Patents by Inventor Peter Wayte
Peter Wayte has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20200113704Abstract: A Charcot trabecular system and method is provided. The Charcot trabecular system embodies a threaded bolt-like fastener, wherein a middle portion of the shank of the systemic fastener is made of a porous material, while the remaining portions of the systemic fastener denser provides a denser material. The porous shank portion may be made of material dimensioned and adapted to pass blood and particulate bone matter therethrough. As a result, in use when connecting bones together, the denser material provides for stabilization and structural support to the associated damaged joint, while the porous shank facilitates optimal bone healing via boney ingrowth and bone ongrowth through and around the implanted systemic fastener.Type: ApplicationFiled: October 10, 2019Publication date: April 16, 2020Inventors: Ryan Pereira, Peter Wayte
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Patent number: 7897103Abstract: An elongated rod assembly is made by preparing a plurality of rods. Each rod is prepared by the steps of furnishing at least one nonmetallic precursor compound, thereafter chemically reducing the precursor compounds to produce the metallic material, and thereafter consolidating the metallic material to form the rod, wherein the rod has a rod length equal to the assembly length. The rods are bundled together to form a bundled rod assembly. The rod assembly may be used as a consumable feedstock in a melting-and-casting operation.Type: GrantFiled: May 27, 2005Date of Patent: March 1, 2011Assignee: General Electric CompanyInventors: Eric Allen Ott, Andrew Philip Woodfield, Clifford Earl Shamblen, Peter Wayte, Mike Eugene Mechley
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Publication number: 20090159161Abstract: A Ti-6Al-4V-0.2O (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2¼ inches. The forged article is heat treated by solution heat treating at a temperature of from about 50° F. to about 85° F. below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900° F. to about 1350° F.Type: ApplicationFiled: December 22, 2008Publication date: June 25, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Peter WAYTE, Ming Cheng LI
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Publication number: 20090032152Abstract: A titanium-alloy article is produced by providing a workpiece of an alpha-beta titanium alloy having a beta-transus temperature, and thereafter mechanically working the workpiece at a mechanical-working temperature above the beta-transus temperature. The mechanically worked workpiece is solution heat treated at a solution-heat-treatment temperature of from about 175° F. below the beta-transus temperature to about 25° F. below the beta-transus temperature, quenched, overage heat treated at an overage-heat-treatment temperature of from about 400° F. below the beta-transus temperature to about 275° F. below the beta-transus temperature, and cooled from the overage-heat-treatment temperature.Type: ApplicationFiled: October 10, 2008Publication date: February 5, 2009Applicant: GENERAL ELECTRIC COMPANYInventors: Andrew Philip WOODFIELD, Wesley Douglas PRIDEMORE, Bernard Harold LAWLESS, Nancy Ann SULLIVAN, Peter WAYTE, Michael James WEIMER, Thomas Froats BRODERICK
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Patent number: 7481898Abstract: A Ti-6Al-4V-0.2O (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2¼ inches. The forged article is heat treated by solution heat treating at a temperature of from about 50° F. to about 75° F. below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900° F. to about 1000° F. The resulting machined gas turbine engine component has a 0.2 percent yield strength of from about 120 ksi to about 140 ksi at its centerline, and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about ½ inch below a surface thereof.Type: GrantFiled: October 24, 2003Date of Patent: January 27, 2009Assignee: General Electric CompanyInventors: Peter Wayte, Ming Cheng Li
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Patent number: 7449075Abstract: A titanium-alloy article is produced by providing a workpiece of an alpha-beta titanium alloy having a beta-transus temperature, and thereafter mechanically working the workpiece at a mechanical-working temperature above the beta-transus temperature. The mechanically worked workpiece is solution heat treated at a solution-heat-treatment temperature of from about 175° F. below the beta-transus temperature to about 25° F. below the beta-transus temperature, quenched, overage heat treated at an overage-heat-treatment temperature of from about 400° F. below the beta-transus temperature to about 275° F. below the beta-transus temperature, and cooled from the overage-heat-treatment temperature.Type: GrantFiled: June 28, 2004Date of Patent: November 11, 2008Assignee: General Electric CompanyInventors: Andrew Philip Woodfield, Wesley Douglas Pridemore, Bernard Harold Lawless, Nancy Ann Sullivan, Peter Wayte, Michael James Weimer, Thomas Froats Broderick
