Patents by Inventor Aaron D. Sippel

Aaron D. Sippel 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: 11028722
    Abstract: The present disclosure is directed to a blade track assembly used in a gas turbine engine. The blade track assembly includes blade track segments made from ceramic matrix composite materials and a tip clearance control system for adjusting the inner diameter of the blade track assembly during use in an engine.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: June 8, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Publication number: 20210164365
    Abstract: A turbine shroud assembly includes a carrier, a blade track segment, and an attachment pin. The carrier is arranged to extend circumferentially at least partway around an axis. The blade track segment includes a runner that faces the axis to define a portion of a primary gas path of the gas turbine engine and an attachment flange that extends radially away from the runner. The attachment pin is configured to mount the blade track segment to the carrier.
    Type: Application
    Filed: December 3, 2019
    Publication date: June 3, 2021
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Patent number: 11021974
    Abstract: A wheel assembly for a gas turbine engine includes a disk, an annular coverplate, and an anti-rotation feature. The disk is adapted to receive blades and rotate about an axis during use of the gas turbine engine. The annular coverplate is coupled with the disk and adapted to block axial movement of the blades. The anti-rotation feature is coupled with the disk and the annular coverplate to resist rotation of the annular coverplate relative to the disk.
    Type: Grant
    Filed: October 10, 2018
    Date of Patent: June 1, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, James Sellhorn
  • Publication number: 20210148250
    Abstract: A turbine module includes a turbine rotor assembly, a turbine case, and a turbine shroud assembly. The turbine rotor assembly is mounted to rotate about a central reference axis. The turbine case is spaced radially outward from the turbine rotor assembly circumferentially around the central reference axis. The turbine shroud assembly includes a plurality of turbine shroud segments mounted to the turbine case. Each turbine shroud segment includes a blade track segment that faces the turbine rotor assembly and a carrier mounted to the turbine case.
    Type: Application
    Filed: November 15, 2019
    Publication date: May 20, 2021
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Publication number: 20210148248
    Abstract: A turbine assembly adapted for use with a gas turbine engine includes an outer case, a blade track segment, and a carrier. The outer case extends circumferentially at least partway around an axis of the engine. The blade track segment is configured to define a portion of a gas path of the turbine assembly. The carrier is coupled with the outer case and the blade track segment to support the blade track segment in position radially relative to the axis.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Publication number: 20210148251
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a blade track segment and a carrier. The blade track segment includes an arcuate shroud wall that extends circumferentially partway around an axis and a mount post that extends radially outward away from the shroud wall. The carrier is coupled with the mount post of the blade track segment to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Publication number: 20210148252
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track segment coupled to a carrier segment, and a sheet-metal seal that seals therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Publication number: 20210148244
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.
    Type: Application
    Filed: November 19, 2019
    Publication date: May 20, 2021
    Inventors: Ted J. Freeman, David J. Thomas, Jeffrey A. Walston, Aaron D. Sippel
  • Patent number: 11008888
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a vane support and a vane heat shield comprising ceramic matrix composite materials to insulate the metallic materials of the vane support. The turbine vane assembly further includes an aero-load transfer rib located outside of a primary gas path and configured to carry loads applied to the vane heat shield to the vane support.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: May 18, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Adam L. Chamberlain
  • Patent number: 10995623
    Abstract: The present disclosure relates generally to blades used in gas turbine engines. More specifically designs in accordance with the present disclosure include turbine blades comprising ceramic matrix composite materials with abrasive tips coupled thereto.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: May 4, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc., Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Andrew Glucklich, Sungbo Shim, Ted J. Freeman
  • Publication number: 20210108799
    Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Publication number: 20210108531
    Abstract: A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.
    Type: Application
    Filed: October 9, 2019
    Publication date: April 15, 2021
    Inventors: Daniel K. Vetters, Aaron D. Sippel, Jeffrey M. Crutchfield, Jeffrey A. Walston
  • Publication number: 20210108532
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a seal segment and an attachment unit. The seal segment includes an arcuate shroud wall that extends circumferentially partway around an axis and a mount post that extends radially outward away from the shroud wall. The attachment unit includes a first carrier and a second carrier that cooperate to define a channel that receives at least a portion of the mount post.
    Type: Application
    Filed: October 12, 2020
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Shaling Starr, Paulo Bazan, Adrian Harding, Jeffrey A. Walston
  • Publication number: 20210108798
    Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.
    Type: Application
    Filed: October 11, 2019
    Publication date: April 15, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Jack D. Petty, Gregory W. Zeaton
  • Publication number: 20210102702
    Abstract: A combustor adapted for use in a gas turbine engine a combustor shell, a heat shield, and a heat shield retainer. The combustor shell is made from metallic materials and is formed to define an internal cavity. The heat shield is formed from ceramic matrix composite materials and is coupled to the dome panel. The heat shield retainer is configured to retain the heat shield to the combustor shell.
    Type: Application
    Filed: October 8, 2019
    Publication date: April 8, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Publication number: 20210102701
    Abstract: A combustor for a gas turbine engine includes a combustor shell, a heat shield and a burner seal. The combustor shell includes metallic materials and is formed to define an interior combustion space. The heat shield includes ceramic matrix composite materials and is configured to shield a portion of the combustor shell from the interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield.
    Type: Application
    Filed: October 8, 2019
    Publication date: April 8, 2021
    Inventors: Ted J. Freeman, Aaron D. Sippel, Paulo Bazan
  • Patent number: 10954809
    Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.
    Type: Grant
    Filed: May 25, 2018
    Date of Patent: March 23, 2021
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Christopher Barrett
  • Patent number: 10934868
    Abstract: A vane assembly for use in a gas turbine engine includes an airfoil, a strut, and a support member. The airfoil is configured to interact with gases flowing through a primary gas path of the engine. The strut is located in an interior region of the airfoil and configured to carry loads that act on the airfoil by the gases. The support member is configured to compensate for relative thermal expansion between the components of the vane assembly caused by heat generated during use of the engine to locate the airfoil radially in the primary gas path.
    Type: Grant
    Filed: September 12, 2018
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel
  • Patent number: 10934891
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.
    Type: Grant
    Filed: November 3, 2017
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco
  • Patent number: 10934871
    Abstract: A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.
    Type: Grant
    Filed: February 22, 2016
    Date of Patent: March 2, 2021
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Peter Broadhead, Aaron D. Sippel, David J. Thomas, Joseph P. Lamusga