Patents by Inventor Ronald Scott

Ronald Scott 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).

  • Flowpath contouring
    Patent number: 10436068
    Abstract: A gas turbine engine includes a compressor section, combustion section, and turbine section. The turbine section includes a turbine component stage, the turbine component stage including a plurality of turbine components together including a flowpath surface along a circumferential direction of the gas turbine engine. The flowpath surface defines in part a core air flowpath of the gas turbine engine and further defines a contour along the circumferential direction. The contour repeats less frequently than once per turbine component to accommodate a hot gas streak through the turbine section.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: October 8, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Nozzle for a gas turbine engine
    Patent number: 10428664
    Abstract: A nozzle assembly for a gas turbine engine includes at least one pair of fixed vanes to define a nozzle between the pair of fixed vanes. The vanes can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator, which can comprise a virtual impactor, can have an accelerator for accelerating fluid moving through the virtual impactor such that the flow path is divided into a major flow moving into the interior chamber and a minor flow moving into a particle collector defined within the virtual impactor. The accelerator accelerates the fluid such that particles within the fluid are carried by their momentum into the particle collector with the minor flow, removing the particles from the major flow of fluid moving into the interior chamber.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: October 1, 2019
    Assignee: General Electric Company
    Inventors: Hojjat Nasr, Ronald Scott Bunker, Gregory Michael Laskowski, Erich Alois Krammer
  • Angled impingement inserts with cooling features
    Patent number: 10422235
    Abstract: An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings.
    Type: Grant
    Filed: May 15, 2015
    Date of Patent: September 24, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Airfoil having cooling circuit
    Patent number: 10415396
    Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Thermal stress relief of a component
    Patent number: 10415408
    Abstract: A component for a gas turbine engine includes a hot side wall, a plurality of connection walls, and a cold side wall. The hot side wall is exposed to a core air flowpath defined by the gas turbine engine. The cold side wall is spaced from the hot side wall and rigidly connected to the hot side wall through the plurality of connection walls. The hot side wall, connection walls, and cold side wall together define a cooling air cavity. The cold side wall defines a thermal stress relief slot for at least partially accommodating a relative thermal expansion between the hot side wall and the cold side wall to reduce an amount of thermal stress within the component during operation of the component.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Turbine engine with a rim seal between the rotor and stator
    Patent number: 10408075
    Abstract: An apparatus relating to a rim seal for turbine engine comprising a wing and discourager extending into a cavity to form a labyrinth fluid path. The wing and discourager can each include a radial extension. Cooling air can pass through the rim seal along the labyrinth fluid path to resist the ingestion of hot gas from a mainstream flow.
    Type: Grant
    Filed: August 16, 2016
    Date of Patent: September 10, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Systems and methods for multi-objective heuristics with conditional genes
    Patent number: 10402728
    Abstract: Systems and methods are provided to engage in multi-objective optimization where there may be potential solutions for evaluation (e.g., chromosomes) that each have one or more conditional genes. The value of each of the conditional genes in each of the chromosomes may be equivalent to one of a plurality of hidden genes in each of the chromosomes. The value of each of the conditional genes may be evaluated prior to determining objective values of each of the chromosomes. The objective values of each of the chromosomes may be used to evaluate the potential solutions embodied in the chromosomes and further drive to more optimized solutions. The use of the conditional genes in the chromosomes may reduce the amount of constraint violation checks that may need to be performed.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: September 3, 2019
    Assignee: The Aerospace Corporation
    Inventors: Timothy Guy Thompson, Matthew Phillip Ferringer, Ronald Scott Clifton, Catherine F. Horan, Kyle D. Hanifen
  • Closed loop cooling method and system with heat pipes for a gas turbine engine
    Patent number: 10400675
    Abstract: An apparatus and method of cooling a gas turbine engine including a core with a compressor section in which the compressor section includes a closed loop cooling circuit having a pump, at least one heat pipe extending from at least one of the stationary vanes, a heat exchanger located within the bypass air flow, and a coolant conduit passing fluidly coupled to the pump and heat exchanger and passing by the heat pipe. The pump pumps coolant through the coolant conduit to draw heat from the heat pipes into the coolant to form heated coolant, the heated coolant then passes through the heat exchanger, where the heat is rejected from the coolant to the bypass air to cool the coolant to form cooled coolant, which is then returned to the heat pipes.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: September 3, 2019
    Assignee: General Electric Company
    Inventors: Mohammed El Hacin Sennoun, Ronald Scott Bunker
  • ACTIVE ICE PRESS ASSEMBLY
    Publication number: 20190264970
    Abstract: An active ice press is provided herein and may be utilized to reshape an initial ice billet as a sculpted ice nugget. The active ice press may include a mold body and an electric heater. The mold body may define an axial direction and a mold cavity within which the sculpted ice nugget is shaped. The mold body may include a first mold segment and a second mold segment. The first mold segment may define a first cavity portion of the mold cavity. The second mold segment may be movably positioned above the first mold segment along the axial direction. The second mold segment may define a second cavity portion of the mold cavity. The electric heater may be disposed within the mold body in conductive thermal engagement with the mold cavity.
