Miglietti, US
Warren Miglietti, Jupiter, FL US
Patent application number | Description | Published |
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20100313419 | METHOD FOR RECONDITIONING A TURBINE BLADE - A method is provided for reconditioning a turbine blade. The turbine blade includes a blade airfoil which extends longitudinally and into the hollow inner space of which inserts can be inserted in the longitudinal direction of the blade for distribution and guiding cooling air which flows in the inner space. The inserts with a rib engage with sealing effect in a U-shaped sealing groove which is machined out on the inner wall of the blade airfoil and extend in the longitudinal direction of the blade. A damaged sealing groove is reconditioned by the sealing groove being removed from the inner wall of the blade airfoil, forming a slot, by an insertion strip, which is provided for sealing, being inserted into the slot, and by the insertion strip, which is seated in the slot, being connected in a materially bonding manner to the inner wall of the blade airfoil. | 12-16-2010 |
20120084980 | Extending Useful Life of a Cobalt-Based Gas Turbine Component - A method of extending the useable life of a gas turbine component fabricated from a cobalt-based alloy is disclosed. The method includes applying a rejuvenation process to the alloy where the alloy is placed in a protected atmosphere and heated to three different elevated temperatures and held at the elevated temperatures for approximately four hours each. Application of the rejuvenation process allows gas turbine components to be returned to service for at least one more service interval of approximately 24,000 operating hours. | 04-12-2012 |
Warren M. Miglietti, Greenville, SC US
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20090113706 | Craze crack repair of combustor liners - A method of repairing a turbine component with one or more craze cracks therein includes the steps of: (a) routing out the one or more cracks to form one or more routed areas; (b) applying a superalloy powder/paste in the one or more routed areas; (c) heat treating the component in place to form one or more repaired areas; and (d) blending the repaired area with adjacent areas of the component. | 05-07-2009 |
Warren Martin Miglietti, Greenville, SC US
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20080210741 | WELD REPAIR AS A COMBINED HEAT TREATMENT BRAZING PROCESS FOR METALLIC COMPONENTS - A method for welding and brazing a metallic component, such as, for example, a metallic component in a turbine, such as a bucket or blade. The method includes the steps of welding the metallic component to create a welded component; covering the welded component with a braze material to create a braze-covered welded component; and subjecting the braze-covered welded component to stress relief treatment. | 09-04-2008 |
20100059573 | PROCESS OF FILLING OPENINGS IN A COMPONENT - A process for filling openings, including blind holes, through-holes, and cavities, in high temperature components. The process entails forming a powder mixture by mixing particles of at least a base alloy and a second alloy that contains a sufficient amount of a melting point depressant to have a lower melting temperature than the base alloy. The powder mixture is combined with a binder and compacted to form a compacted preform, which is then heated to remove the binder and form a rigid sintered preform. The sintered preform is produced, or optionally is further shaped, to have a cross-sectional shape and dimensions to achieve a clearance of up to 200 micrometers with the opening, after which the preform is placed in the opening and diffusion bonded within the opening to form a brazement comprising the particles of the base alloy dispersed in a matrix formed by the second alloy. | 03-11-2010 |
20100237134 | Repair process for coated articles - A process for repairing a damaged portion of a thermal barrier coating on a turbine engine component includes sintering a mixture comprising particles of a bond coat and particles of a brazing alloy to form a composite preform; depositing a thermal barrier coating on the composite preform; contacting the composite preform with the deposited thermal barrier coating with an uncoated surface of the damaged portion of the turbine engine component; and heating the composite preform with the deposited thermal barrier coating to a temperature effective to form a brazed joint between the composite preform and the uncoated surface of the damaged portion of the turbine engine component. | 09-23-2010 |
