Patents by Inventor Gary Michael Itzel

Gary Michael Itzel 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).

  • Patent number: 10774656
    Abstract: An airport having an exterior wall including a plurality of spaced layers for improved cooling and lifetime is disclosed. The airfoil and exterior wall are made by additive manufacturing. The exterior wall includes an exterior layer, an intermediate layer, and an interior layer each separated from adjacent layers by a plurality of standoff members; a plurality of first cooling chambers between the exterior and intermediate layers, the chambers partitioned by a first partitioning wall; a plurality of second cooling chambers between in the intermediate and interior layers, the chambers partitioned by a second partitioning wall; a thermal barrier coating on the exterior layer; a plurality of impingement openings in the intermediate layer and a second plurality of impingement openings in the interior layer; and a plurality of cooling passages in the exterior layer. The exterior layer may also include plateaus on an exterior face through which the cooling passages extend.
    Type: Grant
    Filed: April 9, 2018
    Date of Patent: September 15, 2020
    Assignee: General Electric Company
    Inventors: Gary Michael Itzel, Jeffrey Clarence Jones, James William Vehr
  • Publication number: 20200240273
    Abstract: A component includes an outer wall that includes an exterior surface, and at least one plenum defined interiorly to the outer wall and configured to receive a cooling fluid therein. The component also includes a coating system disposed on the exterior surface. The coating system has a thickness. The component further includes a plurality of adaptive cooling openings defined in the outer wall. Each of the adaptive cooling openings extends from a first end inflow communication with the at least one plenum, outward through the exterior surface and to a second end covered underneath at least a portion of the thickness of the coating system.
    Type: Application
    Filed: October 13, 2017
    Publication date: July 30, 2020
    Inventors: James Albert TALLMAN, Andrew Philip SHAPIRO, Gary Michael ITZEL, Curtis Alan JOHNSON, Victor John MORGAN, Jacob John KITTLESON, Bradley Thomas RICHARDS
  • Publication number: 20200182067
    Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
    Type: Application
    Filed: February 11, 2020
    Publication date: June 11, 2020
    Inventors: Sandip DUTTA, James ZHANG, Gary Michael ITZEL, John McConnell DELVAUX, Matthew Troy HAFNER
  • Patent number: 10655477
    Abstract: Turbine components are disclosed including a component wall defining a constrained portion, a manifold having an impingement wall, and a post-impingement cavity disposed between the manifold and the component wall. The impingement wall includes a wall thickness and defines a plenum and a tapered portion. The tapered portion tapers toward the constrained portion and includes a plurality of impingement apertures and a wall inflection. The wall inflection is disposed proximal to the constrained portion, and the tapered portion is integrally formed as a single, continuous object. The wall inflection may include an inflection radius of less than about 3 times the wall thickness of the impingement wall, or the tapered portion may include a consolidated portion with the impingement wall extending across the plenum. A method for forming the turbine component is also disclosed, including forming the tapered portion as a single, continuous tapered portion by an additive manufacturing technique.
    Type: Grant
    Filed: July 26, 2016
    Date of Patent: May 19, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sandip Dutta, Benjamin Paul Lacy, Gary Michael Itzel, Joseph Anthony Weber, David Edward Schick
  • Patent number: 10633979
    Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage extending between a root and a tip of the airfoil. The airfoil further defines a pocket positioned between the cooling passage and an exterior surface of the airfoil and spaced apart from the cooling passage and the exterior surface. The pocket provides a thermal impediment between the cooling passage and the exterior surface of the airfoil.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: April 28, 2020
    Assignee: General Electric Company
    Inventors: Sandip Dutta, Gary Michael Itzel
  • Patent number: 10590776
    Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of axial cooling channels in the trailing edge portion of the airfoil are arranged to permit axial flow of a cooling fluid from an interior of the turbine component at the trailing edge portion to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a trailing edge portion with axial cooling channels. The axial cooling channels are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
    Type: Grant
    Filed: June 6, 2016
    Date of Patent: March 17, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sandip Dutta, James Zhang, Gary Michael Itzel, John McConnell Delvaux, Matthew Troy Hafner
  • Patent number: 10570750
    Abstract: A turbine component includes an airfoil having an airfoil chamber disposed within the airfoil, the airfoil chamber configured to supply a coolant through the airfoil. The tip of the airfoil includes a rail extending radially from the tip plate, the rail including an inner rail surface defining a tip pocket therein, an outer rail surface and a radially outward facing rail surface between the inner rail surface and the outer rail surface. A tip rail cavity is within and partially circumscribes the rail, the tip rail cavity receiving a coolant flow. A tip rail cooling passage includes an inlet fluidly coupled to the tip rail cavity, a passage length fluidly coupled to the inlet and partially circumscribing the rail, a metering element fluidly coupled to the passage length, and an outlet fluidly coupled to the metering element and extending through the radially outward facing rail surface.
