Patents by Inventor Gregory Vogel
Gregory Vogel 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: 20230408095Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A static air plenum surrounds each of the air/fuel mixing tubes to thermally isolate the air/fuel mixing tube from the respective fuel manifold.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Publication number: 20230408096Abstract: A combustor of a gas turbine engine is provided with a first injector and a second injector. The first injector surrounds a combustion liner and is positioned at a downstream end of a flow sleeve. A dome plate is positioned to receive a fuel/air mixture from the first injector and turn it 180 degrees to enter a combustion zone formed within the combustion liner. The second injector is positioned radially inward of the combustion liner at an inlet end of the combustion zone and receives only compressed air from the first injector. The second injector includes a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Publication number: 20230408097Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. A blocker is provided at an outlet portion of each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes and/or the radially inner subset of air/fuel mixing tubes to form a flame anchoring surface.Type: ApplicationFiled: November 3, 2022Publication date: December 21, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Publication number: 20230135396Abstract: An injector for a combustor of a gas turbine engine is provided with a plurality of air/fuel mixing tubes divided into radially outer and radially inner subsets of air/fuel mixing tubes with a first fuel manifold in fluid communication with the radially outer subset of air/fuel mixing tubes and a second fuel manifold in fluid communication with the radially inner subset of air/fuel mixing tubes. Each of the air/fuel mixing tubes of the radially outer subset of air/fuel mixing tubes includes a substantially quadrilateral cross-sectional profile, and each of the air/fuel mixing tubes of the radially inner subset of air/fuel mixing tubes includes a substantially circular cross-sectional profile.Type: ApplicationFiled: November 3, 2022Publication date: May 4, 2023Inventors: Bryan KALB, Matthew YAQUINTO, Gene CHONG, David PARADES, James BRACKETT, Gregory VOGEL, Hany RIZKALLA, Bernard Tam Yen SAM, Ramesh KESHAVA-BHATTU, Fred HERNANDEZ, Joshua R. MCNALLY
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Patent number: 10392942Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.Type: GrantFiled: November 24, 2015Date of Patent: August 27, 2019Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Jeremy Metternich, Gregory Vogel, Elena P. Pizano, Edwin J. Kawecki
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Patent number: 10352181Abstract: Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.Type: GrantFiled: November 24, 2015Date of Patent: July 16, 2019Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Gregory Vogel, Elena P. Pizano, Jeremy Metternich, Edwin J. Kawecki
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Patent number: 10280763Abstract: An airfoil for a gas turbine engine, the airfoil comprising a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface, the passageway having one or more sections between the first opening and the second opening, the one or more sections in fluid communication with each other, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the passageway, a second diffuser section providing a second change in cross-sectional area within the passageway, a flow conditioning section, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening.Type: GrantFiled: June 8, 2016Date of Patent: May 7, 2019Assignee: Ansaldo Energia Switzerland AGInventors: Alex Torkaman, Gregory Vogel, Christopher Johnston, Michele Borja
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Patent number: 10113745Abstract: An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.Type: GrantFiled: March 26, 2015Date of Patent: October 30, 2018Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Alex Torkaman, Gregory Vogel, Richard Whiting, Jeff Tessier, Wes Smith
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Patent number: 10018065Abstract: This disclosure describes a removable flow control device which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure loss in the flow supply system. The flow control device may be coupled to a blade and rotor assembly and may include a flow modifier for directing flow through a junction at which cooling channels intersect and are in fluid communication. The device may direct, control, meter, channel, or otherwise modify the flow of coolant, and may be coupled to the blade and rotor assembly independently of other blade components so that coupling and decoupling the flow control device does not require modification or de-stacking of the rotor assembly.Type: GrantFiled: September 4, 2015Date of Patent: July 10, 2018Assignee: ANSALDO ENERGIA IP UK LIMITEDInventors: Gregory Vogel, Jeffrey E. Tessier, Alain Hernandez, Chad M. Garner
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Publication number: 20170356294Abstract: An airfoil for a gas turbine engine, the airfoil comprising a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface, the passageway having one or more sections between the first opening and the second opening, the one or more sections in fluid communication with each other, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the passageway, a second diffuser section providing a second change in cross-sectional area within the passageway, a flow conditioning section, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening.Type: ApplicationFiled: June 8, 2016Publication date: December 14, 2017Inventors: Alex Torkaman, Gregory Vogel, Christopher Johnston, Michele Borja
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Publication number: 20170067356Abstract: This disclosure describes a removable flow control device which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure loss in the flow supply system. The flow control device may be coupled to a blade and rotor assembly and may include a flow modifier for directing flow through a junction at which cooling channels intersect and are in fluid communication. The device may direct, control, meter, channel, or otherwise modify the flow of coolant, and may be coupled to the blade and rotor assembly independently of other blade components so that coupling and decoupling the flow control device does not require modification or de-stacking of the rotor assembly.Type: ApplicationFiled: September 4, 2015Publication date: March 9, 2017Inventors: GREGORY VOGEL, JEFF TESSLER, ALAIN HERNANDEZ
