Patents by Inventor John Howard Starkweather
John Howard Starkweather 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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Patent number: 10975731Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator.Type: GrantFiled: May 28, 2015Date of Patent: April 13, 2021Assignee: General Electric CompanyInventors: Robert Francis Manning, Timothy Deryck Stone, Jared Peter Buhler, Victor Hugo Silva Correia, Gregory Michael Laskowski, Robert Carl Murray, Jonathan Russell Ratzlaff, Robert Proctor, John Howard Starkweather, Curtis Walton Stover
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Publication number: 20170261208Abstract: A substrate having one or more shaped effusion cooling holes formed therein. Each shaped cooling hole has a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension. Also methods for making the shaped cooling holes.Type: ApplicationFiled: May 26, 2017Publication date: September 14, 2017Inventors: John Howard Starkweather, William Thomas Bennett, John Franklin Gibbons, Anthony Stephen Urbanski
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Patent number: 9696035Abstract: A method for making shaped cooling holes in a substrate by pulsing and stopping a laser while moving the laser or substrate. The method produces shaped cooling holes with a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension.Type: GrantFiled: May 1, 2013Date of Patent: July 4, 2017Assignee: General Electric CompanyInventors: John Howard Starkweather, William Bennett, John Gibbons, Anthony Urbanski
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Publication number: 20170101894Abstract: An engine component assembly is provided for impingement cooling including discrete cooling features. An insert is located opposite and adjacent to a cooled surface of the engine component and includes a plurality of angled impingement air holes. A cooling fluid flow path is flowing on one side the cooled surface of the engine component and adjacent to the insert and passes through the angled cooling holes of the insert in order to cool the cooled surface of the engine component. Additionally, a plurality of discrete cooling features may be located along the cooled surface of the engine component opposite the plurality of cooling holes in the insert.Type: ApplicationFiled: May 27, 2015Publication date: April 13, 2017Inventors: Phebe Helena PREETHI, William Thomas BENNETT, John Howard STARKWEATHER, Timothy Deryck STONE
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Publication number: 20170101896Abstract: A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator.Type: ApplicationFiled: May 28, 2015Publication date: April 13, 2017Applicant: GENERAL ELECTRIC COMPANYInventors: Robert Francis MANNING, Timothy Deryck STONE, Jared Peter BUHLER, Victor Hugo Silva CORREIA, Gregory Michael LASKOWSKI, Robert Carl MURRAY, Jonathan Russell RATZLAFF, Robert PROCTOR, John Howard STARKWEATHER, Curtis Walton STOVER
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Publication number: 20140248425Abstract: A method of manufacturing a component suitable for use in a gas turbine engine, comprising the steps of forming the component from a substrate having a first surface and a second surface, forming at least one aperture through the substrate from the first surface to the second surface having a first open area, applying a first coating to at least one of the first surface and the second surface adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the first coating, applying a second coating to the first coating adjacent to the at least one aperture, the aperture remaining at least partially unobstructed by the second coating, and removing the second coating from the aperture, leaving most or all of the first coating to define a second open area which is smaller than the first open area.Type: ApplicationFiled: June 20, 2013Publication date: September 4, 2014Inventors: David Bruce Patterson, John Howard Starkweather, Thomas George Holland, Thomas John Tomlinson
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Publication number: 20130269354Abstract: A substrate having one or more shaped effusion cooling holes formed therein. Each shaped cooling hole has a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension. Also methods for making the shaped cooling holes.Type: ApplicationFiled: May 1, 2013Publication date: October 17, 2013Inventors: John Howard Starkweather, William Bennett, John Gibbons, Anthony Urbanski
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Publication number: 20120102959Abstract: A substrate having one or more shaped effusion cooling holes formed therein. Each shaped cooling hole has a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension. Also methods for making the shaped cooling holes.Type: ApplicationFiled: October 29, 2010Publication date: May 3, 2012Inventor: John Howard STARKWEATHER
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Patent number: 7900457Abstract: A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.Type: GrantFiled: October 31, 2006Date of Patent: March 8, 2011Assignee: General Electric CompanyInventors: David Bruce Patterson, Art Johnson, John Howard Starkweather, Daniel Kirtley, Grzegorz Mlynski
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Publication number: 20080010992Abstract: A method for fabricating a combustor liner for a gas turbine engine is provided. The method includes providing an annular shell including a plurality of circumferentially extending panels, wherein the plurality of circumferentially extending panels includes a first panel positioned at an upstream end of the shell and a second panel positioned downstream from, and adjacent to, the first panel. The method also includes forming a plurality of primary dilution holes in the first panel and forming a plurality of secondary dilution holes in the second panel, wherein the primary and secondary dilution holes are configured to discharge dilution air into the shell.Type: ApplicationFiled: October 31, 2006Publication date: January 17, 2008Inventors: David Bruce Patterson, Art Johnson, John Howard Starkweather, Daniel Kirtley, Grzegorz Mlynski
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Patent number: 6846575Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.Type: GrantFiled: June 5, 2003Date of Patent: January 25, 2005Assignee: General Electric CompanyInventors: Wayne Charles Hasz, Robert Alan Johnson, Ching-Pang Lee, Mark Gerard Rettig, Nesim Abuaf, John Howard Starkweather
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Publication number: 20040131877Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.Type: ApplicationFiled: June 5, 2003Publication date: July 8, 2004Inventors: Wayne Charles Hasz, Robert Alan Johnson, Ching-Pang Lee, Mark Gerard Rettig, Nesim Abuaf, John Howard Starkweather
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Patent number: 6598781Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.Type: GrantFiled: June 24, 2002Date of Patent: July 29, 2003Assignee: General Electric CompanyInventors: Wayne Charles Hasz, Robert Alan Johnson, Ching-Pang Lee, Mark Gerard Rettig, Nesim Abuaf, John Howard Starkweather
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Patent number: 6558119Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.Type: GrantFiled: May 29, 2001Date of Patent: May 6, 2003Assignee: General Electric CompanyInventors: Ching-Pang Lee, Jonathan James Stow, John Peter Heyward, John Howard Starkweather, Lawrence Joseph Roedl, Joseph Howell Bowden, Jr.
