Patents by Inventor Brian Kenneth Corsetti
Brian Kenneth Corsetti 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: 20240117743Abstract: An apparatus for an engine component in a turbine engine. The engine component including a wall with a cooling hole having a passage extending between an inlet fluidly coupled to a cooling fluid flow and an outlet at a heated surface. The cooling hole including a layup surface defining a first angle (?) and a layback surface defining a second angle (?).Type: ApplicationFiled: October 5, 2022Publication date: April 11, 2024Inventors: Brian Kenneth Corsetti, John Curtis Calhoun, Dane Michael Dale
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Patent number: 10822957Abstract: 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: GrantFiled: January 15, 2019Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Patent number: 10436038Abstract: 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: GrantFiled: May 24, 2016Date of Patent: October 8, 2019Assignee: General Electric CompanyInventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Patent number: 10392950Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.Type: GrantFiled: May 7, 2015Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Victor Hugo Silva Correia, Brian Kenneth Corsetti, Mark Broomer
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Publication number: 20190145265Abstract: 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: January 15, 2019Publication date: May 16, 2019Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Patent number: 10267161Abstract: 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: GrantFiled: December 7, 2015Date of Patent: April 23, 2019Assignee: General Electric CompanyInventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Patent number: 10227876Abstract: 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: GrantFiled: December 7, 2015Date of Patent: March 12, 2019Assignee: General Electric CompanyInventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
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Publication number: 20190024513Abstract: An airfoil for a turbine engine can include a body having an outer wall defining a pressure side and a suction side, and the body can extend axially between a truncated nose and a trailing edge. A shield can be positioned upstream of the nose to define a leading edge for the airfoil.Type: ApplicationFiled: July 19, 2017Publication date: January 24, 2019Inventors: Robert Francis Manning, Mark Broomer, Brian Kenneth Corsetti
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Publication number: 20180216467Abstract: A turbine engine, such as a gas turbine engine for an aircraft, can include a compressor section, a combustion section, and a turbine section in axial arrangement. The compressor and turbine sections can include a rotating disk having a plurality of blades and a stationary band having a plurality of stationary vanes. The disk and band are spaced axially defining a buffer cavity. One or more extensions extend into the buffer cavity to prevent ingestion of heated gas into the buffer cavity. Recesses on the underside of the extensions can improve the heat transfer coefficient for the extensions.Type: ApplicationFiled: February 2, 2017Publication date: August 2, 2018Inventors: Brian Kenneth Corsetti, Christopher Michael Ceglio, Robert Francis Manning
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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: 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: 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: 20170058684Abstract: A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.Type: ApplicationFiled: May 7, 2015Publication date: March 2, 2017Inventors: Victor Hugo Silva CORREIA, Brian Kenneth CORSETTI, Mark BROOMER
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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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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: 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