Patents by Inventor Steven Douglas Johnson

Steven Douglas Johnson 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: 11674405
    Abstract: An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.
    Type: Grant
    Filed: August 30, 2021
    Date of Patent: June 13, 2023
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Neelesh Nandkumar Sarawate
  • Patent number: 11674396
    Abstract: A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.
    Type: Grant
    Filed: July 30, 2021
    Date of Patent: June 13, 2023
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Jonathan Russell Ratzlaff, Craig Alan Gonyou
  • Publication number: 20230060175
    Abstract: An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.
    Type: Application
    Filed: August 30, 2021
    Publication date: March 2, 2023
    Inventors: Steven Douglas Johnson, Neelesh Nandkumar Sarawate
  • Publication number: 20230066740
    Abstract: A passive flow modulation device for a machine defining an axial direction and a radial direction, the passive flow modulation device including: a first ring with a first coefficient of thermal expansion; a second ring disposed coaxially with the first ring and positioned at least partially inward of the first ring along the radial direction, spaced from the first ring along the axial direction, or both, the first ring, the second ring, or both defining at least in part one or more passages, the second ring with a second coefficient of thermal expansion that is less than the first coefficient of thermal expansion to passively modulate a size of the one or more passages during operation.
    Type: Application
    Filed: August 30, 2021
    Publication date: March 2, 2023
    Inventors: Steven Douglas Johnson, Yu-Liang Lin, Craig Alan Gonyou, Scott Alan Schimmels, Jeffrey Douglas Rambo, Brian Gregg Feie
  • Publication number: 20230059027
    Abstract: A gas turbine engine defining an axial direction and a radial direction, and including a primary cooling circuit configured to receive a first flow of air; and a turbine rotor comprising a rotor blade, the rotor blade defining at least in part a forward wheelspace that is located forward of the rotor blade, the forward wheelspace configured to receive a second flow of air, the rotor blade further defining: a first cooling circuit internal to the rotor blade and in fluid communication with the primary cooling circuit for receiving the first flow of air from the primary cooling circuit; a second cooling circuit internal to the rotor blade and in fluid communication with the forward wheelspace for receiving a portion of the second flow of air from the forward wheelspace; and a means for drawing a portion of the second flow of air into the second cooling circuit.
    Type: Application
    Filed: August 23, 2021
    Publication date: February 23, 2023
    Inventor: Steven Douglas Johnson
  • Publication number: 20230036206
    Abstract: A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.
    Type: Application
    Filed: July 30, 2021
    Publication date: February 2, 2023
    Inventors: Steven Douglas Johnson, Jonathan Russell Ratzlaff, Craig Alan Gonyou
  • Publication number: 20220389825
    Abstract: A turbine engine comprising an engine core having at least a compressor section, a combustor section, and a turbine section in axial flow arrangement defining an axial direction and an engine centerline. The turbine engine further having a rotor and a stator, a carriage assembly carried by the stator, and a seal assembly biased toward the rotor.
    Type: Application
    Filed: June 4, 2021
    Publication date: December 8, 2022
    Inventors: Steven Douglas Johnson, Kevin Randall McManus, Rahul Anil Bidkar
  • Patent number: 11492972
    Abstract: An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.
    Type: Grant
    Filed: December 30, 2019
    Date of Patent: November 8, 2022
    Assignee: General Electric Company
    Inventors: Craig Alan Gonyou, Robert Proctor, Christopher Michael Thompson, Scott Alan Schimmels, Steven Douglas Johnson
  • Publication number: 20220282925
    Abstract: A heat exchanger is provided. The heat exchanger includes a first wall manifold. The heat exchanger further includes a second wall manifold spaced apart from the first wall manifold. The heat exchanger further includes a plurality of vanes that extend generally circumferentially between the first wall manifold and the second wall manifold. The heat exchanger further includes a plurality of fluid circuits defined within the heat exchanger. Each fluid circuit in the plurality of fluid circuits includes an inlet channel portion and an outlet channel portion defined within the first wall manifold. A return channel portion defined within the second wall manifold. At least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes. The at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.
    Type: Application
    Filed: March 2, 2021
    Publication date: September 8, 2022
    Inventors: Nicholas M. Daggett, Steven Douglas Johnson, Anand P. Roday, Scott Alan Schimmels
  • Publication number: 20220282670
    Abstract: A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.
    Type: Application
    Filed: March 2, 2021
    Publication date: September 8, 2022
    Inventors: Daniel Alan Niergarth, Nicholas M. Daggett, Steven Douglas Johnson, Anand P. Roday, Scott Alan Schimmels
  • Patent number: 11391176
    Abstract: A gas turbine engine that includes a turbine interstage region. The turbine interstage region is configured to conduct bore bleed air outwardly. The interstage region includes a central plenum. The interstage region also includes a first mid-seal and a second mid-seal. The central plenum is fluidly connected to bore bleed air by a flow circuit that passes between the first mid-seal and the second mid-seal.
