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).

  • 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
  • TURBINE WHEEL ASSEMBLY WITH RETAINER RINGS FOR CERAMIC MATRIX COMPOSITE MATERIAL BLADES
    Publication number: 20200116034
    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: Application
    Filed: October 10, 2018
    Publication date: April 16, 2020
    Inventors: Ted J. Freeman, Aaron D. Sippel, James Sellhorn
  • Turbine vane assembly with ceramic matrix composite components
    Patent number: 10612399
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes an airfoil, an endwall, and a spar. The airfoil is shaped to interact with hot gases moving axially along a primary gas path of the gas turbine engine. The endwall is shaped to define a boundary of the primary gas path near a radial end of the airfoil. The spar is located in an interior region of the airfoil to carry loads that act on the airfoil during operation of the gas turbine engine.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: April 7, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • TURBINE WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200102842
    Abstract: A turbine wheel assembly adapted for use in a gas turbine engine includes turbine blades made from ceramic matric composite materials. The turbine blades are mounted to a disk and anti-rotation features block movement of the turbine blades around a circumference of the disk.
    Type: Application
    Filed: September 27, 2018
    Publication date: April 2, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH OFFLOADED PLATFORMS AND CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200095875
    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. Each of the plurality of blades includes a root received in the disk and an airfoil that extends radially away from the root. The platforms are arranged around the blades to define a boundary of a flow path of the gas turbine engine.
    Type: Application
    Filed: September 26, 2018
    Publication date: March 26, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE WHEEL ASSEMBLY WITH PLATFORM RETENTION FEATURES
    Publication number: 20200095874
    Abstract: A wheel assembly for a gas turbine engine includes a disk, a plurality of blades, and a platform system. The disk is configured to rotate about an axis during operation of the gas turbine engine. The blades are coupled with the disk for rotation therewith. The platform system includes a plurality of platforms arranged around the blades and a coverplate that blocks movement of the platforms relative to the disk.
    Type: Application
    Filed: September 26, 2018
    Publication date: March 26, 2020
    Inventors: Ted J. Freeman, Aaron D. Sippel, Anthony Razzell
  • TURBINE VANE ASSEMBLY WITH VARIABLE POSITION SUPPORT
    Publication number: 20200080434
    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: Application
    Filed: September 12, 2018
    Publication date: March 12, 2020
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel
  • 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
  • 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
  • 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
  • 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
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS MOUNTED TO CASE
    Publication number: 20200072066
    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: Application
    Filed: August 31, 2018
    Publication date: March 5, 2020
    Inventors: David J. Thomas, Aaron D. Sippel, Ted J. Freeman
  • Turbine shroud assembly with anti-rotation features
    Patent number: 10577978
    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 3, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters, David J. Thomas, Alexandra R. Baucco, Joseph P. Lamusga
  • Turbine disk with blade supported platforms
    Patent number: 10577961
    Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. The blades each fit within slots formed in the rotor disk to couple the blades to the rotor disk. Platform segments are arranged about each of the blades.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: March 3, 2020
    Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce plc, Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Stephen Harris, Aaron D. Sippel, Ted J. Freeman, Anthony Razzell
  • CERAMIC MATRIX COMPOSITE TURBINE BLADE WITH LIGHTENING HOLE
    Publication number: 20200063571
    Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes an airfoil and a tip to discourage air leakage over the tip of the turbine blade. The turbine blade is designed considering weight and strength to include a lightening hole.
    Type: Application
    Filed: August 27, 2018
    Publication date: February 27, 2020
    Inventors: Ted J. Freeman, Aaron D. Sippel, Robert J. Shinavski
  • BRAZED BLADE TRACK FOR A GAS TURBINE ENGINE
    Publication number: 20200056493
    Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
    Type: Application
    Filed: October 23, 2019
    Publication date: February 20, 2020
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • Keystoned blade track
    Patent number: 10563535
    Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
    Type: Grant
    Filed: April 4, 2016
    Date of Patent: February 18, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce plc
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Peter Broadhead, Bruce E. Varney, Jeffrey A. Walston, Steven Hillier
  • Full hoop blade track with flanged segments
    Patent number: 10550709
    Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.
    Type: Grant
    Filed: April 1, 2016
    Date of Patent: February 4, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc, Rolls-Royce High Temperature Composites Inc.
    Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Steven M. Hillier, Peter Broadhead, Joseph Doyle, Michael Jacquinto, Wesley Thibault, Jun Shi, Roderick Townes
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20200025025
    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: Application
    Filed: July 17, 2018
    Publication date: January 23, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Adam L. Chamberlain