Patents by Inventor Jared Peter Buhler
Jared Peter Buhler 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: 20180195725Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. The forward wall defines at least one channel inlet orifice. At least one sidewall defines at least one channel outlet orifice. At least one micro channel cooling circuit is defined between the one or more channel inlet orifices and the one or more channel outlet orifices.Type: ApplicationFiled: January 12, 2017Publication date: July 12, 2018Inventors: William Thomas Bennett, Jared Peter Buhler, Craig Alan Gonyou
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Publication number: 20180016944Abstract: An assembly for removing entrained particles from a fluid stream passing through a gas turbine engine includes a first particle remover, a second particle remover fluidly coupled which receives a particle-laden stream from the first particle remover, and a venturi having a fluidly coupled to the second particle remover to increase the pressure differential across the assembly.Type: ApplicationFiled: July 14, 2016Publication date: January 18, 2018Inventors: Jared Peter Buhler, Christopher Charles Glynn, Corey Bourassa, Monty Lee Shelton, Robert Francis Manning, Victor Hugo Silva Correia
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Patent number: 9845691Abstract: A turbine nozzle segment includes: an arcuate outer band segment; an airfoil-shaped turbine vane extending radially inward from the outer band segment, the turbine vane having a hollow interior; an impingement baffle assembly secured to the outer band so as to define an impingement cavity in cooperation with the outer band segment, wherein the impingement baffle assembly has at least one impingement hole formed therein which is arranged to direct cooling air at the outer band segment; and at least one impingement insert having at least one impingement hole formed therein disposed in the interior of the turbine vane, the impingement insert mating with an opening in the impingement baffle assembly such that the impingement baffle is isolated from direct fluid communication with the impingement cavity.Type: GrantFiled: October 26, 2012Date of Patent: December 19, 2017Assignee: General Electric CompanyInventors: Marshall Scott Allen, Victor Hugo Silva Correia, Robert Proctor, Jared Peter Buhler
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Patent number: 9726024Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit.Type: GrantFiled: December 21, 2012Date of Patent: August 8, 2017Assignee: General Electric CompanyInventors: Jared Peter Buhler, Marshall Scott Allen, Daniel Edward Demers, Robert Francis Manning
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Publication number: 20170159449Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.Type: ApplicationFiled: December 7, 2015Publication date: June 8, 2017Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Publication number: 20170159451Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.Type: ApplicationFiled: May 24, 2016Publication date: June 8, 2017Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Publication number: 20170159450Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.Type: ApplicationFiled: December 7, 2015Publication date: June 8, 2017Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Publication number: 20170128867Abstract: A filter system and method use a filter housing that defines an interior chamber and that includes an inlet opening extending into the interior chamber. The outer air flow housing has an outlet conduit through which a flow of air having particles is directed toward the inlet opening of the filter housing along a flow direction toward the interior chamber of the filter housing. The outer air flow housing engages the filter housing such that the filter housing is separated from the outer air flow housing along the flow direction to permit at least some of the air to pass around an exterior of the filter housing and exit the outer air flow housing while the particles in the at least some of the air pass into the interior chamber of the filter housing through the inlet opening.Type: ApplicationFiled: November 5, 2015Publication date: May 11, 2017Inventors: William Collins Vining, Robert Francis Manning, Victor Hugo Silva Correia, Corey Bourassa, Jared Peter Buhler, Hojjat Nasr
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Publication number: 20170122202Abstract: A gas turbine engine comprising a cyclonic separator provides fluid communication between the compressor section and the turbine section. The cyclonic separator comprises an annular volume receiving a flow of cooling fluid from an inlet and dividing the airflow into a cleaner air outlet and a scavenge outlet. The flow of cooling fluid is provided to the cyclonic separator in a direction tangential to the annular volume such that a cyclonic flow of cooling fluid moves within the annular volume centrifugally separating particles entrained within the airflow to the radial outer area of the annular volume for removal through the scavenge outlet and providing a cleaner airflow to the cleaner air outlet.Type: ApplicationFiled: October 28, 2015Publication date: May 4, 2017Inventors: John Joseph Rahaim, Corey Bourassa, Jared Peter Buhler, Jonathan Russell Ratzlaff
