Patents by Inventor Brandon Flowers Powell
Brandon Flowers Powell 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: 11674442Abstract: A gas turbine engine includes; a compressor, a combustor, and a turbine in serial flow relationship; a heat exchanger, the heat exchanger having an inlet, an outlet, and an internal surface coated with a catalyst, the heat exchanger being located upstream of the compressor; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger.Type: GrantFiled: March 16, 2021Date of Patent: June 13, 2023Assignee: General Electric CompanyInventors: Lawrence Bernard Kool, Brandon Flowers Powell, Narendra Digamber Joshi
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Publication number: 20210285376Abstract: A gas turbine engine includes; a compressor, a combustor, and a turbine in serial flow relationship; a heat exchanger, the heat exchanger having an inlet, an outlet, and an internal surface coated with a catalyst, the heat exchanger being located upstream of the compressor; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system for receiving reformed hydrocarbon fuel from the heat exchanger.Type: ApplicationFiled: March 16, 2021Publication date: September 16, 2021Inventors: Lawrence Bernard Kool, Brandon Flowers Powell, Narendra Digamber Joshi
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Publication number: 20200386189Abstract: A hypersonic propulsion engine includes: a turbine engine including a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbine engine defining a turbine engine inlet upstream of the compressor section and a turbine engine exhaust downstream of the turbine section; a ducting assembly defining a bypass duct having a substantially annular shape and extending around the turbine engine, an afterburning chamber located downstream of the bypass duct and at least partially aft of the turbine engine exhaust, and an inlet section located at least partially forward of the bypass duct and the turbine engine inlet; and an inlet precooler positioned at least partially within the inlet section of the ducting assembly and upstream of the turbine engine inlet, the bypass duct, or both for cooling an airflow provided through the inlet section of the ducting assembly to the turbine engine inlet, the bypass duct, or both.Type: ApplicationFiled: April 24, 2020Publication date: December 10, 2020Inventors: Brandon Flowers Powell, Narendra Digamber Joshi, Timothy John Sommerer, Nicholas William Rathay, William Dwight Gerstler, Kapil Kumar Singh, Brandon Wayne Miller
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Patent number: 10253648Abstract: The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.Type: GrantFiled: March 4, 2016Date of Patent: April 9, 2019Assignee: General Electric CompanyInventors: David Todd Bentley, Christopher Ryan Johnson, Brandon Flowers Powell
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Patent number: 10018067Abstract: A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends.Type: GrantFiled: January 9, 2014Date of Patent: July 10, 2018Assignee: General Electric CompanyInventors: Kevin Samuel Klasing, Richard William Albrecht, Jr., Brandon Flowers Powell, Mark Willard Marusko, Anthony Venzon, Thomas Ryan Wallace
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Patent number: 9777631Abstract: An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the outer duct including: a first frontal area shape at the first inlet plane which defines, cooperatively with an exterior of the fan duct, at least one lobe through which air can pass; and a second frontal area shape at a second inlet plane located axially downstream from the forward end which is circular, and which defines, cooperatively with an exterior of the fan duct, an annulus through which air can pass.Type: GrantFiled: September 30, 2011Date of Patent: October 3, 2017Assignee: General Electric CompanyInventors: Brandon Flowers Powell, Trevor Andrew Tersmette, Craig Bradley Spencer
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Publication number: 20170254215Abstract: The present disclosure is directed to a variable area turbine nozzle. The variable area turbine nozzle includes a first vane segment, a second vane segment arranged with the first vane segment, and a trailing edge segment arranged with the first and second vane segments. The vane also includes a first actuating system for pivoting the second vane segment with respect to the first vane segment and a second actuating system for pivoting the trailing edge with respect to the first and second vane segments.Type: ApplicationFiled: March 4, 2016Publication date: September 7, 2017Inventors: David Todd Bentley, Christopher Ryan Johnson, Brandon Flowers Powell
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Publication number: 20150369077Abstract: A clearance control apparatus for a gas turbine engine including an annular turbine case having opposed inner and outer surfaces; an annular manifold surrounding a portion of the turbine case, the manifold including: an inlet port in fluid communication with the manifold and the outer surface of the turbine case, and an exit port; and a bypass pipe having an upstream end coupled to the exit port, a downstream end coupled to a low-pressure sink, and a valve disposed between upstream and downstream ends, the valve selectively moveable between a first position which blocks flow between the upstream and downstream ends, and a second position which permits flow between the upstream and downstream ends.Type: ApplicationFiled: January 9, 2014Publication date: December 24, 2015Inventors: Kevin Samuel KLASING, Richard William ALBRECHT, Jr., Brandon Flowers POWELL, Mark WIllard MARUSKO, Anthony VENZON, Thomas Ryan WALLACE
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Patent number: 8622687Abstract: A method of operating a compressor in an adaptive core engine is disclosed. The method comprises the steps of operating a front block compressor to increase pressure of a fluid to a first pressure ratio in a high-power mode operation; operating a rear block compressor coupled to the front block compressor such that the front block compressor and the rear block compressor operate at the same physical speed; closing a rear block stator vane located axially forward from the rear block compressor such that the flow of the fluid into the rear block compressor is substantially cut off; and keeping a blocker door opened such that substantially all of the fluid pressurized by the front block compressor flows through a bypass passage during the high-power mode operation.Type: GrantFiled: August 30, 2010Date of Patent: January 7, 2014Assignee: General Electric CompanyInventors: Rollin George Giffin, Brandon Flowers Powell, Mark Harrington, James Edward Johnson
