Patents by Inventor William J. Howe
William J. Howe 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: 20140130353Abstract: A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique.Type: ApplicationFiled: November 27, 2013Publication date: May 15, 2014Inventors: Harry L. Kington, William J. Howe
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Patent number: 8137075Abstract: Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions. The outer disk portion is bonded to the inner disk portion of the bore section, and the second plurality of blade portions is bonded to the first plurality of blade portions of the bore section.Type: GrantFiled: August 31, 2007Date of Patent: March 20, 2012Assignee: Honeywell International Inc.Inventors: William J. Howe, Harry L. Kington, James Neumann
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Publication number: 20090119919Abstract: A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique.Type: ApplicationFiled: November 12, 2007Publication date: May 14, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Harry L. Kington, William J. Howe
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Publication number: 20090056125Abstract: Compressor impellers, compressor sections, and methods of manufacturing compressor impellers and cooling the compressor impellers are provided. In an embodiment, and by way of example only, a compressor impeller includes a bore section and a rim section. The bore section comprises a first nickel-based alloy and includes an inner disk portion and a first plurality of blade portions extending therefrom. The rim section comprises a second nickel-based alloy and includes an outer disk portion and a second plurality of blade portions.Type: ApplicationFiled: August 31, 2007Publication date: March 5, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: William J. Howe, Harry L. Kington, James Neumann
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Patent number: 6942445Abstract: A cooled shroud assembly includes an angled slot and a plurality of dilution jet openings. The shroud forward cavity is modified such that at least one recirculation zone is produced. The angled slot forces an axial change in momentum of the hot gas flow and increases radial and axial pressure variation attenuation. The cooled shroud assembly isolates the shroud structure and seals from the hot flow path and a cooling flow from the dilution jet openings dilutes the hot gas flow. A series of recirculation zones shields the shroud carrier and high pressure seals from the hot gas flow.Type: GrantFiled: December 4, 2003Date of Patent: September 13, 2005Assignee: Honeywell International Inc.Inventors: Mark C. Morris, William J. Howe, George E. Zurmehly, Alan G. Tiltman, George W. Wolfmeyer, John F. Sciacca
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Patent number: 6931859Abstract: Cooling air to the blades and disks of a gas turbine may be modulated to provide a variable turbine cooling flow. A bellows may be extended by providing a high pressure compressor discharge flow to an interior of the bellows. The bellows may be compressed when the interior of the bellows communicates with ambient pressure air. The extension/compression of the bellows moves an arm over orifices in a cooling air flow path. The pressure inside of the bellows is metered to move the arm over at least one orifice, thereby restricting cooling air flow when the engine is running at low power. The pressure inside of the bellows is metered to move the arm to uncover all of the slots to provide maximum cooling flow when the engine is running at high power. The resulting variable cooling flow system results in less need for cooling air at low powers, thus reducing engine fuel consumption.Type: GrantFiled: December 17, 2003Date of Patent: August 23, 2005Assignee: Honeywell International Inc.Inventors: Peter L. Morgan, William J. Howe, Mark C. Morris, Adrian R. Allan, Donald L. Palmer
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Patent number: 6554562Abstract: A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.Type: GrantFiled: June 15, 2001Date of Patent: April 29, 2003Assignee: Honeywell International, Inc.Inventors: Rodolphe Dudebout, Mark C. Morris, Douglas P. Freiberg, Craig W. McKeever, Richard J. Musiol, Ardeshir Riahi, William J. Howe
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Publication number: 20030002975Abstract: A method and apparatus to reduce the average and maximum temperatures to which the nozzles in the hot-section of gas-turbine engine are subjected is described. The method relates to the circumferential alignment of fuel nozzles and downstream turbine nozzles in a gas turbine engine. This situates the hot-streak emerging from each fuel nozzle in between the like-numbered turbine nozzle airfoils. The most severe operating condition for reducing the durability of nozzle airfoils is the one generating hot operating temperature conditions. By identifying the temperature profile passing through downstream nozzle airfoils, airfoils in static stages can be selectively spaced around the circumference of the ring attached to the casing of the gas turbine engine to avoid high temperature exposure to the airfoils. This method and apparatus mitigates the worst oxidation and thermo-mechanical fatigue damage in the airfoils by allowing the hot gas regions to pass through the path in between two adjacent airfoils.Type: ApplicationFiled: June 15, 2001Publication date: January 2, 2003Applicant: Honeywell International, Inc.Inventors: Rodolphe Dudebout, Mark C. Morris, Douglas P. Freiberg, Craig W. McKeever, Richard J. Musiol, Ardeshir Riahi, William J. Howe
