Patents by Inventor Brian J. Shoemaker

Brian J. Shoemaker 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).

  • Turbine shroud ring for a gas turbine engine having a tip clearance probe
    Patent number: 11225880
    Abstract: A gas turbine engine assembly includes adjacent components and a probe assembly. The probe assembly is configured to measure a distance between the probe assembly and blades located radially inward of the adjacent components.
    Type: Grant
    Filed: February 2, 2018
    Date of Patent: January 18, 2022
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Brian J. Shoemaker, Ted J. Freeman
  • Turbine shroud ring for a gas turbine engine with radial retention features
    Patent number: 10655491
    Abstract: A gas turbine engine assembly includes a turbine shroud having a carrier segment and adjacent blade track segments. The carrier segment is arranged around a central axis of the gas turbine engine and the blade track segments are supported by the carrier segment. The turbine shroud segment further includes a retainer that is configured to locate the blade track segments radially relative to the central axis of the gas turbine engine.
    Type: Grant
    Filed: February 22, 2017
    Date of Patent: May 19, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Brian J. Shoemaker, Ted J. Freeman
  • Split line flow path seals
    Patent number: 10584605
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
    Type: Grant
    Filed: August 9, 2017
    Date of Patent: March 10, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc., Rolls-Royce plc
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker, Steven Hillier
  • Seal segment retention ring with chordal seal feature
    Patent number: 10519807
    Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.
    Type: Grant
    Filed: April 19, 2017
    Date of Patent: December 31, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Brian J. Shoemaker, Joseph P. Lamusga, Ted J. Freeman
  • Gas turbine engine features for tip clearance inspection
    Patent number: 10428674
    Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.
    Type: Grant
    Filed: January 31, 2017
    Date of Patent: October 1, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Brian J. Shoemaker, Ted J. Freeman
  • SEAL COATING FOR CERAMIC MATRIX COMPOSITE
    Publication number: 20180311934
    Abstract: A system may include a first component that includes a substrate including a ceramic or a CMC, a bond coat on the substrate, and a seal coating including at least one rare earth silicate on the bond coat. The system also includes a second component that defines a surface. The surface of the second component contacts the seal coating, and the first component and the second component are substantially stationary relative to each other.
    Type: Application
    Filed: April 28, 2017
    Publication date: November 1, 2018
    Inventors: Brian J. Shoemaker, Aaron Sippel, Ted Freeman
  • SEAL SEGMENT RETENTION RING WITH CHORDAL SEAL FEATURE
    Publication number: 20180306063
    Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.
    Type: Application
    Filed: April 19, 2017
    Publication date: October 25, 2018
    Inventors: Brian J. Shoemaker, Joseph P. Lamusga, Ted J. Freeman
  • TURBINE SHROUD RING FOR A GAS TURBINE ENGINE WITH RADIAL RETENTION FEATURES
    Publication number: 20180238188
    Abstract: A gas turbine engine assembly includes a turbine shroud having a carrier segment and adjacent blade track segments. The carrier segment is arranged around a central axis of the turbine shroud and the blade track segments are supported by the carrier segment.
    Type: Application
    Filed: February 22, 2017
    Publication date: August 23, 2018
    Inventors: Brian J. Shoemaker, Ted J. Freeman
  • GAS TURBINE ENGINE FEATURES FOR TIP CLEARANCE INSPECTION
    Publication number: 20180216481
    Abstract: Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assembly includes a turbine wheel assembly and a turbine shroud. The turbine wheel assembly includes a disk and a plurality of blades that extend outwardly from the disk in a radial direction away from an axis. The turbine shroud extends around the blades of the turbine wheel assembly to block gasses from passing over the blades during operation of the turbine assembly. The turbine shroud includes a plurality of blade track segments arranged circumferentially adjacent to one another about the axis to form a ring. Each blade track segment has a runner that forms a primary track surface facing the axis and spaced from the axis in the radial direction.
    Type: Application
    Filed: January 31, 2017
    Publication date: August 2, 2018
    Inventors: Aaron D. Sippel, Brian J. Shoemaker, Ted J. Freeman
  • SPLIT LINE FLOW PATH SEALS
    Publication number: 20170370240
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
    Type: Application
    Filed: August 9, 2017
    Publication date: December 28, 2017
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker, Steven Hillier
  • Split line flow path seals
    Patent number: 9759079
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
    Type: Grant
    Filed: May 28, 2015
    Date of Patent: September 12, 2017
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc., Rolls-Royce plc
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker, Steven Hillier
  • SPLIT LINE FLOW PATH SEALS
    Publication number: 20160348521
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
    Type: Application
    Filed: May 28, 2015
    Publication date: December 1, 2016
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker