Patents by Inventor Lawrence A Binek

Lawrence A Binek 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).

  • ADDITIVELY CONTROLLED SURFACE ROUGHNESS FOR DESIGNED PERFORMANCE
    Publication number: 20220154601
    Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.
    Type: Application
    Filed: February 7, 2022
    Publication date: May 19, 2022
    Applicant: Raytheon Technologies Corporation
    Inventors: Vijay Narayan Jagdale, Jesse R. Boyer, Om P. Sharma, Evan J. Butcher, Lawrence Binek, Bryan G. Dods
  • Linked locking module
    Patent number: 11332957
    Abstract: A locking module (40) for selectively coupling a first component and a second component of a lockable device (20) includes a locking member (42) rotatable between an unlocked position and a locked position and an engagement member (50) associated with said locking member (42). Translation of said engagement member (50) drives movement of said locking member (42) between said locked position and said unlocked position to selectively decouple said first component from the second component.
    Type: Grant
    Filed: February 28, 2018
    Date of Patent: May 17, 2022
    Assignee: CARRIER CORPORATION
    Inventors: Lawrence Binek, Joseph Zacchio
  • SPLIT CASE STRUCTURE FOR A GAS TURBINE ENGINE
    Publication number: 20220136409
    Abstract: An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.
    Type: Application
    Filed: October 30, 2020
    Publication date: May 5, 2022
    Inventors: Lawrence A. Binek, Randolph T. Lyda
  • Powder evacuation systems
    Patent number: 11318676
    Abstract: An additive manufacturing system includes a build chamber housing a recoater and a sintering laser. A build plate is moveable within the build chamber to accommodate growth of a part formed by the recoater and the sintering laser. At least one powder evacuation cavity at least partially surrounds a build volume of the build chamber. The build volume of the build chamber is defined between the build plate and the recoater and is configured to hold a sintered part and unsintered powder during an additive manufacturing build in the build chamber.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: May 3, 2022
    Assignee: Hamilton Sundstrand Corporation
    Inventors: David W. Morganson, Lawrence Binek
  • Support structure for combustor components and method of using same
    Patent number: 11320145
    Abstract: A method for forming a combustor of a gas turbine engine includes additively manufacturing a combustor wall of the combustor. The combustor wall includes a component, projecting from a surface of the combustor wall, and a support structure in communication with the component and the surface of the combustor wall. The support structure is a lattice structure.
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: May 3, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence A. Binek, Sean R. Jackson, Evan J. Butcher
  • SPALL PLATE FOR CONSUMABLE COMBUSTOR SUPPORT STRUCTURES
    Publication number: 20220107088
    Abstract: A combustor may comprise an outer wall defining, at least, a portion of a combustion chamber. A dilution chute may extend from an interior surface of the outer wall. A support structure may extend between the dilution chute and the interior surface of the outer wall. A spall plate may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet of the combustion chamber.
    Type: Application
    Filed: December 14, 2021
    Publication date: April 7, 2022
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Lawrence A. Binek, Sean R. Jackson, Evan J. Butcher
  • TURBINE ENGINE COMPONENT WITH INTEGRATED WAVEGUIDE
    Publication number: 20220099001
    Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine case, a first transceiver and a second transceiver. The turbine engine case includes a case wall and a waveguide. The waveguide is formed integral with the case wall. The waveguide includes a waveguide channel. The second transceiver is configured to be in signal communication with the first transceiver through the waveguide channel.
    Type: Application
    Filed: September 28, 2020
    Publication date: March 31, 2022
    Inventors: Lawrence A. Binek, Sean R. Jackson
  • FUEL INJECTOR ASSEMBLY FOR A TURBINE ENGINE
    Publication number: 20220082250
    Abstract: An apparatus is provided for a turbine engine. This apparatus includes a fuel conduit and a fuel nozzle. The fuel conduit includes a supply passage. The fuel nozzle includes a nozzle passage, an end wall and a nozzle orifice. The nozzle passage has a longitudinal centerline and extends longitudinally through the fuel nozzle along the longitudinal centerline from the end wall to the nozzle orifice. The nozzle passage is configured with a convergent portion and a throat portion. The nozzle passage converges radially inward towards the longitudinal centerline as the convergent portion extends longitudinally along the longitudinal centerline away from the end wall and towards the throat portion. The supply passage is fluidly coupled to the nozzle passage by a fuel aperture in the end wall. A centerline of the fuel aperture is angularly and laterally offset from the longitudinal centerline.
    Type: Application
    Filed: September 11, 2020
    Publication date: March 17, 2022
    Inventors: Lawrence A. Binek, Timothy S. Snyder
  • FUEL INJECTOR ASSEMBLY FOR A TURBINE ENGINE
    Publication number: 20220082257
    Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a fuel nozzle. The fuel nozzle includes an airflow inlet, a nozzle orifice, a fuel passage and a swirler passage. The fuel passage is fluidly coupled with the swirler passage through a first fuel aperture in a wall between the fuel passage and the swirler passage. The swirler passage extends along a helical trajectory away from the airflow inlet and towards the nozzle orifice.
    Type: Application
    Filed: September 11, 2020
    Publication date: March 17, 2022
    Inventors: Lawrence A. Binek, Timothy S. Snyder
  • Bullet, Weapon Provided with Such Bullets, Kit for Assembling the Same, and Corresponding Methods of Manufacturing, Operating and Use Associated Thereto
    Publication number: 20220074720
    Abstract: A bullet including a drag-reducing assembly provided about its main body, and configured for being triggered upon a blast from a cartridge, in order to reduce a resulting base drag of the bullet during flight trajectory. The drag-reducing assembly includes at least one cavity being configured for receiving and containing a portion of gun gas from the cartridge and corresponding blast, and at least one peripheral orifice for releasing gun gas from the at least one cavity during the flight trajectory of the bullet, in order to fill a partial vacuum behind the bullet during flight trajectory, and thus reduce the resulting base drag, for an improved overall ballistic performance of the bullet.