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Patent number: 6481959Abstract: A supplemental air cooling system for use in gas turbine engines to inhibit the ingestion of hot flow path gases into circumferential locations of turbine disk cavities is provided. The supplemental air cooling is provided through a simple set of cooling air holes located on each side of the turbine nozzle airfoil trailing edges, and proximately placed to be below the turbine nozzle structural element flow discouragers. Turbine disk cavity cooling purge air entering the disk cavity through the cooling air holes produces dynamic pressure cooling air jets which force the incoming hot ingestion air to turn circumferentially and go back out in the flow path before it enters the turbine disk cavity. The result is a decrease in hot gas ingestion, a reduction in disk rotor and static structural metal temperatures, a reduction in the amount of required cooling air flow, and enhanced performance of the gas turbine engine by virtue of improved specific fuel consumption.Type: GrantFiled: April 26, 2001Date of Patent: November 19, 2002Assignee: Honeywell International, Inc.Inventors: Mark C. Morris, William J. Howe, Carl D. Wright, Douglas P. Freiberg, Nnawuihe A. Okpara
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Publication number: 20020159880Abstract: A supplemental air cooling system for use in gas turbine engines to inhibit the ingestion of hot flow path gases into circumferential locations of turbine disk cavities is provided. The supplemental air cooling is provided through a simple set of cooling air holes located on each side of the turbine nozzle airfoil trailing edges, and proximately placed to be below the turbine nozzle structural element flow discouragers. Turbine disk cavity cooling purge air entering the disk cavity through the cooling air holes produces dynamic pressure cooling air jets which force the incoming hot ingestion air to turn circumferentially and go back out in the flow path before it enters the turbine disk cavity. The result is a decrease in hot gas ingestion, a reduction in disk rotor and static structural metal temperatures, a reduction in the amount of required cooling air flow, and enhanced performance of the gas turbine engine by virtue of improved specific fuel consumption.Type: ApplicationFiled: April 26, 2001Publication date: October 31, 2002Applicant: Honeywell International, Inc.Inventors: Mark C. Morris, William J. Howe, Carl D. Wright, Douglas P. Freiberg, Nnawuihe A. Okpara
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Patent number: 5545004Abstract: A hot gas recirculation pocket is provided in a gas turbine engine to capture hot gas ingested from an annular hot gas flow path into an internal cooled engine cavity, and to recirculate the ingested hot gas to the hot gas flow path. The engine includes rows of stator vanes and rotor blades mounted in an axially alternating sequence along the hot gas flow path, wherein the rotor blades are peripherally supported by rotor disks disposed within the cooled engine cavity and coupled to a main engine shaft. The recirculation pocket is defined by a contoured shroud mounted within the cooled engine cavity to form a radially outwardly open toroidal-shaped pocket for capturing and recirculating any hot gas ingested through the space between adjacent rows of stator vanes and rotor blades.Type: GrantFiled: December 23, 1994Date of Patent: August 13, 1996Assignee: AlliedSignal Inc.Inventors: Kuo-San Ho, William J. Howe, Jeffrey E. May
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Patent number: 4674955Abstract: An arrangement for supplying coolant flow to turbine blades in a gas turbine engine is disclosed which utilizes a preswirl assembly to impart a tangential velocity to the coolant flow substantially greater than the tangential velocity of the rotor at the point at which the air is supplied to the rotor. The overswirled air is injected radially inwardly into an internal passage contained in the rotor, and the coolant flow continues to be an overswirled condition within the internal passageway. The amount of overswirl imparted to the coolant flow is such that the tangential velocity of the coolant flow is greater than the tangential velocity of the blades at the location on the blades the coolant flow is supplied to the blades for blade cooling, thereby resulting in substantially improved efficiency in the cooling system.Type: GrantFiled: December 21, 1984Date of Patent: June 23, 1987Assignee: The Garrett CorporationInventors: William J. Howe, Duane B. Bush, Erian A. Baskharone
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Patent number: 4067442Abstract: A package and a method of safely packaging rigid containers, such as glass bottles, in a carton without using inner partitions to separate the containers. The containers are placed on a bottom wall of a corrugated or similar paperboard carton blank so as to occupy substantially fully the area thereof. The vertical wall portions of the blank are then brought to bear snugly against said containers and to squeeze the containers against each other. Then sufficient force is applied against the package walls so that they are indented by the containers that bear against them. Top wall portions of the carbon blank are then brought to a horizontal position and are pressed down on the containers until both the top wall portions and the bottom wall are indented by the containers, and the walls are then secured together.Type: GrantFiled: May 14, 1976Date of Patent: January 10, 1978Assignee: Georgia-Pacific CorporationInventor: William J. Howe
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Patent number: 3979882Abstract: A package and a method of safely packaging rigid containers, such as glass bottles, in a carton without using inner partitions to separate the containers. The containers are placed on a bottom wall of a corrugated or similar paperboard carton blank so as to occupy substantially fully the area thereof. The vertical wall portions of the blank are then brought to bear snugly against said containers and to squeeze the containers against each other. Then sufficient force is applied against the package walls so that they are indented by the containers that bear against them. Top wall portions of the carbon blank are then brought to a horizontal position and are pressed down on the containers until both the top wall portions and the bottom wall are indented by the containers, and the walls are then secured together.Type: GrantFiled: November 3, 1975Date of Patent: September 14, 1976Assignee: Georgia-Pacific CorporationInventor: William J. Howe