    Type: Application
    Filed: February 23, 2018
    Publication date: August 29, 2019
    Inventors: Ronald Scott Tarr, Justin Tyler Brown, Tomas Garces, Samuel Vincent DuPlessis
  • Engine component for a gas turbine engine
    Patent number: 10378444
    Abstract: 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: Grant
    Filed: August 19, 2015
    Date of Patent: August 13, 2019
    Assignee: General Electric Company
    Inventors: Robert Francis Manning, Ronald Scott Bunker, Robert Frederick Bergholz, Robert David Briggs
  • Airfoil with cooling circuit
    Patent number: 10358928
    Abstract: An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: July 23, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Additive manufacturing method for making complex film holes
    Patent number: 10350684
    Abstract: A method of forming a cooling hole structure on a turbine component. The turbine component has a component wall with inner and outer surfaces. A bore passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of: A) forming a recess communicating with the bore and the outer surface; and B) using an additive manufacturing process to form an exit region in the recess.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: July 16, 2019
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Airfoil having impingement openings
    Patent number: 10352177
    Abstract: An airfoil for a turbine engine having a perimeter wall bounding an interior and defining a pressure side and a suction side, a radially extending rib located within the interior and spaced from the leading edge to define a radially extending leading edge chamber, and at least one impingement opening in the rib defining a flow path aligned with the leading edge.
    Type: Grant
    Filed: February 16, 2016
    Date of Patent: July 16, 2019
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Robert David Briggs, Timothy Deryck Stone
  • Casting with a second metal component formed around a first metal component using hot isostactic pressing
    Patent number: 10343218
    Abstract: The present disclosure generally relates to casting molds including a casting shell surrounding at least a portion of a casting core comprising a first metal component and a hot isostactic pressed second metal component around the first metal component. In one aspect, the first metal component may have a lower melting point than the second metal component. In another aspect, the second metal component may retain some metal powder grain structure.
    Type: Grant
    Filed: February 29, 2016
    Date of Patent: July 9, 2019
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Douglas Gerard Konitzer
  • Trailing edge cooling for a turbine blade
    Patent number: 10344598
    Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: July 9, 2019
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Zachary Daniel Webster
  • REAGENTS AND METHODS FOR SCREENING MPS I, II, IIIA, IIIB, IVA, VI, AND VII
    Publication number: 20190144916
    Abstract: Reagents, methods, and kits for assaying enzymes associated with lysosomal storage diseases MPS-I, MPS-II, MPS-IIIA, MPS-IIIB, MPS-IVA, MPS-VI, and MPS VII.
    Type: Application
    Filed: December 18, 2018
    Publication date: May 16, 2019
    Applicant: University of Washington through its Center for Commercialization
    Inventors: Michael H. Gelb, Arun Babu Kumar, Frances Hocutt, Zdenek Spacil, Mariana Natali Barcenas Rodriguez, Frantisek Turecek, C. Ronald Scott
  • FILLET OPTIMIZATION FOR TURBINE AIRFOIL
    Publication number: 20190145265
    Abstract: 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: Application
    Filed: January 15, 2019
    Publication date: May 16, 2019
    Inventors: Jared Peter Buhler, Ronald Scott Bunker, Victor Hugo Silva Correia, Brian Kenneth Corsetti
  • Multiple Stage Shock Absorber with Gas Permeable Internal Floating Piston
    Publication number: 20190136933
    Abstract: Disclosed herein is a single shock body equipped with the gas permeable internal floating piston. The gas permeable internal floating piston was specifically designed for installation in the multiple stage air shock, the gas permeable internal floating piston being disclosed in the parent application. The gas permeable internal floating piston automatically separates the oil from the gas within the shock body thereby significantly reducing the complexity and cost of manufacturing a shock absorber with the gas permeable internal floating piston. Also, separation is maintained during the operation of the shock throughout the shock's lifetime. The gas permeable internal floating piston can operate with oils derived from either petroleum or synthetic base stocks, additives, and various gases including dry air, nitrogen, oxygen, carbon monoxide, carbon dioxide, helium, neon, and argon.
    Type: Application
    Filed: September 10, 2018
    Publication date: May 9, 2019
    Inventor: Ronald Scott Bandy
  • Turbine engine assembly and method of assembling the same
    Patent number: 10280760
    Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: May 7, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Narendra Digamber Joshi, Christian Lee Vandervort, Krishan Lal Luthra, Ronald Scott Bunker, Joel Meier Haynes, Venkat Eswarlu Tangirala
  • Metallo-silicate catalyst (MSC) compositions, methods of preparation and methods of use in partial upgrading of hydrocarbon feedstocks
    Patent number: 10272417
    Abstract: The invention relates to the preparation of novel bi- or tri metallic silicate micro-porous and/or meso-porous materials based on cerium, nickel, copper and/or zinc on a porous silicate framework matrix to use its molecular sieve effect to target preferentially the acidic organic molecules present in hydrocarbon feedstocks like crude oil, bitumen, VGO and the like. The chosen metals are selected based on their ability to activate steam and transfer oxygen for completing the oxidation of carboxylic compounds or decarboxylating them. These composite materials can be prepared under hydrothermal synthesis conditions in order to produce suitable porous solids where the metals are well dispersed and preferentially distributed inside the channels of the silicate framework where they can interact only with the molecules that can go inside the channels.
    Type: Grant
    Filed: August 4, 2017
    Date of Patent: April 30, 2019
    Assignees: PC-CUPS Ltd., CENOVUS ENERGY INC
    Inventors: Pedro Pereira Almao, Gerardo Vitale-Rojas, Maria Josefina Perez Zurita, Lante Antonio Carbognani, Ronald Scott Smith, Clementina Sosa