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Publication number: 20080124210Abstract: A rotor assembly for a turbine is provided. The rotor assembly includes a first portion of a rotor component forged from a first material. The first material is processed using a first process. The rotor assembly also includes a second portion of the rotor component separately forged from a second material that is the same material as the first material. The second portion is processed using a second process and is coupled to the first portion at a first axial position. A method for fabricating a rotor assembly for a turbine is also provided.Type: ApplicationFiled: November 28, 2006Publication date: May 29, 2008Inventors: Peter Wayte, Brian Francis Mickle, Andrew Philip Woodfield
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Patent number: 7249412Abstract: A BLISK having a damaged blade, with a repair region that has a thickness less than a specified thickness as a result of damage during manufacture or prior service, is repaired by depositing repair metal onto the repair region to increase its thickness to greater than its specified thickness dimension. Only the repair region is stress relieved by heating the repair region to a stress-relieving temperature of from about 1150° F. to about 1250° F. for a time of at least about 1 hour. The intentional manipulation of microstructure in only the thinner airfoil sections allows multiple repairs, which are not possible in the thicker sections of the BLISK. An alpha-case thickness of repair metal, preferably of at least about 0.0002 inches of repair metal, is removed from a surface of the repair region.Type: GrantFiled: May 25, 2004Date of Patent: July 31, 2007Assignee: General Electric CompanyInventors: Peter Wayte, Thomas Froats Broderick
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Patent number: 7097783Abstract: A process for detecting an aluminum-based material deposited onto a titanium-based gas turbine engine component during engine operation is disclosed. The process comprises immersing at least a portion of the titanium-based component, which has been subjected to engine operation, into an acid solution to form an etched component. The acid solution comprises sodium fluoride, sulphuric acid and water. The etched component may then be removed from the solution and visually inspected for dark areas in contrast to light areas, the dark areas indicating deposited aluminum-based material.Type: GrantFiled: July 17, 2003Date of Patent: August 29, 2006Assignee: General Electric CompanyInventor: Peter Wayte
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Publication number: 20050284549Abstract: A titanium-alloy article is produced by providing a workpiece of an alpha-beta titanium alloy having a beta-transus temperature, and thereafter mechanically working the workpiece at a mechanical-working temperature above the beta-transus temperature. The mechanically worked workpiece is solution heat treated at a solution-heat-treatment temperature of from about 175° F. below the beta-transus temperature to about 25° F. below the beta-transus temperature, quenched, overage heat treated at an overage-heat-treatment temperature of from about 400° F. below the beta-transus temperature to about 275° F. below the beta-transus temperature, and cooled from the overage-heat-treatment temperature.Type: ApplicationFiled: June 28, 2004Publication date: December 29, 2005Applicant: GENERAL ELECTRIC COMPANYInventors: Andrew Woodfield, Wesley Pridemore, Bernard Lawless, Nancy Sullivan, Peter Wayte, Michael Weimer, Thomas Broderick
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Publication number: 20050274008Abstract: A BLISK having a damaged blade, with a repair region that has a thickness less than a specified thickness as a result of damage during manufacture or prior service, is repaired by depositing repair metal onto the repair region to increase its thickness to greater than its specified thickness dimension. Only the repair region is stress relieved by heating the repair region to a stress-relieving temperature of from about 1150° F. to about 1250° F. for a time of at least about 1 hour. The intentional manipulation of microstructure in only the thinner airfoil sections allows multiple repairs, which are not possible in the thicker sections of the BLISK. An alpha-case thickness of repair metal, preferably of at least about 0.0002 inches of repair metal, is removed from a surface of the repair region.Type: ApplicationFiled: May 25, 2004Publication date: December 15, 2005Applicant: General Electric CompanyInventors: Peter Wayte, Thomas Broderick
