Patents by Inventor Jacob John Kittleson

Jacob John Kittleson 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).

  • 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
  • Patent number: 10717101
    Abstract: A method of forming a cooling assembly in a turbomachine part is provided. The method includes placing an encapsulated diffuser insert partially into a hole in the turbomachine part. The encapsulated diffuser insert has an unobstructed central passageway with a generally circular cross-section at a first end and an elongated rectangular cross-section at a second end opposing the first end. The second end has a sacrificial cap. A coating step coats the turbomachine part to at least partially encapsulate the encapsulated diffuser insert in a coating. A removing step removes the sacrificial cap to enable air flow through the central passageway. The encapsulated diffuser insert remains in the hole of the turbomachine part and the coating, thereby providing the unobstructed central passageway with a generally circular first end and an elongated rectangular second end adjacent to an outer surface of the turbomachine part.
    Type: Grant
    Filed: February 16, 2018
    Date of Patent: July 21, 2020
    Assignee: General Electric Company
    Inventors: Tyler Christopher Henson, Jacob John Kittleson, Lauren Alexandra Schuhle
  • Patent number: 10605100
    Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.
    Type: Grant
    Filed: May 24, 2017
    Date of Patent: March 31, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jacob John Kittleson, John McConnell Delvaux
  • Patent number: 10584600
    Abstract: A ceramic matrix composite (CMC) turbine blade includes an airfoil, a hub extending from the airfoil, and a shank extending from the hub. The airfoil includes a leading edge, a trailing edge, a pressure side, and a suction side. The shank includes a dovetail root having a dovetail path curved in a radial plane. In some embodiments, a leading shank length of the shank at the leading edge and a trailing shank length of the shank at the trailing edge are greater than an intermediate shank length at an intermediate location between the leading edge and the trailing edge. At least one of the airfoil, the hub, and the shank is formed from a CMC. A method of forming the CMC turbine blade includes forming the dovetail root to have a dovetail path curved in a radial plane.
    Type: Grant
    Filed: June 14, 2017
    Date of Patent: March 10, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Jacob John Kittleson
  • Patent number: 10563524
    Abstract: A ceramic matrix composite (CMC) turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region. At least one central CMC ply extending from the root region is interwoven with at least one insert extending toward the narrowed neck region from the hub region. A method of forming a CMC turbine blade includes interweaving at least one central CMC ply extending from the root region with at least one insert extending toward the narrowed neck region from the hub region. The CMC turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region.
    Type: Grant
    Filed: June 14, 2017
    Date of Patent: February 18, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jacob John Kittleson, Peter De Diego
  • Patent number: 10533432
    Abstract: A preform CMC article is disclosed comprising an interior ply structure having at least one interior CMC ply including at least one longitudinal CMC ply disposed along the article length, an exterior shell ply forming an article surface and having at least one exterior CMC ply substantially surrounding the interior ply structure, and at least one wicking portion in which the interior ply structure penetrates the exterior ply shell with an exposed edge of the longitudinal CMC ply disposed at the article surface. A CMC article is disclosed including the interior ply structure and the exterior ply shell, wherein the longitudinal CMC ply includes an exposed edge disposed at the surface of the CMC article. A method for forming the CMC article is disclosed including wicking a melt infiltration agent into the article through the wicking portion into the interior ply structure along the longitudinal CMC ply.
    Type: Grant
    Filed: February 1, 2017
    Date of Patent: January 14, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jacob John Kittleson, James Murray, Gregory Scot Corman
  • Patent number: 10465533
    Abstract: A process of producing a hot gas path turbine component. The process includes forming a void in a first ceramic matrix composite ply and forming a void in a second ceramic matrix composite ply. The second ceramic matrix composite ply is positioned on the first ceramic matrix composite ply such that the positioning aligns the voids to at least partially define a cavity in the component. A third ceramic matrix composite ply is positioned on the first ceramic matrix composite ply and the first ceramic matrix composite ply, the second ceramic matrix composite ply and the third ceramic matrix composite ply are densified to form a densified body. The cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Victor John Morgan, Jacob John Kittleson, Andres Jose Garcia-Crespo, Benjamin Paul Lacy
  • Patent number: 10443410
    Abstract: A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: October 15, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Peter de Diego, Jacob John Kittleson
  • Publication number: 20190257207
    Abstract: A hollow CMC article, a mandrel for forming the article and a method for forming the article are disclosed. The article includes a ply-wrap layer defining a cavity. The ply-wrap layer includes a first face, a second face, a root portion bridging the faces, and a plurality of CMC wrap plies. The root portion defines a terminus of the ply-wrap layer including a cross-sectional conformation consisting of a curve having a single turning point. Each of the plurality of CMC wrap plies are disposed along the first face, wrap over the root portion, and extend along the second face. The hollow article further includes a plurality of CMC lateral plies disposed along the faces.
    Type: Application
    Filed: May 7, 2019
    Publication date: August 22, 2019
    Applicant: General Electric Company
    Inventors: Jacob John KITTLESON, James Murray
  • Publication number: 20190255550
    Abstract: A method of forming a cooling assembly in a turbomachine part is provided. The method includes placing an encapsulated diffuser insert partially into a hole in the turbomachine part. The encapsulated diffuser insert has an unobstructed central passageway with a generally circular cross-section at a first end and an elongated rectangular cross-section at a second end opposing the first end. The second end has a sacrificial cap. A coating step coats the turbomachine part to at least partially encapsulate the encapsulated diffuser insert in a coating. A removing step removes the sacrificial cap to enable air flow through the central passageway. The encapsulated diffuser insert remains in the hole of the turbomachine part and the coating, thereby providing the unobstructed central passageway with a generally circular first end and an elongated rectangular second end adjacent to an outer surface of the turbomachine part.
    Type: Application
    Filed: February 16, 2018
    Publication date: August 22, 2019
    Applicant: General Electric Company
    Inventors: Tyler Christopher Henson, Jacob John Kittleson, Lauren Alexandra Schuhle
  • Patent number: 10329927
    Abstract: A hollow CMC article, a mandrel for forming the article and a method for forming the article are disclosed. The article includes a ply-wrap layer defining a cavity. The ply-wrap layer includes a first face, a second face, a root portion bridging the faces, and a plurality of CMC wrap plies. The root portion defines a terminus of the ply-wrap layer including a cross-sectional conformation consisting of a curve having a single turning point. Each of the plurality of CMC wrap plies are disposed along the first face, wrap over the root portion, and extend along the second face. The hollow article further includes a plurality of CMC lateral plies disposed along the faces.
    Type: Grant
    Filed: August 15, 2016
    Date of Patent: June 25, 2019
    Assignee: General Electric Company
    Inventors: Jacob John Kittleson, James Murray
  • Patent number: 10273813
    Abstract: A process of producing a ceramic matrix composite component. The process includes positioning core plies on a mandrel. At least partially rigidizing the core plies to form a preform ceramic matrix composite arrangement defining a tip cavity and a hollow region. Ceramic matrix composite tip plies are positioned on the preform ceramic matrix composite arrangement and within the tip cavity. The ceramic matrix composite tip plies are densified to form a tip region of the composite component.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: April 30, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jacob John Kittleson, James Joseph Murray, III
  • Patent number: 10260358
    Abstract: A process of producing a ceramic matrix composite component. The process includes positioning a plurality of ceramic matrix composite plies on top of one another and forming a cavity therein. At least a portion of the cavity includes a terminal diameter sufficiently small to permit infiltration of a densifying material. The plurality of ceramic matrix composite plies are densified to form a densified body. The densifying results in the portion of the cavity including the terminal diameter being filled with densifying material and the cavity is present in the densified body. A ceramic matrix composite having cavities therein is also disclosed.
