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 WHEEL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE BLADES
    Publication number: 20200018177
    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: Application
    Filed: July 11, 2018
    Publication date: January 16, 2020
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190390558
    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: Application
    Filed: June 20, 2018
    Publication date: December 26, 2019
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190368360
    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: Application
    Filed: June 1, 2018
    Publication date: December 5, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • CERAMIC MATRIX COMPOSITE BLADE TRACK ASSEMBLY WITH TIP CLEARANCE CONTROL
    Publication number: 20190368367
    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: Application
    Filed: May 30, 2018
    Publication date: December 5, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Brazed blade track for a gas turbine engine
    Patent number: 10494935
    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: Grant
    Filed: April 8, 2016
    Date of Patent: December 3, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • BLISK BONDED CMC AIRFOIL HAVING ATTACHMENT
    Publication number: 20190345831
    Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The retention assembly is secured with the disk by forming a diffusion joint with the disk.
    Type: Application
    Filed: May 14, 2018
    Publication date: November 14, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel, Bruce E. Varney
  • Machinable CMC insert
    Patent number: 10472976
    Abstract: An assembly comprising a ceramic matrix composite component, a monolithic insert, and a polymer char and a method for producing the same. The ceramic matrix composite component may include an exterior surface, with the monolithic insert bonded to the exterior surface of the ceramic matrix composite component. The polymer char may be sandwiched between the monolithic insert and the exterior surface of the ceramic matrix composite that may bond the monolithic insert to the ceramic matrix composite component.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: November 12, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce American Technologies, Inc.
    Inventors: Ted J. Freeman, Thomas D. Nixon, Sean E. Landwehr, Aaron D. Sippel, Donald W. Reinhart
  • Machinable CMC insert
    Patent number: 10465534
    Abstract: A ceramic matrix composite component and a ceramic insert, and a method for producing the same. The ceramic matrix composite component may include an exterior surface comprising silicon fibers in a silicon carbide matrix. The insert may include a continuous porosity bonded to the exterior surface of the ceramic matrix composite component. The silicon carbide matrix of the ceramic matrix composite component may extend into the porosity of the ceramic insert to bond the ceramic insert to the ceramic matrix composite component.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: November 5, 2019
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Thomas D. Nixon, Sean E. Landwehr, Aaron D. Sippel, Donald W. Reinhart
  • TURBINE BLADE WITH ATTACHMENT-SUPPORTED PLATFORM FOR COMPOSITE MATERIAL CONSTRUCTION
    Publication number: 20190330990
    Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes a root, an airfoil, and a platform. The root is adapted to attach the turbine blade to a disk. The airfoil is shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade when the turbine blade is used in a gas turbine engine. The platform is arranged between the root and the airfoil and is shaped to block gasses from the gas path migrating toward the root when the turbine blade is used in a gas turbine engine.
    Type: Application
    Filed: June 28, 2019
    Publication date: October 31, 2019
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Ted J. Freeman, David J. Thomas
  • Machinable CMC insert
    Patent number: 10458653
    Abstract: An assembly comprising a ceramic matrix composite component, a ceramic insert, and a ply and a method for producing the same. The ceramic matrix composite component may comprise silicon carbide fibers in a silicon carbide matrix. The ceramic inset may be adjacent to the ceramic matrix composite component. The ply may at least partially cover the ceramic insert such that the ceramic insert may be sandwiched between the ply and the ceramic matrix composite component, and the ply may extend beyond the ceramic insert in at least one direction so that the ply is joined to the ceramic matrix composite. The ply may comprise at least one layer of silicon carbide fibers or carbon fibers in a silicon carbide matrix.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: October 29, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Ted J. Freeman, Thomas D. Nixon, Sean E. Landwehr, Aaron D. Sippel, Donald W. Reinhart
  • Turbine shroud with sealing features
    Patent number: 10458263
    Abstract: A segmented turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and retainers. The blade track is mounted onto the retainers, and the retainers are attached to the carrier to support the blade track radially outside of the blades.
    Type: Grant
    Filed: September 27, 2016
    Date of Patent: October 29, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas
  • TURBINE BLADE WITH ABRADABLE TIP
    Publication number: 20190323364
    Abstract: The present disclosure relates to turbine blades adapted for use in gas turbine engines. In particular, this disclosure is directed to turbine blades that include components made from ceramic matrix composite materials and that incorporate abradable materials.
    Type: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Aaron D. Sippel, Ted J. Freeman
  • TURBINE DISK WITH PLATFORMS COUPLED TO DISK
    Publication number: 20190323372
    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: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • TURBINE DISK WITH BLADE SUPPORTED PLATFORMS
    Publication number: 20190323371
    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: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Stephen Harris, Aaron D. Sippel, Ted J. Freeman, Anthony Razzell
  • CERAMIC MATRIX COMPOSITE TURBINE BLADE WITH ABRASIVE TIP
    Publication number: 20190323363
    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: Application
    Filed: April 23, 2018
    Publication date: October 24, 2019
    Inventors: Aaron D. Sippel, Andrew Glucklich, Sungbo Shim, Ted J. Freeman
  • Seal assembly for gas turbine engine components
    Patent number: 10443420
    Abstract: A gas turbine engine assembly includes adjacent components and a seal assembly. The seal assembly is configured to block gasses from passing through the interface of the adjacent components.
    Type: Grant
    Filed: January 11, 2017
    Date of Patent: October 15, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Daniel K. Vetters
  • Turbine blade with ceramic matrix composite material construction
    Patent number: 10443409
    Abstract: A turbine blade of ceramic matrix composite material construction adapted for use in a gas turbine engine is disclosed. The turbine blade includes a root, an airfoil, and a platform. The root is adapted to attach the turbine blade to a disk. The airfoil is shaped to interact with hot gasses moving through the gas path of a gas turbine engine and cause rotation of the turbine blade when the turbine blade is used in a gas turbine engine. The platform is arranged between the root and the airfoil and is shaped to block gasses from the gas path migrating toward the root when the turbine blade is used in a gas turbine engine.
    Type: Grant
    Filed: October 28, 2016
    Date of Patent: October 15, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Ted J. Freeman, David J. Thomas
  • FULL HOOP BLADE TRACK WITH KEYSTONING SEGMENTS
    Publication number: 20190301296
    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: Application
    Filed: March 27, 2018
    Publication date: October 3, 2019
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Turbine wheel assembly with ceramic matrix composite components
    Patent number: 10428661
    Abstract: A gas turbine engine includes a turbine section having static turbine vane rings and turbine wheel assemblies. The vane rings are arranged to direct combustion products toward blades included in the turbine wheel assemblies to cause the turbine wheel assemblies to rotate.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: October 1, 2019
    Assignees: Roll-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters
  • 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