201A | 1999-05-18 | Melvin Robert Jackson; Bernard Patrick Bewlay; Wayne Alan Demo; Stephen Joseph Ferrigno |
| A method for forming integral extensions on the end of directionally oriented, superalloy articles, such as airfoil blading members or other components used in gas turbine or other turbine engines. An extension is formed directly on an article by dipping a portion or end of the article into a molten bath of a compatible alloy, followed by withdrawal of the end under controlled conditions sufficient to cause an integral extension to solidify on the article. A ceramic mold is utilized over the dipped end of the article with a mold cavity that generally defines the shape of the extension to be formed. The mold may be formed in situ, or preformed and attached to the subject article. Extensions formed by the method of this invention have a microstructure that is continuous and compatible with that of the article. Such microstructures may include epitaxial growth of the extension from the microstructure of the article. The method establishes a temperature gradient within the article during solidification that may be further controlled by auxiliary heating and/or cooling of the article and/or extension during the practice of the method. | ||||||
| 95 | Method for replacing blade tips of directionally solidified and single crystal turbine blades | US892034 | 1997-07-14 | US5822852A | 1998-10-20 | Bernard Patrick Bewlay; Melvin Robert Jackson |
| A method for repairing a blade tip of a turbine blade of a gas turbine engine. The method is particularly directed to replacing the squealer tip (14) of a directionally solidified (DS) or single crystal (SX) turbine blade (10), and can be carried out using a brazing or welding technique. The method generally entails the step of machining the tip (14) to remove any damaged, worn, oxidized or eroded portions thereof sustained by the blade (10) during engine operation. A DS or SX superalloy replacement tip (18) is then placed on the surface generated by the machining operation. If a brazing operation is used, a brazing alloy composition (16) is first applied to the blade tip or replacement tip (18) prior to placement of the replacement tip (18). The brazing alloy composition (16) is composed of at least two alloys, one of which having a melting point lower than the recrystallization temperature and solvus temperature of the superalloy of the turbine blade (10), such that heating causes the brazing alloy composition (16) to flow and thereby join the replacement tip (18) to the blade tip of the turbine blade (10). Alternatively, if a welding operation is employed, the joining operation entails transmitting current through the turbine blade (10) and replacement tip (18) to resistance weld the replacement tip (18) to the blade tip of the blade (10). | ||||||
| 96 | Method for forming an article extension by melting of a mandrel in a ceramic mold | US672154 | 1996-06-27 | US5673744A | 1997-10-07 | Bernard Patrick Bewlay; Melvin Robert Jackson; Ann Melinda Ritter |
| An extension is formed directly on an article by melting a portion or end of the article having an attached integral mandrel within a ceramic mold, followed by cooling of the end under controlled conditions sufficient to cause an integral extension to solidify on the article. A ceramic mold is attached on the end of the article over the integral mandrel with a mold cavity that generally defines the shape of the extension to be formed. The mold may be formed in situ on the mandrel, or preformed and attached to the subject article over the mandrel. Extensions formed by the method of this invention have a microstructure that is continuous and compatible with that of the article. Such microstructures may include epitaxial growth of the extension from the microstructure of the article. The method establishes a temperature gradient within the article during solidification that may be further controlled by auxiliary heating and/or cooling of the article and/or extension during the practice of the method. | ||||||
| 97 | Process and apparatus for repair of drive blades such as turbine blades | US1583 | 1993-01-06 | US5261480A | 1993-11-16 | Jurgen Wortmann; Fritz Staub; Bruno Walser |
| A process and apparatus for the repair of single-crystal drive blades, such as turbine blades, in which a sound portion of the blade is inserted into an open bottom of a casting mold in communication with a casting cavity in the mold adopted to the shape of the blade. The molten metal is then cast into the mold to unite with the sound portion and an epitaxial single-crystal solidification of the melt is produced on the sound portion to form the entire blade. A part of the sound portion has an outer surface layer thereof removed to expose a core region which is constituted of substantially pure single crystal material prior to casting. The sound part is secured in a holder which is coupled to the casting mold for only a matter of seconds before the molten metal is cast into the mold. | ||||||
| 98 | Method of repairing one-piece pulverizing roller assembly | US596930 | 1990-10-12 | US5079819A | 1992-01-14 | Robert L. Parham |
| A one-piece pulverizing mill roller assembly and method of rebuilding the same. The roller assembly comprises a body, an integral hub portion and an integral circumferential outside tread portion which mates with an annular groove in a grinding table. The roller assembly is composed of a relatively lower hardness steel which will accept hard surface weld beads to rebuild the circumferential outside tread portion as it wears. The rebuilding can be performed in-place in the pulverizing mill. | ||||||
| 99 | Method of repairing defective pump casings | US8797261 | 1961-02-08 | US3136013A | 1964-06-09 | FRANCIS FUNK CHARLES; EUGENE FUNK JOHN; YORK JACK L; BOURGEOIS FUNK MARGUERITE; FUNK GUY L; FUNK MARGARE M |
| 100 | Method of resurfacing worn machine parts | US41413154 | 1954-03-04 | US2798269A | 1957-07-09 | MONKOWSKI HENRY V |
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