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).

  • Publication number: 20250179935
    Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a blade track segment arranged circumferentially at least partway around an axis of the gas turbine engine, a carrier segment arranged circumferentially at least partway around the axis, and a mount assembly configured to couple the blade track segment to the carrier segment. The turbine vane is located axially aft of the turbine shroud assembly and helps retain the mount assembly in place.
    Type: Application
    Filed: December 4, 2023
    Publication date: June 5, 2025
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Clark Snyder
  • Publication number: 20250179928
    Abstract: An assembly adapted for use in a gas turbine engine includes a blade track segment, a carrier segment, and a retainer. The blade track segment defines a portion of a gas path of the gas turbine engine. The carrier segment supports the blade track segment to locate the blade track segment radially outward of the axis. The retainer couples the blade track segment to the carrier segment. The carrier segment may include a plurality of impingement passageways to conduct cooling air to the blade track segment.
    Type: Application
    Filed: December 4, 2023
    Publication date: June 5, 2025
    Inventors: Ted J. Freeman, Aaron D. Sippel, Clark Snyder
  • Publication number: 20250179937
    Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.
    Type: Application
    Filed: December 9, 2024
    Publication date: June 5, 2025
    Inventors: David J. Thomas, Christopher Downie, Aaron D. Sippel, Ted J. Freeman, Clark Snyder
  • Patent number: 12286906
    Abstract: A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.
    Type: Grant
    Filed: December 4, 2023
    Date of Patent: April 29, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Clark Snyder, David J. Thomas, Ted J. Freeman, Aaron D. Sippel
  • Patent number: 12286885
    Abstract: A turbine assembly adapted for use with a gas turbine engine includes a turbine shroud assembly and a turbine vane. The turbine shroud assembly includes a carrier segment arranged circumferentially at least partway around an axis and a blade track segment supported by the carrier segment to locate the blade track segment radially outward of the axis. The turbine vane is located axially forward of the turbine shroud assembly and cooperates with the turbine shroud assembly to form a tortuous flow path therebetween.
    Type: Grant
    Filed: December 4, 2023
    Date of Patent: April 29, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, David J. Thomas, Ted J. Freeman, Clark Snyder, Jeffrey A. Stone
  • Patent number: 12258880
    Abstract: A turbine shroud assembly comprising a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall that is formed to include a first recess that extends circumferentially into the first shroud wall. The second shroud segment includes a second carrier segment and a second blade track having a second shroud wall that is formed to include a second recess that extends circumferentially into the second shroud wall. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
    Type: Grant
    Filed: May 30, 2024
    Date of Patent: March 25, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Clark J. Snyder
  • Patent number: 12241376
    Abstract: A turbine assembly includes a turbine case, a turbine shroud assembly including a carrier segment, and a locating plate. The locating plate is coupled with the turbine case axially forward of the carrier segment to block axially forward movement of the carrier segment and prevent separation of the carrier segment from the turbine case. The locating plate includes a main wall, a raised portion extending upwardly a first radial distance, and two circumferentially spaced apart extensions extending upwardly a second radial distance. The second radial distance is greater than the first radial distance such that, in a first arrangement, only the extensions contact the turbine case and such that, in a second arrangement, the raised portion is pulled toward the turbine case via a fastener so as to contact the turbine case in addition to the extensions.
    Type: Grant
    Filed: December 4, 2023
    Date of Patent: March 4, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Clark Snyder, David J. Thomas, Ted J. Freeman, Aaron D. Sippel
  • Patent number: 12228044
    Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a plurality of seals. The first shroud segment includes a first carrier segment and a first blade track segment having a first shroud wall. The second shroud segment includes a second carrier segment and a second blade track. The plurality of seals extend circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
    Type: Grant
    Filed: June 26, 2024
    Date of Patent: February 18, 2025
    Assignees: Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Clark J. Snyder, Steven Hillier
  • Patent number: 12215593
    Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a seal assembly. The first shroud segment includes a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The seal assembly is configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment.
    Type: Grant
    Filed: May 30, 2024
    Date of Patent: February 4, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: David J. Thomas, Aaron D. Sippel, Ted J. Freeman, Clark J. Snyder
  • Patent number: 12203376
    Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a carrier, a seal segment, and a mount assembly. The carrier is configured to be coupled to a turbine case. The seal segment is shaped to define a gas path boundary of the shroud assembly. The mounting assembly is configured to couple the seal segment to the carrier.
    Type: Grant
    Filed: June 16, 2023
    Date of Patent: January 21, 2025
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • Patent number: 12188365
    Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.
