Patents by Inventor Randy Lee Lewis
Randy Lee Lewis 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: 11746703Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: GrantFiled: July 7, 2021Date of Patent: September 5, 2023Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Publication number: 20210340912Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: ApplicationFiled: July 7, 2021Publication date: November 4, 2021Inventors: Michael Anthony RUTHEMEYER, Darrell Glenn SENILE, Bernard James RENGGLI, Randy Lee LEWIS
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Patent number: 11078845Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: GrantFiled: September 6, 2018Date of Patent: August 3, 2021Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Publication number: 20200025087Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: ApplicationFiled: September 6, 2018Publication date: January 23, 2020Inventors: Michael Anthony RUTHEMEYER, Darrell Glenn SENILE, Bernard James RENGGLI, Randy Lee LEWIS
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Patent number: 10132242Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: GrantFiled: April 26, 2013Date of Patent: November 20, 2018Assignee: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Publication number: 20150075176Abstract: A gas turbine engine assembly includes first and second annular members having different first and second thermal expansion coefficients connected together with dual arm V brackets. Brackets include first and second arms angularly spaced apart from a bracket centerline and extending axially away from bracket bases attached to a first one of the first and second annular members. Arms are attached to a second one of the first and second annular members. A turbine frame includes struts extending between outer and inner rings. An annular mixer and centerbody substantially made from a ceramic matrix composite materials is connected to and supported by the outer and inner rings with first and second sets respectively of the dual arm V brackets. Bracket bases of the first and second sets are attached to the outer and inner rings respectively. Arms of the first and second sets are attached to mixer and centerbody respectively.Type: ApplicationFiled: April 26, 2013Publication date: March 19, 2015Applicant: General Electric CompanyInventors: Michael Anthony Ruthemeyer, Darrell Glenn Senile, Bernard James Renggli, Randy Lee Lewis
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Patent number: 8806849Abstract: A method of operating a turbine engine system and a turbine engine system are provided. The method comprises supplying a flow of oxygen to a combustion chamber defined within a plurality of turbines coupled serially together within the turbine engine system, supplying a flow of hydrocarbonaccous fuel to the combustion chambers of each of the plurality of turbines in the turbine engine system, and supplying a working fluid to an inlet of a first turbine engine coupled within the turbine engine system, wherein the working fluid is substantially nitrogen-free and wherein each of the turbines coupled within the turbine engine system is operable with the resulting fuel-oxygen-working fluid mixture.Type: GrantFiled: July 30, 2008Date of Patent: August 19, 2014Assignees: The University of Wyoming, General Electric CompanyInventors: John Frederick Ackerman, Matthew Timothy Franer, Randy Lee Lewis, David Allen Bell, Morris Dee Argyle, Brian Francis Towler
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Patent number: 8726670Abstract: A gas turbine engine augmentor includes an inter-liner cavity including an axially extending annular gap separating augmentor and tailpipe liners. A purge flow cavity is in fluid communication with a fan bypass duct and with the cavity. An ejector in fluid communication with the bypass duct includes an ejector nozzle positioned and aimed to direct an ejector nozzle flow from inside the ejector nozzle across the cavity. The purge flow cavity may be bifurcated into forward and aft purge flow cavities which are in fluid communication with the ejector and inter-liner cavity respectively. An annular dividing wall having ejector metering apertures may be disposed between the forward purge flow cavity and an ejector plenum of the ejector. An annular trapped vortex cavity pilot may be located upstream of the annular gap. The aft purge flow cavity may be outwardly bounded by a seal having purge metering apertures disposed therethrough.Type: GrantFiled: June 24, 2010Date of Patent: May 20, 2014Assignee: General Electric CompanyInventors: Frank Gerald Bachman, Randy Lee Lewis, Robert Steven Bockwich, Shane Bunnag
