Patents by Inventor Loic Fabries

Loic Fabries 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).

  • Pinned platform for blade with circumferential attachment
    Patent number: 11156111
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system that includes a plurality of platforms and pins. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the wheel to define a flow path of the gas turbine engine and the pins extend into the platforms and the disk to couple the platforms with the disk.
    Type: Grant
    Filed: August 31, 2018
    Date of Patent: October 26, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • Turbine blade assembly with ceramic matrix composite components
    Patent number: 10641111
    Abstract: A wheel assembly for a gas turbine engine includes a disk and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root.
    Type: Grant
    Filed: August 31, 2018
    Date of Patent: May 5, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • Platform with axial attachment for blade with circumferential attachment
    Patent number: 10633986
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending attachment feature that is received in the disk. The platforms each have an axially extending attachment feature that is received in the disk.
    Type: Grant
    Filed: August 31, 2018
    Date of Patent: April 28, 2020
    Assignees: Rolls-Roye Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • PINNED PLATFORM FOR BLADE WITH CIRCUMFERENTIAL ATTACHMENT
    Publication number: 20200072063
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system that includes a plurality of platforms and pins. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the wheel to define a flow path of the gas turbine engine and the pins extend into the platforms and the disk to couple the platforms with the disk.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • TURBINE BLADE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20200072065
    Abstract: A wheel assembly for a gas turbine engine includes a disk and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending root received in the disk and an airfoil that extends radially away from the root.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries
  • PLATFORM WITH AXIAL ATTACHMENT FOR BLADE WITH CIRCUMFERENTIAL ATTACHMENT
    Publication number: 20200072064
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a plurality of platforms. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades each include a circumferentially extending attachment feature that is received in the disk. The platforms each have an axially extending attachment feature that is received in the disk.
    Type: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, Loic Fabries