    Type: Application
    Filed: November 1, 2021
    Publication date: March 10, 2022
    Inventors: Anthony A. Binek, Gabriel Idan Romagnolo, Lawrence A. Binek
  • Thermal insulation features for gas turbine engines
    Patent number: 11268404
    Abstract: A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.
    Type: Grant
    Filed: May 22, 2020
    Date of Patent: March 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: David W. Morganson, Lawrence A. Binek
  • Spall plate for consumable combustor support structures
    Patent number: 11262077
    Abstract: A combustor may comprise an outer wall defining, at least, a portion of a combustion chamber. A dilution chute may extend from an interior surface of the outer wall. A support structure may extend between the dilution chute and the interior surface of the outer wall. A spall plate may extend from the interior surface of the outer wall. The spall plate may be located between the support structure and an outlet of the combustion chamber.
    Type: Grant
    Filed: September 20, 2019
    Date of Patent: March 1, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence A. Binek, Sean R. Jackson, Evan J. Butcher
  • Gas turbine engine with integral combustion liner and turbine nozzle
    Patent number: 11248789
    Abstract: A core engine article includes a combustor liner defining a combustion chamber therein and a turbine nozzle. The combustor liner includes a plurality of injector ports, and the plurality of injector ports have a shape that tapers to a corner on a forward side of the injector ports. The turbine nozzle includes a plurality of airfoils. The combustor liner and turbine nozzle are integral with one another. A method of making a core engine article is also disclosed.
    Type: Grant
    Filed: December 7, 2018
    Date of Patent: February 15, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence Binek, Jesse R. Boyer, Dmytro Mykolayovych Voytovych
  • Additively controlled surface roughness for designed performance
    Patent number: 11242769
    Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.
    Type: Grant
    Filed: December 17, 2018
    Date of Patent: February 8, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Vijay Narayan Jagdale, Jesse R. Boyer, Om P. Sharma, Evan Butcher, Lawrence Binek, Bryan G. Dods
  • KINETIC DISASSEMBLY OF SUPPORT STRUCTURE SYSTEM FOR ADDITIVELY MANUFACTURED ROTATING COMPONENTS
    Publication number: 20220032554
    Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.
    Type: Application
    Filed: October 18, 2021
    Publication date: February 3, 2022
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Lawrence Binek, Matthew B. Kennedy, Evan Butcher, Jesse R. Boyer, Vijay Narayan Jagdale, Dmytro Mykolayovych Voytovych
  • ARTICLE AND METHOD FOR MANUFACTURING AN EXPANDED COMBUSTOR LINER
    Publication number: 20220018541
    Abstract: A method of manufacturing a nested combustor liner includes manufacturing a nested combustor liner into a green state including a plurality of annular interior walls radially adjacent to one another and circumferentially surrounding an exhaust duct aperture and a plurality of annular exterior walls radially adjacent to one another and radially spaced apart from and circumferentially surrounding the plurality of annular interior walls and an ignitor wall attached to a first annular interior wall at a first interior end, extending radially toward and attached to a first annular exterior wall at a first exterior end. The method includes assembling the plurality of annular interior walls and the plurality of annular exterior walls, forming an assembled combustor liner. The method includes densifying the assembled combustor liner.
    Type: Application
    Filed: July 16, 2020
    Publication date: January 20, 2022
    Inventors: Lawrence A. Binek, Jesse R. Boyer
  • MONOLITHIC COMBUSTOR FOR ATTRITIABLE ENGINE APPLICATIONS
    Publication number: 20210396151
    Abstract: A monolithic combustor apparatus comprises an outer casing comprising a forward flange, a fuel manifold disposed on the outer casing and defining an annular chamber extending perimetrically around the outer casing, a combustor liner disposed within the outer casing, the combustor liner defining an annular combustion chamber, a first annular plenum disposed between the outer casing and the combustor liner, an inner liner disposed radially from the combustor liner, a first inner flange extending forward from the combustor liner, and a second inner flange extending radially inward from the first inner flange.
    Type: Application
    Filed: September 2, 2021
    Publication date: December 23, 2021
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Lawrence Binek, Jesse R. Boyer, Evan Butcher, Dmytro Mykolayovych Voytovych
  • Additively manufactured thermally insulating structure
    Patent number: 11199136
    Abstract: An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: December 14, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Evan Butcher, Jesse R. Boyer, Om P. Sharma, Lawrence Binek, Bryan G. Dods, Vijay Narayan Jagdale
  • THERMAL INSULATION FEATURES FOR GAS TURBINE ENGINES
    Publication number: 20210363897
    Abstract: A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.
    Type: Application
    Filed: May 22, 2020
    Publication date: November 25, 2021
    Inventors: David W. Morganson, Lawrence A. Binek
  • Kinetic disassembly of support structure system for additively manufactured rotating components
    Patent number: 11179895
    Abstract: A rotary component may comprise a first structure configured to rotate about an axis and a second structure configured to rotate about the axis. A support structure may be coupled to the first structure at a first attachment location and to the second structure at a second attachment location. The support structure may be configured to separate from the first structure and the second structure in response to a centrifugal force generated by the first structure and the second structure rotating about the axis.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: November 23, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Lawrence Binek, Matthew B. Kennedy, Evan Butcher, Jesse R. Boyer, Vijay Narayan Jagdale, Dmytro Mykolayovych Voytovych