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Publication number: 20170114720Abstract: A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.Type: ApplicationFiled: May 29, 2015Publication date: April 27, 2017Inventors: Timothy Deryck STONE, Gregory Michael LASKOWSKI, Robert PROCTOR, Curtis STOVER, Robert Francis Manning, Victor Hugo Silva CORREIA, Jared Peter BUHLER, Robert Carl MURRAY, Corey BOURASSA, Jr., Byron Andrew PRITCHARD, Jonathan Russell RATZLAFF
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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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Patent number: 9518474Abstract: A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.Type: GrantFiled: March 20, 2014Date of Patent: December 13, 2016Assignee: General Electric CompanyInventors: Jason David Shapiro, Jared Peter Buhler, Brian Kenneth Corsetti
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Publication number: 20160123154Abstract: An engine component for a turbine engine includes a particle collector having a substrate configured to retain at least some particles from a particle-laden stream passing through a portion of the engine. A fluid bypass around the substrate of the collector enables the particle-laden stream to bypass the substrate if the substrate is filled with particles.Type: ApplicationFiled: September 22, 2015Publication date: May 5, 2016Inventors: Robert Francis MANNING, Victor Hugo Silva CORREIA, Jared Peter BUHLER, Byron Andrew PRITCHARD, JR., William Collins Vining, Corey BOURASSA, Gregory Michael LASKOWSKI, David Vickery PARKER
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Publication number: 20160045923Abstract: An inertial separator for removing particles from a fluid stream includes a body defining a through passage, with at least one separator inlet and at least one separator outlet, a turn provided in the body between the at least one separator inlet and the at least one separator outlet, and a flow splitter having at least one particle outlet fluidly coupled to the outside of the through passage.Type: ApplicationFiled: May 15, 2015Publication date: February 18, 2016Inventors: Victor Hugo Silva CORREIA, Robert Francis MANNING, Jared Peter BUHLER
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Patent number: 8985944Abstract: A composite annular shroud supported by a support assembly including at least two single piece full 360 degree rings and at least partially disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement with an inner flange of the innermost ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.Type: GrantFiled: March 30, 2011Date of Patent: March 24, 2015Assignee: General Electric CompanyInventors: Jason David Shapiro, Jared Peter Buhler, Brian Kenneth Corsetti
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Publication number: 20140348636Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit.Type: ApplicationFiled: December 21, 2012Publication date: November 27, 2014Inventors: Jared Peter Buhler, Marshall Scott Allen, Daniel Edward Demers, Robert Francis Manning
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Publication number: 20140202168Abstract: A composite annular shroud supported by a support assembly including at least one ring and at least partially disposed within the ring. The shroud is biased against and in sealing engagement with an inner flange of the ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.Type: ApplicationFiled: March 20, 2014Publication date: July 24, 2014Inventors: Jason David Shapiro, Jared Peter Buhler, Brian Kenneth Corsetti
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Publication number: 20120247124Abstract: A composite annular shroud supported by a support assembly including at least two single piece full 360 degree rings and at least partially disposed within an innermost one of the rings. The shroud is biased against and in sealing engagement with an inner flange of the innermost ring. A three ring assembly includes the inner ring disposed radially inwardly of a middle ring disposed radially inwardly of an outer ring and the shroud at least partially disposed within the inner ring. At least three clocking pins extend radially inwardly from the middle ring through slots in the inner ring into notches in the shroud. The middle ring may be an aft end of a support ring fixedly connected to an engine backbone. Mounting pins may be press fitted into pin holes in the middle ring and extend radially outwardly from the middle ring through radial holes in the outer ring.Type: ApplicationFiled: March 30, 2011Publication date: October 4, 2012Inventors: Jason David Shapiro, Jared Peter Buhler, Brian Kenneth Corsetti