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Publication number: 20050223849Abstract: An elongated rod assembly is made by preparing a plurality of rods. Each rod is prepared by the steps of furnishing at least one nonmetallic precursor compound, thereafter chemically reducing the precursor compounds to produce the metallic material, and thereafter consolidating the metallic material to form the rod, wherein the rod has a rod length equal to the assembly length. The rods are bundled together to form a bundled rod assembly. The rod assembly may be used as a consumable feedstock in a melting-and-casting operation.Type: ApplicationFiled: May 27, 2005Publication date: October 13, 2005Applicant: GENERAL ELECTRIC COMPANYInventors: Eric Ott, Andrew Woodfield, Clifford Shamblen, Peter Wayte, Mike Mechley
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Publication number: 20050087272Abstract: A Ti-6Al-4V-0.2O (Ti64) forged article is fabricated by forging a workpiece to make a forged gas turbine engine component having a thick portion thereof with a section thickness greater than 2¼ inches. The forged article is heat treated by solution heat treating at a temperature of from about 50° F. to about 75° F. below the beta-transus temperature of the alloy, thereafter water quenching the gas turbine engine component to room temperature, and thereafter aging the gas turbine engine component at a temperature of from about 900° F. to about 1000° F. The resulting machined gas turbine engine component has a 0.2 percent yield strength of from about 120 ksi to about 140 ksi at its centerline, and a 0.2 percent yield strength of from about 160 ksi to about 175 ksi at a location about ½ inch below a surface thereof.Type: ApplicationFiled: October 24, 2003Publication date: April 28, 2005Applicant: General Electric CompanyInventors: Peter Wayte, Ming Li
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Publication number: 20050011863Abstract: A process for detecting an aluminum-based material deposited onto a titanium-based gas turbine engine component during engine operation is disclosed. The process comprises immersing at least a portion of the titanium-based component, which has been subjected to engine operation, into an acid solution to form an etched component. The acid solution comprises sodium fluoride, sulphuric acid and water. The etched component may then be removed from the solution and visually inspected for dark areas in contrast to light areas, the dark areas indicating deposited aluminum-based material.Type: ApplicationFiled: July 17, 2003Publication date: January 20, 2005Inventor: Peter Wayte
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Patent number: 5356545Abstract: A dry film, low coefficient of friction lubricant for titanium pieces is prepared by mixing together solid lubricant particles, poly(tetrafluoroethylene), a suspending agent, and a curable resin in an evaporable carrier. The mixture is applied to titanium or titanium alloy surfaces that contact each other in service. The carrier is evaporated during a subsequent thermal cure, leaving a lubricating film on the surfaces.Type: GrantFiled: January 15, 1991Date of Patent: October 18, 1994Assignee: General Electric CompanyInventor: Peter Wayte
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Patent number: 5240375Abstract: An improved type wear protection system for a turbine engine rotor and blade, in which a multilayer clad shim is interposed between a dovetail portion of a blade and the dovetail slot portion of a rotor, is described. The shim, preferably comprised of surface layers of phosphor bronze and a center layer of austenitic stainless steel, is especially effective in preventing fretting damage to titanium engine components.Type: GrantFiled: January 10, 1992Date of Patent: August 31, 1993Assignee: General Electric CompanyInventor: Peter Wayte
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Patent number: 5160243Abstract: A metallic reinforced shim is attached to the dovetail of turbine or compressor blades. The shim reduces frictionally induced wear damage to the rotor. In one form, a single ply shim reinforced with a metallic doubler has an anti-fretting layer deposited on the shim face contacting the dovetail slot pressure face, and a doubler layer fastened to the anti-fretting layer in the non-contacting regions to prevent slippage of the shim on the blade. In another form, a multi-layer shim has two layers interposed between the blade dovetail and the disk dovetail slot, with the layers treated so that they do not readily slip relative to the titanium pieces, but do slip relative to each other. The shim is also reinforced with a metallic doubler. Fretting is confined to the consumable shim, and therefore the disk dovetail slot and the mating blade dovetails are not subject to surface degradation with corresponding reduction in fatigue capability.Type: GrantFiled: January 15, 1991Date of Patent: November 3, 1992Assignee: General Electric CompanyInventors: Fredrick C. Herzner, Jerome A. Juenger, Peter Wayte