    Type: Grant
    Filed: December 6, 2017
    Date of Patent: February 25, 2020
    Assignee: General Electric Company
    Inventors: Nicholas William Rathay, Gary Michael Itzel
  • Publication number: 20200049017
    Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.
    Type: Application
    Filed: October 18, 2019
    Publication date: February 13, 2020
    Inventors: Sandip DUTTA, James ZHANG, Gary Michael ITZEL, John McConnell DELVAUX, Matthew Troy HAFNER
  • Patent number: 10550721
    Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: February 4, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Troy Hafner, Gary Michael Itzel, John McConnell Delvaux, Sandip Dutta
  • Patent number: 10480327
    Abstract: A component configured for impingement cooling includes an inner wall defining a plurality of apertures. Each aperture of the plurality of apertures is configured to emit a cooling fluid therethrough. The component also includes an outer wall spaced from the inner wall. The outer wall and the inner wall extend along a longitudinal axis of the component. The component further includes a plurality of angled walls extending between the inner wall and the outer wall. The plurality of angled walls define a plurality of angled channels in fluid communication with the plurality of apertures. Each angled wall of the plurality of angled walls extends at an acute angle relative to the longitudinal axis.
    Type: Grant
    Filed: January 3, 2017
    Date of Patent: November 19, 2019
    Assignee: General Electric Company
    Inventors: Nicholas William Rathay, James Albert Tallman, Gary Michael Itzel
  • Patent number: 10472973
    Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.
    Type: Grant
    Filed: June 6, 2016
    Date of Patent: November 12, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sandip Dutta, James Zhang, Gary Michael Itzel, John McConnell Delvaux, Matthew Troy Hafner
  • Patent number: 10472980
    Abstract: A seal in a gas turbine for sealing a radial gap defined between rotating and stationary structure. The rotating structure may include a row of rotor blades. The seal may include a pad attached to the stationary structure. The pad may include an abradable structure. The pad may further include a liner attached to and covering an outer surface of the abradable structure. The stationary structure to which the pad is attached may define an axial section of the outer radial boundary of the annular flowpath, the axial section coinciding axially with an axial position of the row of rotor blades.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: November 12, 2019
    Assignee: General Electric Company
    Inventors: Gary Michael Itzel, Ibrahim Sezer
  • Publication number: 20190309634
    Abstract: An airport having an exterior wall including a plurality of spaced layers for improved cooling and lifetime is disclosed. The airfoil and exterior wall are made by additive manufacturing. The exterior wall includes an exterior layer, an intermediate layer, and an interior layer each separated from adjacent layers by a plurality of standoff members; a plurality of first cooling chambers between the exterior and intermediate layers, the chambers partitioned by a first partitioning wall; a plurality of second cooling chambers between in the intermediate and interior layers, the chambers partitioned by a second partitioning wall; a thermal barrier coating on the exterior layer; a plurality of impingement openings in the intermediate layer and a second plurality of impingement openings in the interior layer; and a plurality of cooling passages in the exterior layer. The exterior layer may also include plateaus on an exterior face through which the cooling passages extend.
    Type: Application
    Filed: April 9, 2018
    Publication date: October 10, 2019
    Inventors: Gary Michael Itzel, Jeffrey Clarence Jones, James William Vehr
  • Patent number: 10392944
    Abstract: Various aspects include a turbomachine component, along with a turbomachine and related storage medium. In some cases, the turbomachine component includes: a body defining an inner cavity, the body having an outer surface and an inner surface opposing the outer surface, the inner surface facing the inner cavity; and a mount coupled with the inner surface of the body, the mount including: an impingement baffle coupled with and separated from the inner surface of the body, the impingement baffle including a set of apertures configured to permit flow of a heat transfer fluid therethrough to contact the inner surface of the body; and a reclamation channel connected with the impingement baffle for reclaiming the heat transfer fluid.
    Type: Grant
    Filed: July 12, 2016
    Date of Patent: August 27, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: James Albert Tallman, Gary Michael Itzel
  • Patent number: 10385727
    Abstract: A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band define a first set of cooling channels and a second set of cooling channels formed beneath a gas side surface of the corresponding inner band or outer band. The inner band or the outer band further define a coolant distribution plenum that is in fluid communication with the first and second sets of cooling channels. The coolant distribution plenum provides a stream of coolant to at least one of the first set of cooling channels and the second set of cooling channels.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: Sandip Dutta, Benjamin Paul Lacy, Gary Michael Itzel, James William Vehr
  • Publication number: 20190169999
    Abstract: A turbine component includes an airfoil having an airfoil chamber disposed within the airfoil, the airfoil chamber configured to supply a coolant through the airfoil. The tip of the airfoil includes a rail extending radially from the tip plate, the rail including an inner rail surface defining a tip pocket therein, an outer rail surface and a radially outward facing rail surface between the inner rail surface and the outer rail surface. A tip rail cavity is within and partially circumscribes the rail, the tip rail cavity receiving a coolant flow. A tip rail cooling passage includes an inlet fluidly coupled to the tip rail cavity, a passage length fluidly coupled to the inlet and partially circumscribing the rail, a metering element fluidly coupled to the passage length, and an outlet fluidly coupled to the metering element and extending through the radially outward facing rail surface.
    Type: Application
    Filed: December 6, 2017
    Publication date: June 6, 2019
    Inventors: Nicholas William Rathay, Gary Michael Itzel
  • Patent number: 10287894
    Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. A plurality of nested cooling channels in the trailing edge portion of the airfoil permit passage of a cooling fluid from an interior of the turbine component to an exterior of the turbine component at the trailing edge portion. A method of making a turbine component includes forming an airfoil having a leading edge, a trailing edge portion extending to a trailing edge, and a plurality of nested cooling channels in the trailing edge portion. Each nested cooling channel fluidly connects an interior of the turbine component with an exterior of the turbine component at the trailing edge portion. A method of cooling a turbine component is also disclosed.
    Type: Grant
    Filed: June 6, 2016
    Date of Patent: May 14, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sandip Dutta, James Zhang, Gary Michael Itzel, John McConnell Delvaux, Matthew Troy Hafner
  • Patent number: 10260356
    Abstract: The present disclosure is directed to a nozzle cooling system for a gas turbine engine. An impingement plate is positioned radially inwardly from a radially inner surface of an inner side wall of a nozzle. The impingement plate and the inner side wall collectively define an inner chamber. The impingement plate includes a first portion defining one or more impingement apertures and a second portion defining one or more post-impingement apertures. A duct plate encloses the first portion of the impingement plate. The duct plate, the first portion of the impingement plate, and inner side wall collectively define an outer chamber in fluid communication with the inner chamber through the one or more impingement apertures. Compressed air from the outer chamber flows through the one or more impingement apertures into the inner chamber and exits the inner chamber through the one or more post-impingement apertures.
    Type: Grant
    Filed: June 2, 2016
    Date of Patent: April 16, 2019
    Assignee: General Electric Company
    Inventors: Travis Michael Gaulden, Gary Michael Itzel, Robert Carl Meyer
  • Patent number: 10208614
    Abstract: Apparatuses are disclosed including a first article, a second article, a sewing member and a thermal break. The second article includes a second material composition having a second thermal tolerance greater than a first thermal tolerance of a first material composition of the first article. The sealing member is disposed between and contacts the first article and the second article, and includes a third material composition having a third thermal tolerance less than the second thermal tolerance and less than an operating temperature of the second article. The thermal break is defined by the second article, and is proximate to the sealing member and partitioned from the sealing member by a portion of the second article. The thermal break interrupts a thermal conduction path from the second article to the sealing member. The first article and the second article compress the sealing member, forming a thermal gradient-tolerant seal.
    Type: Grant
    Filed: February 26, 2016
    Date of Patent: February 19, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Matthew Troy Hafner, Gary Michael Itzel, Sandip Dutta
  • Publication number: 20180340427
    Abstract: The present disclosure is directed to a rotor blade for a turbomachine. The rotor blade includes an airfoil defining a cooling passage extending between a root and a tip of the airfoil. The airfoil further defines a pocket positioned between the cooling passage and an exterior surface of the airfoil and spaced apart from the cooling passage and the exterior surface. The pocket provides a thermal impediment between the cooling passage and the exterior surface of the airfoil.
    Type: Application
    Filed: May 24, 2017
    Publication date: November 29, 2018
    Inventors: Sandip Dutta, Gary Michael Itzel