    Type: Grant
    Filed: December 4, 2023
    Date of Patent: January 7, 2025
    Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.
    Inventors: David J. Thomas, Christopher Downie, Aaron D. Sippel, Ted J. Freeman, Clark Snyder
  • Patent number: 12158072
    Abstract: A turbine shroud assembly includes a first shroud segment, a second shroud segment, and a damping strip seal. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment about the central axis. The damping strip seal extends circumferentially into the first shroud segment and the second shroud segment to block gases from passing between the first shroud segment and the second shroud segment.
    Type: Grant
    Filed: December 4, 2023
    Date of Patent: December 3, 2024
    Assignee: Rolls-Royce Corporation
    Inventors: Aaron D. Sippel, David J. Thomas, Ted J. Freeman, Clark Snyder, Grant Cook, Jeffrey A. Stone
  • Patent number: 12152499
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a first shroud segment, a second shroud segment, and a damping strip seal assembly. The first shroud segment has a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment. The second shroud segment is arranged circumferentially adjacent the first shroud segment. The damping strip seal assembly includes an axial seal member, a forward seal, and an aft seal member.
    Type: Grant
    Filed: December 4, 2023
    Date of Patent: November 26, 2024
    Assignee: Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Clark Snyder
  • Patent number: 12146417
    Abstract: Turbine shroud structures and a method of assembling a turbine shroud into a turbine are disclosed. The method includes arranging turbine shroud segments into a full ring and inserting the full ring into a turbine case as a single unit.
    Type: Grant
    Filed: February 23, 2023
    Date of Patent: November 19, 2024
    Assignee: Rolls-Royce Corporation
    Inventor: Aaron D. Sippel
  • Publication number: 20240287915
    Abstract: Turbine shroud structures and a method of assembling a turbine shroud into a turbine are disclosed. The method includes arranging turbine shroud segments into a full ring and inserting the full ring into a turbine case as a single unit.
    Type: Application
    Filed: February 23, 2023
    Publication date: August 29, 2024
    Inventor: Aaron D. Sippel
  • Patent number: 12031443
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track assembly and a carrier assembly. The blade track assembly includes a blade track segment made of ceramic matrix composite materials and arranged to define a portion of a path of the turbine shroud assembly. The carrier assembly includes a carrier segment made of metallic materials that supports the blade track segment to locate the blade track segment radially outward of the axis.
    Type: Grant
    Filed: November 29, 2022
    Date of Patent: July 9, 2024
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Publication number: 20240175371
    Abstract: A turbine shroud assembly for use with a gas turbine engine includes a blade track assembly and a carrier assembly. The blade track assembly includes a blade track segment made of ceramic matrix composite materials and arranged to define a portion of a path of the turbine shroud assembly. The carrier assembly includes a carrier segment made of metallic materials that supports the blade track segment to locate the blade track segment radially outward of the axis.
    Type: Application
    Filed: November 29, 2022
    Publication date: May 30, 2024
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Patent number: 11885225
    Abstract: A turbine shroud assembly includes a carrier segment, a blade track segment, and a retainer. The carrier segment is formed to include an attachment-receiving space. The blade track segment includes a shroud wall and attachment flanges that extends radially outward from the shroud wall into the attachment-receiving space of the carrier segment. The retainer couples the blade track segment to the carrier segment.
    Type: Grant
    Filed: January 25, 2023
    Date of Patent: January 30, 2024
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel, David J. Thomas
  • Patent number: 11879362
    Abstract: A turbine section of a gas turbine engine includes a case, a plurality of flow path components, and a mounting system. The case extends circumferentially at least partway around an axis of the gas turbine engine. The plurality of flow path components includes a flow path segment and a turbine vane. The mounting system couples the flow path segment to the case to support the flow path segment radially relative to the axis of the gas turbine engine.
    Type: Grant
    Filed: February 21, 2023
    Date of Patent: January 23, 2024
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel
  • Patent number: 11840936
    Abstract: A turbine shroud assembly includes a carrier assembly, a blade track segment, a retainer, and a clip shim. The carrier assembly is arranged circumferentially at least partway around an axis. The blade track segment is supported by the carrier assembly to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The retainer extends into the carrier assembly and the blade track segment. The clip shim is located between the carrier assembly and the blade track and configured to urge the blade track segment axially toward the carrier assembly.
    Type: Grant
    Filed: November 30, 2022
    Date of Patent: December 12, 2023
    Assignee: Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Aaron D. Sippel