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Publication number: 20130081375Abstract: An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the outer duct including: a first frontal area shape at the first inlet plane which defines, cooperatively with an exterior of the fan duct, at least one lobe through which air can pass; and a second frontal area shape at a second inlet plane located axially downstream from the forward end which is circular, and which defines, cooperatively with an exterior of the fan duct, an annulus through which air can pass.Type: ApplicationFiled: September 30, 2011Publication date: April 4, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Brandon Flowers Powell, Trevor Andrew Tersmette, Craig Bradley Spencer
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Publication number: 20110167784Abstract: A method of operating a gas turbine engine is disclosed having the steps of directing a flow of air to a front fan stage at a selected fan flow rate, fan speed and front fan stage pressure ratio corresponding to a selected first operating power level, pressurizing a portion of the flow from the front fan stage in a aft fan rotor to a first tip pressure ratio to generate a first overall fan pressure ratio, selecting a second operating power level that is lower than the first operating power level and reducing the flow in the aft fan rotor and pressurizing to a second tip pressure ratio to generate a second overall pressure ratio that is substantially lower than the first overall fan pressure ratio while the flow rate in the front fan stage is held substantially constant.Type: ApplicationFiled: December 21, 2009Publication date: July 14, 2011Inventors: JAMES EDWARD JOHNSON, Brandon Flowers Powell
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Publication number: 20110167792Abstract: An adaptive gas turbine engine is disclosed having a convertible fan system adapted to have a variable fan pressure ratio while the air flow into the convertible fan system remains substantially constant and an adaptive core having a compressor capable of maintaining a substantially constant core pressure ratio while a core airflow flow rate is varied.Type: ApplicationFiled: December 21, 2009Publication date: July 14, 2011Inventors: JAMES EDWARD JOHNSON, Brandon Flowers Powell
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Publication number: 20110167791Abstract: A gas turbine engine is disclosed having a fan system with a front stage fan rotor and an aft fan rotor coupled to a low-pressure turbine, a core having a compressor coupled to a high-pressure turbine, an annular inner bypass passage and an annular outer bypass passage. The aft fan rotor has a row of aft fan blades having an arcuate splitter that forms a portion of an inner flow passage and an outer flow passage wherein the aft fan blade pressurizes an inner flow and an outer flow and wherein the fan tip pressure ratio can be changed while the air flow into the front stage fan rotor is held substantially constant.Type: ApplicationFiled: December 21, 2009Publication date: July 14, 2011Inventors: James Edward Johnson, Brandon Flowers Powell
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Publication number: 20110171007Abstract: A convertible fan system is disclosed having a fan rotor with a plurality of fan blades having an arcuate splitter that forms a portion of an inner flow passage and an outer flow passage wherein an inner portion of the fan blade pressurizes an inner flow in the inner flow passage and an outer portion of the fan blade pressurizes an outer flow in the outer flow passage and a vane system having an outer vane that is adapted to be able to vary the flow in the outer flow passage such that pressure ratio of the fan system can be varied.Type: ApplicationFiled: December 21, 2009Publication date: July 14, 2011Inventors: James Edward Johnson, Brandon Flowers Powell
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Publication number: 20110076158Abstract: A method of operating a compressor in an adaptive core engine is disclosed. The method comprises the steps of operating a front block compressor to increase pressure of a fluid to a first pressure ratio in a high-power mode operation; operating a rear block compressor coupled to the front block compressor such that the front block compressor and the rear block compressor operate at the same physical speed; closing a rear block stator vane located axially forward from the rear block compressor such that the flow of the fluid into the rear block compressor is substantially cut off; and keeping a blocker door opened such that substantially all of the fluid pressurized by the front block compressor flows through a bypass passage during the high-power mode operation.Type: ApplicationFiled: August 30, 2010Publication date: March 31, 2011Inventors: ROLLIN GEORGE GIFFIN, BRANDON FLOWERS POWELL, MARK HARRINGTON, JAMES EDWARD JOHNSON
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Patent number: 7614210Abstract: A variable cycle turbofan engine includes first and second fans independently joined to respective turbines. A first bypass duct surrounds a core engine disposed in flow communication with the second fan. A second bypass duct surrounds the first bypass duct in flow communication with the first fan. A first exhaust nozzle is joined to both the core engine and first bypass duct. And, a second exhaust nozzle is joined to the second bypass duct.Type: GrantFiled: February 13, 2006Date of Patent: November 10, 2009Assignee: General Electric CompanyInventors: Brandon Flowers Powell, John Jared Decker
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Patent number: 7530217Abstract: An axial flow positive displacement engine has an inlet axially spaced apart and upstream from an outlet. Inner and outer bodies have offset inner and outer axes extend from the inlet to the outlet through first, second, and third sections of a core assembly in serial downstream flow relationship. At least one of the bodies is rotatable about its axis. The inner and outer bodies have intermeshed inner and outer helical blades wound about the inner and outer axes respectively. The inner and outer helical blades extend radially outwardly and inwardly respectively and have first, second, and third twist slopes in the first, second, and third sections respectively. The first twist slopes are less than the second twist slopes and the third twist slopes are less than the second twist slopes. A combustion section extends axially downstream from the second section through at least a portion of the third section.Type: GrantFiled: December 16, 2005Date of Patent: May 12, 2009Assignee: General Electric CompanyInventors: Kurt David Murrow, Brandon Flowers Powell