Patents by Inventor Robert Frederick Bergholz
Robert Frederick Bergholz 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: 20220170383Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.Type: ApplicationFiled: February 16, 2022Publication date: June 2, 2022Inventors: Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter
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Patent number: 11280215Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.Type: GrantFiled: October 28, 2015Date of Patent: March 22, 2022Assignee: General Electric CompanyInventors: Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter
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Patent number: 10386069Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.Type: GrantFiled: June 13, 2013Date of Patent: August 20, 2019Assignee: General Electric CompanyInventors: Shawn Michael Pearson, Robert Frederick Bergholz, Douglas Ray Smith, Frederick Alan Buck, Stephen Mark Molter, Kevin Robert Feldmann
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Patent number: 10378444Abstract: An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.Type: GrantFiled: August 19, 2015Date of Patent: August 13, 2019Assignee: General Electric CompanyInventors: Robert Francis Manning, Ronald Scott Bunker, Robert Frederick Bergholz, Robert David Briggs
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Patent number: 10370978Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.Type: GrantFiled: October 15, 2015Date of Patent: August 6, 2019Assignee: General Electric CompanyInventors: Matthew Lee Krumanaker, Steven Robert Brassfield, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
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Patent number: 10364681Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.Type: GrantFiled: October 15, 2015Date of Patent: July 30, 2019Inventors: Matthew Lee Krumanaker, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
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Patent number: 10208605Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.Type: GrantFiled: October 15, 2015Date of Patent: February 19, 2019Assignee: General Electric CompanyInventors: Matthew Lee Krumanaker, Steven Robert Brassfield, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
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Patent number: 10030525Abstract: A turbine component includes a component wall with inner and outer surfaces wherein a diffuser hole passes through the component wall between the inner surface and the outer surface. The diffuser hole has a hole axis and includes: a metering section extending from an inlet at the inner surface to a junction plane between the inner and outer surfaces; and a diffuser section extending from the junction plane to an outlet at the outer surface, and increasing in flow area from the junction plane to the outlet, the diffuser section having an upstream portion defining a first area ratio and a downstream portion defining a second area ratio different from the first area ratio.Type: GrantFiled: March 18, 2015Date of Patent: July 24, 2018Assignee: General Electric CompanyInventor: Robert Frederick Bergholz
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Publication number: 20170335716Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.Type: ApplicationFiled: October 28, 2015Publication date: November 23, 2017Inventors: Robert Frederick BERGHOLZ, Jason Randolph ALLEN, Robert David BRIGGS, Kevin Robert FELDMANN, Curtis Walton STOVER, Zachary Daniel WEBSTER, Fernando REITER
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Patent number: 9777635Abstract: An engine component includes a hot surface in thermal communication with a hot combustion gas flow, and a cooling surface, opposite the hot surface, along which a cooling fluid flows. At least one vortex generator is provided on the cooling surface, and can induce a vortex in the cooling fluid in response to contact with the flowing cooling fluid.Type: GrantFiled: December 31, 2014Date of Patent: October 3, 2017Assignee: General Electric CompanyInventors: Robert Frederick Bergholz, Aaron Ezekiel Smith
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Publication number: 20170191417Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.Type: ApplicationFiled: January 6, 2016Publication date: July 6, 2017Inventors: Ronald Scott Bunker, Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Byron Andrew Pritchard, JR., Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter, Michael Alan Meade
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Publication number: 20170107825Abstract: An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.Type: ApplicationFiled: October 15, 2015Publication date: April 20, 2017Inventors: Matthew Lee Krumanaker, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
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Publication number: 20170107829Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.Type: ApplicationFiled: October 15, 2015Publication date: April 20, 2017Inventors: Matthew Lee Krumanaker, Steven Robert Brassfield, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
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Publication number: 20170107824Abstract: A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.Type: ApplicationFiled: October 15, 2015Publication date: April 20, 2017Inventors: Matthew Lee Krumanaker, Steven Robert Brassfield, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
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Publication number: 20170051674Abstract: An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.Type: ApplicationFiled: August 19, 2015Publication date: February 23, 2017Inventors: Robert Francis Manning, Ronald Scott Bunker, Robert Frederick Bergholz, Robert David Briggs
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Publication number: 20160273364Abstract: A turbine component includes a component wall with inner and outer surfaces wherein a diffuser hole passes through the component wall between the inner surface and the outer surface. The diffuser hole has a hole axis and includes: a metering section extending from an inlet at the inner surface to a junction plane between the inner and outer surfaces; and a diffuser section extending from the junction plane to an outlet at the outer surface, and increasing in flow area from the junction plane to the outlet, the diffuser section having an upstream portion defining a first area ratio and a downstream portion defining a second area ratio different from the second area ratio.Type: ApplicationFiled: March 18, 2015Publication date: September 22, 2016Inventor: Robert Frederick BERGHOLZ
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Publication number: 20160201476Abstract: An airfoil for a turbine engine includes a cooling cavity and a cooling fluid supply cavity which supplies cooling fluid to the cooling cavity through a passage. The cooling cavity can be provided with a swirl feature for imparting a swirling motion to the cooling fluid.Type: ApplicationFiled: October 14, 2015Publication date: July 14, 2016Inventors: Ronald Scott BUNKER, Robert Frederick BERGHOLZ, Robert David BRIGGS, Kevin Robert FELDMANN
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Publication number: 20160186660Abstract: An engine component includes a hot surface in thermal communication with a hot combustion gas flow, and a cooling surface, opposite the hot surface, along which a cooling fluid flows. At least one vortex generator is provided on the cooling surface, and can induce a vortex in the cooling fluid in response to contact with the flowing cooling fluid.Type: ApplicationFiled: December 31, 2014Publication date: June 30, 2016Inventors: Robert Frederick Bergholz, Aaron Ezekiel Smith
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Patent number: 9175569Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes in downstream serial cooling flow relationship, a curved inlet, a constant area and constant width metering section, and a spanwise diverging section leading into the trailing edge cooling slot, and a spanwise height substantially greater than a hole width through the cooling hole. A pressure sidewall surface of the pressure sidewall may be planar through the metering and diverging sections. The width may be constant through the metering and diverging sections. A raised floor may include a flat up ramp in the diverging section, a flat down ramp in the slot.Type: GrantFiled: March 30, 2012Date of Patent: November 3, 2015Assignee: General Electric CompanyInventors: Robert Frederick Bergholz, Jr., Daniel Lee Durstock
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Patent number: 9145773Abstract: A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to trailing edge. Each cooling hole includes an asymmetric flow cross section through one or more asymmetric intermediate sections leading into slot. Flow cross section is asymmetric with respect to a mid-plane extending axially and spanwise through intermediate sections. Different trailing edge cooling holes may include different asymmetric flow cross sections. Lands may extend between the cooling slots. A raised floor may extend away from at least one of pressure or suction sidewalls at least partially through one or more asymmetric intermediate sections and optionally at least partially through cooling slot. Raised floor may include up and down ramps and a flat transition section between ramps.Type: GrantFiled: May 14, 2012Date of Patent: September 29, 2015Assignee: General Electric CompanyInventors: Robert Frederick Bergholz, Jr., Daniel Lee Durstock