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).

  • COMBUSTOR FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE SEALING ELEMENT
    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
  • COMBUSTOR LINER FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    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
  • TURBINE SHROUD SEGMENT HAVING A SEAL SEGMENT PERIMETER SEAL WITH SEPARATED BUFFER CAVITIES
    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
  • TURBINE SHROUD WITH FRICTION MOUNTED CERAMIC MATRIX COMPOSITE BLADE TRACK
    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
  • COMBUSTOR FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE HEAT SHIELD AND SEAL RETAINER
    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
  • COMBUSTOR FOR A GAS TURBINE ENGINE WITH CERAMIC MATRIX COMPOSITE HEAT SHIELD
    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
  • Ceramic matrix full hoop blade track
    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
  • Turbine shroud assembly with locating pads
    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
  • Turbine vane assembly with variable position support
    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
  • Segmented turbine shroud with sealing features
    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
  • Turbine vane assembly with ceramic matrix composite components mounted to case
    Patent number: 10927689
    Abstract: A vane assembly for a gas turbine engine is provided having an outer casing and an inner casing radially spaced apart from the outer casing. An airfoil extends radially between the outer casing and the inner casing. The airfoil includes a spar having an outer endwall positioned adjacent the outer casing and an inner endwall positioned adjacent the inner casing. A pressure side and a suction side extend between the inner endwall and the outer endwall. A ceramic matrix composite cover has a pressure side extending along the pressure side of the spar and a suction side extending along the suction side of the spar.
    Type: Grant
    Filed: August 31, 2018
    Date of Patent: February 23, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: David J. Thomas, Aaron D. Sippel, Ted J. Freeman
  • TURBINE SHROUD WITH CERAMIC MATRIX COMPOSITE SEAL SEGMENTS MOUNTED TO METALLIC CARRIERS
    Publication number: 20210025284
    Abstract: A turbine shroud assembly of a gas turbine engine includes a carrier, a blade track segment and a mounting assembly. The carrier is made from metallic materials. The blade track segment is made from ceramic matrix composite materials. The mounting assembly is configured to couple the blade track segment to the carrier.
    Type: Application
    Filed: July 24, 2019
    Publication date: January 28, 2021
    Inventors: Aaron D. Sippel, Daniel K. Vetters
  • Turbine disk with platforms coupled to disk
    Patent number: 10890081
    Abstract: A disk assembly for use in a turbine of a gas turbine engine. The disk assembly includes a disk and a plurality of platforms coupled with the disk. The disk includes a plurality of radially extending disk lugs that define slots for receiving airfoils. The platforms are coupled to the disk lugs between neighboring blades to block radially inward movement of hot gasses toward the disk.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: January 12, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • TURBINE WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200340364
    Abstract: A turbine blade comprising ceramic matrix composite materials and designed for incorporation into a turbine wheel assembly is disclosed in this paper. Further disclosed are features for managing stiffness and dampening in order to influence vibratory response of such a turbine blade when used as part of a turbine wheel assembly in a gas turbine engine.
    Type: Application
    Filed: April 26, 2019
    Publication date: October 29, 2020
    Inventors: Shaling Starr, Aaron D. Sippel, Ted J. Freeman
  • Turbine vane assembly with ceramic matrix composite components
    Patent number: 10808560
    Abstract: A turbine vane assembly includes an airfoil, a support strut, and an inner seal panel. The airfoil is formed to include an interior region of the airfoil. The support strut is located in the interior region of the airfoil and configured to carry loads that act on the airfoil. The inner seal panel extends at least partway about the axis to resist fluid communication between a region upstream of the inner seal panel and a region downstream of the inner seal panel.
    Type: Grant
    Filed: June 20, 2018
    Date of Patent: October 20, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • Turbine shroud assembly with tandem seals
    Patent number: 10746037
    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: August 18, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • Turbine shroud with movable attachment features
    Patent number: 10746054
    Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.
    Type: Grant
    Filed: January 16, 2019
    Date of Patent: August 18, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature High Composites Inc., Rolls-Royce North American Technologies, Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Robert J. Shinavski, Zacheriah A. Cole
  • Turbine engine assembly with tubular locating inserts
    Patent number: 10738642
    Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The supported component includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend into the carrier to couple the supported component with the carrier.
    Type: Grant
    Filed: June 5, 2018
    Date of Patent: August 11, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Jun Shi, Jeffrey A. Walston, Aaron D. Sippel
  • Full hoop blade track with keystoning segments
    Patent number: 10697315
    Abstract: A blade track used in gas turbine engines to define an outer boundary of the primary gas path through a turbine section of a gas turbine engine is disclosed. The blade track includes segments comprising ceramic matrix composite materials that are assembled such that the blade track segments keystone against one another to provide a self-supporting full hoop assembly. Circumferentially-extending splines may be used to couple adjacent segments to one. Also disclosed are other heat shielding assemblies used in gas turbine engines that share features with the illustratively disclosed blade track.
    Type: Grant
    Filed: March 27, 2018
    Date of Patent: June 30, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Turbine wheel assembly with ceramic matrix composite blades
    Patent number: 10655479
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a blade-attachment system, and a plurality of blades. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blade-attachment system is configured to couple the plurality of blades with the disk for rotation therewith.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: May 19, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman