Patents by Inventor Zachary John Snider

Zachary John Snider 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: 10612393
    Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: April 7, 2020
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Allison Christine Gose, Daniel Burnos, Gregory Thomas Foster
  • Publication number: 20200072073
    Abstract: A turbine engine having a variable nozzle assembly that includes: a variable nozzle having an airfoil that extends radially across an annulus formed between inner and outer platforms; and a segmented shaft that translates a torque between segments included therewithin. The segmented shaft may include a first and second segment. The first segment of the segmented shaft may include: the airfoil of the variable nozzle; an outer stem extending from the outer end of the airfoil; and an inner stem extending from the inner end of the airfoil. A first and second connector may connect the first segment to the inner platform and outer platform, respectively. A third connector may connect the first segment to the second segment. The first and second connector may include a first and second spherical bearing, respectively. The third connector may include a first universal joint.
    Type: Application
    Filed: August 29, 2018
    Publication date: March 5, 2020
    Applicant: General Electric Company
    Inventors: Zachary John Snider, Gary Charles Liotta
  • Publication number: 20200072086
    Abstract: A method for constructing a variable nozzle assembly within a turbine engine that includes: constructing a variable nozzle sub-assembly; attaching the variable nozzle sub-assembly to a casing; and linking segments of a segmented shaft via an opening. Constructing the variable nozzle sub-assembly may include: attaching a downstream inner platform to a upstream inner platform; inserting an outer stem of a first segment through an outer stem opening formed through the downstream outer platform; connecting the first segment to the downstream outer platform by loading a first bearing about a protruding spherical shaped section of the outer stem; inserting the inner stem through an opening formed through the downstream inner platform while aligning sidewalls of the downstream and upstream outer platforms; mechanically securing the aligned sidewalls; and connecting the first segment to the downstream inner platform by loading a second bearing about a protruding spherical shaped section of the inner stem.
    Type: Application
    Filed: August 29, 2018
    Publication date: March 5, 2020
    Applicant: General Electric Company
    Inventors: Zachary John Snider, Gary Charles Liotta
  • Publication number: 20200025026
    Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.
    Type: Application
    Filed: July 19, 2018
    Publication date: January 23, 2020
    Inventors: Travis J Packer, Benjamin Paul Lacy, Ibrahim Sezer, Zachary John Snider, Brad Wilson VanTassel
  • Patent number: 10465521
    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body and a coolant return passage extends within the airfoil body, with each passage having respective a supply and return connection passage to an exterior surface of the airfoil body. A seat in the exterior surface of the airfoil body receives a cover that includes a trench on an interior surface thereof to fluidly connect the return connection passage and the supply connection passage and form a coolant passage for the airfoil body. Various arrangements of cooling circuits may be created with the cover that allow for reuse of the coolant.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: November 5, 2019
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Gregory Thomas Foster, Srikanth Chandrudu Kottilingam
  • Patent number: 10260363
    Abstract: Aspects of the disclosure include a sealing insert, turbine component, and code for manufacturing a sealing insert. A sealing insert includes at least one insert wall for insertion proximate a component wall to define a space between the at least one insert wall and the component wall. At least one compressible seal is provided between the at least one insert wall and the component wall. The compressible seal or seals divide the space into a plurality of compartments.
    Type: Grant
    Filed: December 8, 2016
    Date of Patent: April 16, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Zachary John Snider, Sandip Dutta, Kassy Moy Hart
  • Publication number: 20190107499
    Abstract: The present application thus provides a thermal barrier coating spallation detection system for a gas turbine. The thermal barrier coating spallation detection system may include a hot gas path component with a phosphor layer and a thermal barrier coating, a stimulant radiation source, and an optical device such that the optical device directs stimulant radiation at the thermal barrier coating and receives emission radiation. A change in the received emission radiation indicates spallation of the thermal barrier coating.
    Type: Application
    Filed: October 6, 2017
    Publication date: April 11, 2019
    Inventors: Andrew David Ellis, Kurt Kramer Schleif, Zachary John Snider
  • Patent number: 10233761
    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: March 19, 2019
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Gregory Thomas Foster, Joseph Anthony Weber, James Fredric Wiedenhoefer
  • Publication number: 20180371920
    Abstract: A hollowed body component made by additive manufacturing is disclosed. The hollow body has a longitudinal extent, an exterior surface and an interior surface, the interior surface having a first side and an opposing, second side. A first set of curved supports are curved along lengths thereof and extend between the first side and the opposing, second side to support the hollow body at least during the additive manufacturing thereof. Some embodiments include cooling passages open to the interior surface. Here, the curved supports extend between opposing pairs of passage-free spaces on the interior surface to support the hollow body at least during the additive manufacturing thereof. In one example, the component is an impingement insert for a hot gas path component.
    Type: Application
    Filed: June 26, 2017
    Publication date: December 27, 2018
    Inventors: Travis J Packer, Elisabeth Kraus Black, Robert William Davidoff, Zachary John Snider
  • Publication number: 20180363471
    Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.
    Type: Application
    Filed: June 15, 2017
    Publication date: December 20, 2018
    Inventors: Zachary John Snider, Allison Christine Gose, Daniel Burnos, Gregory Thomas Foster
  • Publication number: 20180363470
    Abstract: A turbine airfoil includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a cooling air supply cavity disposed within the turbine airfoil, and a near wall cooling cavity disposed within the turbine airfoil and fluidly coupled to the cooling air supply cavity to receive cooling air. In addition, the near wall cooling cavity partially extends along the suction side wall from adjacent the leading edge to a location more proximal the trailing edge. Moreover, the near wall cooling cavity provides near wall cooling to a high heat load region along the suction side wall.
    Type: Application
    Filed: June 15, 2017
    Publication date: December 20, 2018
    Inventors: Zachary John Snider, Daniel Burnos, Lana Maria Osusky, Brian Gene Brzek, Gregory Thomas Foster
  • Publication number: 20180194688
    Abstract: A CMC ply assembly is disclosed including at least one matrix ply interspersed amongst a plurality of CMC plies. Each of the plurality of CMC plies includes a first matrix and a plurality of ceramic fibers. The at least one matrix ply includes a second matrix and is essentially free of ceramic fibers. The plurality of CMC plies and the at least one matrix ply are arranged in an undensified ply stack having an article conformation. A CMC article is disclosed including a plurality of densified CMC plies and at least one densified matrix ply interspersed amongst the plurality of densified CMC plies. A method for forming the CMC article is disclosed including forming, carburizing, infusing a melt infiltration agent into, and densifying the CMC ply assembly. The melt infiltration agent infuses more completely through the at least one matrix ply than through the plurality of CMC plies.
    Type: Application
    Filed: January 9, 2017
    Publication date: July 12, 2018
    Inventors: Matthew Troy HAFNER, John McConnell DELVAUX, Glenn Curtis TAXACHER, Zachary John SNIDER
  • Publication number: 20180163555
    Abstract: Aspects of the disclosure include a sealing insert, turbine component, and code for manufacturing a sealing insert. A sealing insert includes at least one insert wall for insertion proximate a component wall to define a space between the at least one insert wall and the component wall. At least one compressible seal is provided between the at least one insert wall and the component wall. The compressible seal or seals divide the space into a plurality of compartments.
    Type: Application
    Filed: December 8, 2016
    Publication date: June 14, 2018
    Inventors: Zachary John Snider, Sandip Dutta, Kassy Moy Hart
  • Publication number: 20180149028
    Abstract: The present disclosure is directed to a gas turbine engine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
    Type: Application
    Filed: November 30, 2016
    Publication date: May 31, 2018
    Inventors: Sandip Dutta, Benjamin Paul Lacy, Gary Michael Itzel, Zachary John Snider
  • Publication number: 20180112534
    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body and a coolant return passage extends within the airfoil body, with each passage having respective a supply and return connection passage to an exterior surface of the airfoil body. A seat in the exterior surface of the airfoil body receives a cover that includes a trench on an interior surface thereof to fluidly connect the return connection passage and the supply connection passage and form a coolant passage for the airfoil body. Various arrangements of cooling circuits may be created with the cover that allow for reuse of the coolant.
    Type: Application
    Filed: October 26, 2016
    Publication date: April 26, 2018
    Inventors: Zachary John Snider, Gregory Thomas Foster, Srikanth Chandrudu Kottilingam
  • Publication number: 20180112547
    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
    Type: Application
    Filed: October 26, 2016
    Publication date: April 26, 2018
    Inventors: Zachary John Snider, Gregory Thomas Foster, Joseph Anthony Weber, James Fredric Wiedenhoefer
  • Publication number: 20180017466
    Abstract: A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.
    Type: Application
    Filed: September 27, 2017
    Publication date: January 18, 2018
    Applicant: General Electric Company
    Inventors: Andrea Booher Kretschmar, Zachary John Snider, Nathan Lee Brown, Kurt Kramer Schleif, Michael Allen Ball
  • Patent number: 9863269
    Abstract: A system for packaging electronic components in a rotatable shaft includes an annular carrier shaft having a first end that is axially spaced from a second end and an inner surface that is radially spaced from an outer surface, and a plurality of transmitter assemblies annularly arranged within the carrier shaft. Each transmitter assembly includes a transmitter housing radially supported within the carrier shaft via a pair of circumferentially spaced rail members. Each transmitter assembly comprises a daughter board that extends laterally and longitudinally across a bottom portion of the transmitter housing and at least one electronic component electrically coupled to the daughter board. The electronic component extends substantially perpendicular to the daughter board within the transmitter housing.
    Type: Grant
    Filed: November 10, 2016
    Date of Patent: January 9, 2018
    Assignee: General Electric Company
    Inventors: Donald W. Shaw, Kurt Kramer Schleif, Zachary John Snider
  • Publication number: 20170342910
    Abstract: The present disclosure is directed to a system for attaching an instrument lead to a gas turbine engine component. The system includes a gas turbine engine component that includes a surface. A first sleeve couples to the surface of the gas turbine engine component. The first sleeve defines a first sleeve passageway extending therethrough. An instrument lead extends through the first sleeve passageway. A first potting material couples the instrument lead to the first sleeve to prevent the instrument lead from moving longitudinally relative to the first sleeve.
    Type: Application
    Filed: May 25, 2016
    Publication date: November 30, 2017
    Inventors: Zachary John Snider, Joshua Lee Margolies, Kurt Kramer Schleif
  • Patent number: 9777589
    Abstract: A system for routing rotatable wire bundles which extend from a rotor shaft of a turbomachine includes a plurality of wire bundles which extend outwardly from an inner passage of the rotor shaft of the turbomachine. An annular wire barrel is coupled to an end of the rotor shaft. A plurality of thru-holes is defined within and/or by the wire barrel. The plurality of thru-holes is annularly arranged therein. Each thru-hole extends through an aft wall of the wire barrel and is circumferentially spaced from adjacent thru-holes. Each wire bundle extends individually through a corresponding thru-hole of the plurality of thru-holes.
    Type: Grant
    Filed: October 24, 2014
    Date of Patent: October 3, 2017
    Assignee: General Electric Company
    Inventors: Kurt Kramer Schleif, Donald W. Shaw, Zachary John Snider, Mario Joseph Arceneaux