    Type: Grant
    Filed: December 16, 2019
    Date of Patent: July 19, 2022
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Nicholas R. Dinsmore, Daniel Tyler Jarboe
  • Publication number: 20220213802
    Abstract: A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.
    Type: Application
    Filed: January 6, 2021
    Publication date: July 7, 2022
    Inventors: Steven Douglas Johnson, Julius John Montgomery, Brandon Wayne Miller, Robert Proctor, Bradley W. Fintel, Jeffrey Douglas Rambo
  • Publication number: 20220154644
    Abstract: A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.
    Type: Application
    Filed: November 16, 2020
    Publication date: May 19, 2022
    Inventors: Steven Douglas Johnson, Jonathan Russell Ratzlaff
  • Patent number: 11300368
    Abstract: A cross-flow heat exchanger for gas turbine engines which may be utilized to transfer heat from one fluid flow 46 to a second independent fluid flow wherein one of the fluid flows has a high differential inlet pressure and temperature. The heat exchanger has robust construction to inhibit mixing of the fluid flows during a single burst duct event.
    Type: Grant
    Filed: August 6, 2019
    Date of Patent: April 12, 2022
    Assignee: General Electric Company
    Inventors: Thomas Kupiszewski, Christopher Charles Glynn, Steven Douglas Johnson, John Andrew Kemme, Mehdi Milani Baladi, Michael Epstein
  • Publication number: 20220010558
    Abstract: A secure handrail may include an angled mounting bracket that is sized and shaped to fit onto a door. The angled mounting bracket may have a first plate that is sized and shape to fit against an inner face of door jamb when a door is closed in the door jamb. The angle mounting bracket further have a second plate that is sized and shaped to fit against a front face of the door jamb or against a casing mounted over a door jamb, and a handrail connected to the mounting bracket.
    Type: Application
    Filed: July 8, 2021
    Publication date: January 13, 2022
    Inventor: Steven Douglas Johnson
  • Publication number: 20210310422
    Abstract: A gas turbine engine includes: a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine; a secondary flowpath connected in flow communication with the primary flowpath; and an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein: the air cycle rotor is coupled in mechanical driving relationship with the at least one engine rotor; the air cycle rotor is coupled in fluid flow communication with the secondary flowpath; and the air cycle rotor is coupled in fluid flow communication with at least one heat exchanger.
    Type: Application
    Filed: June 17, 2021
    Publication date: October 7, 2021
    Inventors: Steven Douglas Johnson, Jeffrey Rambo
  • Patent number: 11073091
    Abstract: A gas turbine engine includes: a compressor, a combustor, and a turbine arranged in sequential flow relationship along a primary flowpath, the turbine being connected in mechanical driving relationship to the compressor, so as to define at least one engine rotor that is rotatable about a centerline axis of the engine; a secondary flowpath connected in flow communication with the primary flowpath; and an air cycle machine including an air cycle rotor carrying an at least one air cycle compressor and at least one air cycle expander, wherein: the air cycle rotor is coupled in mechanical driving relationship with the at least one engine rotor; the air cycle rotor is coupled in fluid flow communication with the secondary flowpath; and the air cycle rotor is coupled in fluid flow communication with at least one heat exchanger.
    Type: Grant
    Filed: June 14, 2018
    Date of Patent: July 27, 2021
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Jeffrey Rambo
  • Publication number: 20210199051
    Abstract: An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.
    Type: Application
    Filed: December 30, 2019
    Publication date: July 1, 2021
    Inventors: Craig Alan Gonyou, Robert Proctor, Christopher Michael Thompson, Scott Alan Schimmels, Steven Douglas Johnson
  • Patent number: 11047481
    Abstract: A seal assembly of a rotary includes a radially oriented plate that axially opposes a front and rear support plates of a stator interface. The seal assembly also includes a film-riding shoe coupled with the radially oriented plate. The shoe forms a shoe fluid bearing between the shoe and a rotating component responsive to rotation of the rotating component and pressurization of fluid in the rotary machine upstream of the stator interface. One or more of the stator interface or the film-riding shoe includes one or more ports or pathways through which higher-pressure fluid upstream of the stator housing in the rotary machine flows to form an aft axial fluid bearing between the radially oriented plate and the rear support plate of the stator interface.
    Type: Grant
    Filed: March 8, 2019
    Date of Patent: June 29, 2021
    Assignee: General Electric Company
    Inventors: Rahul Anil Bidkar, Steven Douglas Johnson, Nathan Evan McCurdy Gibson
  • Publication number: 20210123358
    Abstract: An airfoil assembly and method for an engine comprising a plurality of circumferentially arranged platforms having confronting end faces each platform defining a base portion from which an airfoil extends outwardly defining a radial direction and from which a set of legs extends radially inward, a disk post coupled to at least one leg of the set of legs, a cavity formed by the platform, set of legs, and the disk post defining a static pressure zone during operation, a high pressure zone located exteriorly of the cavity; and at least one blocking spline seal.
    Type: Application
    Filed: October 29, 2019
    Publication date: April 29, 2021
    Inventors: Steven Douglas Johnson, Robert Proctor