    Type: Grant
    Filed: October 29, 2015
    Date of Patent: April 16, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jacob John Kittleson, Victor John Morgan
  • Publication number: 20180363474
    Abstract: A ceramic matrix composite (CMC) turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region. At least one central CMC ply extending from the root region is interwoven with at least one insert extending toward the narrowed neck region from the hub region. A method of forming a CMC turbine blade includes interweaving at least one central CMC ply extending from the root region with at least one insert extending toward the narrowed neck region from the hub region. The CMC turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region.
    Type: Application
    Filed: June 14, 2017
    Publication date: December 20, 2018
    Inventors: Jacob John KITTLESON, Peter DE DIEGO
  • Publication number: 20180363475
    Abstract: A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.
    Type: Application
    Filed: June 16, 2017
    Publication date: December 20, 2018
    Inventors: Peter de DIEGO, Jacob John KITTLESON
  • Publication number: 20180363479
    Abstract: A ceramic matrix composite (CMC) turbine blade includes an airfoil, a hub extending from the airfoil, and a shank extending from the hub. The airfoil includes a leading edge, a trailing edge, a pressure side, and a suction side. The shank includes a dovetail root having a dovetail path curved in a radial plane. In some embodiments, a leading shank length of the shank at the leading edge and a trailing shank length of the shank at the trailing edge are greater than an intermediate shank length at an intermediate location between the leading edge and the trailing edge. At least one of the airfoil, the hub, and the shank is formed from a CMC. A method of forming the CMC turbine blade includes forming the dovetail root to have a dovetail path curved in a radial plane.
    Type: Application
    Filed: June 14, 2017
    Publication date: December 20, 2018
    Inventor: Jacob John KITTLESON
  • Publication number: 20180340429
    Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.
    Type: Application
    Filed: May 24, 2017
    Publication date: November 29, 2018
    Inventors: Jacob John KITTLESON, John McConnell DELVAUX
  • Publication number: 20180216477
    Abstract: A preform CMC article is disclosed comprising an interior ply structure having at least one interior CMC ply including at least one longitudinal CMC ply disposed along the article length, an exterior shell ply forming an article surface and having at least one exterior CMC ply substantially surrounding the interior ply structure, and at least one wicking portion in which the interior ply structure penetrates the exterior ply shell with an exposed edge of the longitudinal CMC ply disposed at the article surface. A CMC article is disclosed including the interior ply structure and the exterior ply shell, wherein the longitudinal CMC ply includes an exposed edge disposed at the surface of the CMC article. A method for forming the CMC article is disclosed including wicking a melt infiltration agent into the article through the wicking portion into the interior ply structure along the longitudinal CMC ply.
    Type: Application
    Filed: February 1, 2017
    Publication date: August 2, 2018
    Inventors: Jacob John KITTLESON, James MURRAY, Gregory Scot CORMAN
  • Patent number: 10022921
    Abstract: A turbine component patch delivery system can include a compressed gas source fluidly connected to a delivery line comprising a dispensing end. The turbine component patch delivery system can further include one or more turbine component patch carriers that can be projected out of the dispensing end of the delivery line by the compressed gas source, wherein each of the one or more turbine component patch carriers comprise a turbine component patch material housed within a breakaway shell.
    Type: Grant
    Filed: December 12, 2014
    Date of Patent: July 17, 2018
    Assignee: General Electric Company
    Inventors: Jacob John Kittleson, Don Mark Lipkin
  • Publication number: 20180106154
    Abstract: A method of forming an article includes forming a plurality of channels and ridges in a silicon-containing layer on a surface of a substrate of the article using a mask placed on the surface of the substrate or the silicon-containing layer.
    Type: Application
    Filed: October 13, 2016
    Publication date: April 19, 2018
    Inventors: Donald Joseph BALDWIN, Joshua Lee MARGOLIES, Jacob John Kittleson