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Publication number: 20110315789Abstract: A gas turbine engine augmentor includes an inter-liner cavity including an axially extending annular gap separating augmentor and tailpipe liners. A purge flow cavity is in fluid communication with a fan bypass duct and with the cavity. An ejector in fluid communication with the bypass duct includes an ejector nozzle positioned and aimed to direct an ejector nozzle flow from inside the ejector nozzle across the cavity. The purge flow cavity may be bifurcated into forward and aft purge flow cavities which are in fluid communication with the ejector and inter-liner cavity respectively. An annular dividing wall having ejector metering apertures may be disposed between the forward purge flow cavity and an ejector plenum of the ejector. An annular trapped vortex cavity pilot may be located upstream of the annular gap. The aft purge flow cavity may be outwardly bounded by a seal having purge metering apertures disposed therethrough.Type: ApplicationFiled: June 24, 2010Publication date: December 29, 2011Inventors: Frank Gerald Bachman, Randy Lee Lewis, Robert Steven Bockwich, Shane Bunnag
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Publication number: 20100024378Abstract: A gas turbine engine system is provided. The gas turbine engine system includes a gas turbine engine and an exhaust gas conditioning system. The gas turbine engine includes at least one combustion chamber and at least one turbine downstream from the combustion chamber. The combustion chamber is coupled in flow communication to a source of hydrocarbonaceous fuel and to a source of oxygen. The gas turbine engine is operable with a working fluid that is substantially nitrogen-free. The exhaust gas conditioning system is coupled between a discharge outlet of the gas turbine engine and an inlet of the gas turbine engine.Type: ApplicationFiled: July 30, 2008Publication date: February 4, 2010Inventors: John Frederick Ackermann, Matthew Timothy Franer, Randy Lee Lewis, David Allen Bell, Morris Dee Argyle, Brian Francis Towler
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Publication number: 20100024433Abstract: A gas turbine engine system is provided. The gas turbine engine system includes a gas turbine engine, an exhaust gas conditioning system, and a sequestration chamber. The gas turbine engine includes at least one compressor, at least one combustion chamber downstream from the compressor, and at least one turbine downstream from the combustion chamber. The combustion chamber is coupled in flow communication to a source of hydrocarbonaceous fuel and to a source of oxygen. The gas turbine engine is operable with a working fluid that is substantially nitrogen-free. The exhaust gas conditioning system is coupled between a discharge outlet and an inlet of the gas turbine engine. The exhaust gas conditioning system receives all of the exhaust discharged from the gas turbine engine. The sequestration chamber stores carbon dioxide and is coupled to the gas turbine engine for receiving working fluid bled from the turbine upstream from combustion chamber.Type: ApplicationFiled: July 30, 2008Publication date: February 4, 2010Inventors: John Frederick Ackermann, Matthew Timothy Franer, Randy Lee Lewis, David Allen Bell, Morris Dee Argyle, Brian Francis Towler
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Publication number: 20100024381Abstract: A method of operating a turbine engine system and a turbine engine system are provided. The method comprises supplying a flow of oxygen to a combustion chamber defined within a plurality of turbines coupled serially together within the turbine engine system, supplying a flow of hydrocarbonaccous fuel to the combustion chambers of each of the plurality of turbines in the turbine engine system, and supplying a working fluid to an inlet of a first turbine engine coupled within the turbine engine system, wherein the working fluid is substantially nitrogen-free and wherein each of the turbines coupled within the turbine engine system is operable with the resulting fuel-oxygen-working fluid mixture.Type: ApplicationFiled: July 30, 2008Publication date: February 4, 2010Inventors: John Frederick Ackermann, Matthew Timothy Franer, Randy Lee Lewis, David Allen Bell, Morris Dee Argyle, Brian Francis Towler
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Patent number: 7251941Abstract: An afterburner includes an exhaust duct with a fixed area outer nozzle at an aft end thereof, and an ablative inner nozzle therein. The smaller inner nozzle is consumed during reheat operation to expose the larger outer nozzle for increased propulsion thrust.Type: GrantFiled: March 10, 2004Date of Patent: August 7, 2007Assignee: General Electric CompanyInventors: John Michael Koshoffer, Randy Lee Lewis
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Patent number: 6092359Abstract: A process for carrying out chemical reactions in the gas phase or gas-liquid phase comprises feeding the chemical reagents under pressure into the combustion chamber of a turbine engine, where they react to form a desired chemical product. The heat energy evolved in the process can be utilized through the action of the turbine to power auxiliary equipment attached to the turbine engine, such as an electrical generator. In another embodiment, the turbine engine is utilized to carry out at least two reactions: a primary reaction which occurs in the combustion chamber of the engine, and a second reaction which occurs in an augmentor-section of the engine, utilizing the product of the primary reaction as a reagent in the production of a final product.Type: GrantFiled: August 27, 1997Date of Patent: July 25, 2000Assignee: General Electric CompanyInventors: John Frederick Ackermann, Randy Lee Lewis, William Randolph Stowell