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Publication number: 20160281987Abstract: An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.Type: ApplicationFiled: March 26, 2015Publication date: September 29, 2016Inventors: ALEX TORKAMAN, GREGORY VOGEL, RICHARD WHITING, JEFF TESSIER, WES SMITH
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Publication number: 20160146019Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.Type: ApplicationFiled: November 24, 2015Publication date: May 26, 2016Inventors: Elena P. PIZANO, Jeremy METTERNICH, Gregory VOGEL, Edwin J. KAWECKI
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Publication number: 20160146018Abstract: The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.Type: ApplicationFiled: November 24, 2015Publication date: May 26, 2016Inventors: JEREMY METTERNICH, GREGORY VOGEL, ELENA P. PIZANO, EDWIN J. KAWECKI
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Publication number: 20160146017Abstract: Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.Type: ApplicationFiled: November 24, 2015Publication date: May 26, 2016Inventors: Gregory Vogel, Elena P. Pizano, Jeremy Metternich, Edwin J. Kawecki
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Patent number: 8413449Abstract: A thermal machine includes a hot gas channel; a shell bounding the hot gas channel; a cooling shirt surrounding the shell; and a cooling channel disposed between the shell and the cooling shirt and configured to convection cool the hot gas channel with a cooling medium, wherein the cooling shirt includes at least one local divergence in the guidance of the cooling medium so as to compensate for non-uniformities in at least one of a thermal load on the shell and a flow of the cooling medium in the cooling channel.Type: GrantFiled: August 16, 2010Date of Patent: April 9, 2013Assignee: Alstom Technology LtdInventors: Hartmut Haehnle, Russell Bond Jones, Gregory Vogel, Remigi Tschuor
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Patent number: 8272220Abstract: A thermal machine including a wall defining a hot gas duct for transferring a hot gas stream and a cooling jacket disposed at a distance from the wall on an outside of the hot gas duct so as to define a cooling duct with an inlet and an outlet. The cooling duct is configured to conduct a cooling medium along an external face of the wall from the inlet to an outlet in a direction counter to a flow of hot gas in the hot gas duct. An impingement cooling plate is disposed at the inlet of the cooling duct and includes cooling baffle holes configured such that cooling medium entering the cooling duct through the cooling baffle holes flows in a direction perpendicular to the wall. The impingement cooling plate is positioned such that an inflow-side edge sealingly abuts the wall of the hot gas duct so as to reduce a transverse flow of the cooling medium through the cooling duct.Type: GrantFiled: August 20, 2010Date of Patent: September 25, 2012Assignee: Alstom Technology LtdInventors: Hartmut Haehnle, Gregory Vogel, Russell Bond Jones, Marion Duggans (-Oneil), Remigi Tschuor
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Patent number: 7997866Abstract: A gas turbine airfoil (1) includes a pressure sidewall (15) and a suction sidewall (16), extending from a root to a tip and from a leading edge region to a trailing edge and having at least one cooling passage between the pressure sidewall (15) and the suction sidewall (16) for cooling air to pass through and cool the airfoil from within. One or several of the cooling passages (3) extend along the leading edge of the airfoil (1) and several film cooling holes (1,2) extend from the internal cooling passages (3) along the leading edge region to the outer surface of the leading edge region. The film cooling holes (1,2) each have a shape that is diffused in a radial outward direction of the leading edge of the airfoil (1) at least over a part of the length of the film cooling hole (1,2).Type: GrantFiled: August 15, 2007Date of Patent: August 16, 2011Assignee: ALSTOM Technology Ltd.Inventors: Shailendra Naik, Gregory Vogel
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Publication number: 20110113790Abstract: A thermal machine including a wall defining a hot gas duct for transferring a hot gas stream and a cooling jacket disposed at a distance from the wall on an outside of the hot gas duct so as to define a cooling duct with an inlet and an outlet. The cooling duct is configured to conduct a cooling medium along an external face of the wall from the inlet to an outlet in a direction counter to a flow of hot gas in the hot gas duct. An impingement cooling plate is disposed at the inlet of the cooling duct and includes cooling baffle holes configured such that cooling medium entering the cooling duct through the cooling baffle holes flows in a direction perpendicular to the wall. The impingement cooling plate is positioned such that an inflow-side edge sealingly abuts the wall of the hot gas duct so as to reduce a transverse flow of the cooling medium through the cooling duct.Type: ApplicationFiled: August 20, 2010Publication date: May 19, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Hartmut HAEHNLE, Gregory VOGEL, Russell Bond JONES, Marion DUGGANS (-ONEIL), Remigi TSCHUOR
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Publication number: 20110110761Abstract: A thermal machine includes a hot gas channel; a shell bounding the hot gas channel; a cooling shirt surrounding the shell; and a cooling channel disposed between the shell and the cooling shirt and configured to convection cool the hot gas channel with a cooling medium, wherein the cooling shirt includes at least one local divergence in the guidance of the cooling medium so as to compensate for non-uniformities in at least one of a thermal load on the shell and a flow of the cooling medium in the cooling channel.Type: ApplicationFiled: August 16, 2010Publication date: May 12, 2011Applicant: ALSTOM TECHNOLOGY LTD.Inventors: Hartmut HAEHNLE, Russell Bond JONES, Gregory VOGEL, Remigi TSCHUOR