20100260932 | COLD SPRAY METHOD OF APPLYING ALUMINUM SEAL STRIPS - A method for applying a seal strip to a surface of a turbine component by accelerating solid particles to a velocity sufficient to cause the solid particles to plastically deform and bond to the surface and each other when impacted on the surface, and impacting the solid particles on the surface so as to cause the solid particles to deform and bond to the surface and each other to form the seal strip on the surface. | 10-14-2010 |
20110135483 | COMPOSITE TURBINE BLADE AND METHOD OF MANUFACTURE THEREOF - A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice. | 06-09-2011 |
20130287587 | COMPOSITE TURBINE BLADE AND METHOD OF MANUFACTURE - A composite turbine blade and a method of manufacture thereof is disclosed. The composite turbine blade comprises a turbine blade portion comprising a first material and a first tip plate comprising a second material. The turbine blade portion has an exterior wall and an interior wall surrounding a hollow interior cavity, and a top surface extending from the exterior wall to the interior wall bounding an orifice that is fluidly connected to the hollow interior cavity. The first tip plate may be attached to the turbine blade along the top surface and extending from proximate the exterior wall of the turbine blade across the orifice to cover the orifice. | 10-31-2013 |
Warren Martin Miglietti, Jupiter, FL US
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20140259668 | TURBINE BLADE TIP REPAIR - A method for repairing a blade tip of a turbine blade based on a dual fusion weld process for portions of a tip plate and a mechanical locking bead over the tip plate. A damaged portion of blade is removed. The damaged portion is removed at an initial cut level. An undamaged portion of the turbine blade exists as a base below the initial cut level. A replacement section is rebuilt via laser cladding. The replacement section is machined to form a tip pocket. A tip plate is placed in the tip pocket. The tip plate comprises at least a first portion and a second portion. The tip plate is welded using a dual fusion weld process comprising a first weld process and a second weld process. A squealer tip is built using a welding process that forms a mechanical locking bead over the tip plate. | 09-18-2014 |
Warren Martin Andre Miglietti, Jupiter, SC US
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20110052386 | METHOD OF WELDING SINGLE CRYSTAL TURBINE BLADE TIPS WITH AN OXIDATION-RESISTANT FILLER MATERIAL - A method for depositing material on a turbine airfoil having a tip wall extending past a tip cap, wherein the tip wall includes a first alloy with a single crystal microstructure. The method includes: depositing a second alloy on at least a portion of the tip wall to form a repair structure, wherein a high temperature oxidation resistance of the second alloy is greater than a high temperature oxidation resistance of the first alloy, and wherein the repair structure has a crystallographic orientation that is substantially the same as a crystallographic orientation of the tip wall. | 03-03-2011 |
20110081480 | METHOD OF DEPOSITION OF METALLIC COATINGS USING ATOMIZED SPRAY - A method of coating a metal substrate such as the components in second and third stages of gas turbine engines in order to increase the oxidation and corrosion resistance of the metal substrate under high temperature operating conditions, the method including the steps of forming a powdered mixture of a high-melt superalloy or MCrAlY component, where M comprises Fe, Ni and/or Co, and a low-melt component containing about 2-5 wt. % silicon, boron or hafnium, applying the powdered mixture to the surface of the metal substrate at room temperature using an atomized spray to form a uniform surface coating, and then heating the coated substrate surface under vacuum conditions to a temperature in the range of about 1900° F. to 2275° F. to obtain a uniform coating composition providing oxidation resistance to the underlying substrate. | 04-07-2011 |
Warren Martin Andre Miglietti, Greenville, NC US
Patent application number | Description | Published |
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20090159645 | Brazing alloy compositions and methods - Various braze alloy compositions are described, along with methods for using them. In one instance, a boron-free, high-temperature braze alloy includes selected amounts of chromium, hafnium, and nickel. The braze alloy can be used, for example, as a component in a wide gap braze mixture where a higher or lower melting point superalloy and/or brazing powder is used. The braze alloys may permit joining or repairing of superalloy articles with complex shapes, and may be used in high temperature applications. In some other braze alloy embodiments, a nickel- or cobalt-based braze composition can contain selected amounts of boron, but includes restricted amounts of chromium. | 06-25-2009 |