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Publication number: 20020187042Abstract: An airfoil for a gas turbine engine, the airfoil having a core body with an airfoil body, an integral partial height squealer tip, and an integral tip cap between the airfoil body and the integral partial height squealer tip; and a squealer tip extension bonded to the partial height squealer tip. A method for manufacture and repair of an airfoil.Type: ApplicationFiled: May 29, 2001Publication date: December 12, 2002Inventors: Ching-Pang Lee, Jonathan James Stow, John Peter Heyward, John Howard Starkweather, Lawrence Joseph Roedl, Joseph Howell Bowden
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Patent number: 6491496Abstract: A gas turbine engine hollow airfoil has chordally spaced apart leading and trailing edges extending radially from a radially inner base to a radially outer airfoil tip. A cooling circuit within the airfoil has radially extending first, middle, and last channels arranged respectively in series with the first channel in fluid communication with a source of cooling air from outside the airfoil. The last channel is in fluid communication with one of the edges. A refresher passageway extends through a radially inner wall bounding a radially inner portion of the last channel and is in fluid communication with the source of cooling air. The refresher passageway is separate, spaced apart, and independent from the first channel. In one embodiment, a metering plate covers an inlet to the refresher passageway and the metering plate has a metering hole over the inlet and the metering hole is adjustable.Type: GrantFiled: February 23, 2001Date of Patent: December 10, 2002Assignee: General Electric CompanyInventor: John Howard Starkweather
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Publication number: 20020168537Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.Type: ApplicationFiled: June 24, 2002Publication date: November 14, 2002Inventors: Wayne Charles Hasz, Robert Alan Johnson, Ching-Pang Lee, Mark Gerard Rettig, Nesim Abuaf, John Howard Starkweather
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Patent number: 6478540Abstract: A turbine bucket includes an airfoil extending from a platform, having high and low pressure sides; a wheel mounting portion; a hollow shank portion located radially between the platform and the wheel mounting portion, the platform having an under surface. An impingement cooling plate is located in the hollow shank portion, spaced from the under surface, and the impingement plate is formed with a plurality of impingement cooling holes therein.Type: GrantFiled: December 19, 2000Date of Patent: November 12, 2002Assignee: General Electric CompanyInventors: Nesim Abuaf, Kevin Joseph Barb, Sanjay Chopra, David Max Kercher, Iain Robertson Kellock, Dean Thomas Lenahan, Sankar Nellian, John Howard Starkweather, Douglas Arthur Lupe
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Patent number: 6471479Abstract: A gas turbine engine hollow airfoil includes an airfoil outer wall having width wise spaced apart pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of the airfoil and extending radially outward from a base to a tip. The airfoil includes a single three pass aft flowing serpentine cooling circuit and a straight through leading edge cooling channel extending radially through the airfoil and bounded in part by the leading edge. The exemplary embodiment includes a trailing edge cooling plenum and a straight through single pass trailing edge feed channel for providing cooling air to the trailing edge cooling plenum.Type: GrantFiled: February 23, 2001Date of Patent: October 29, 2002Assignee: General Electric CompanyInventor: John Howard Starkweather
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Patent number: 6468669Abstract: An article includes turbulation material bonded to a surface of a substrate via a bonding agent, such as a braze alloy. In an embodiment, the turbulation material includes a particulate phase of discrete metal alloy particles having an average particle size within a range of about 125 microns to about 4000 microns. Other embodiments include methods for applying turbulation and articles for forming turbulation.Type: GrantFiled: May 3, 1999Date of Patent: October 22, 2002Assignee: General Electric CompanyInventors: Wayne Charles Hasz, Robert Alan Johnson, Ching-Pang Lee, Mark Gerard Rettig, Nesim Abuaf, John Howard Starkweather