Patents by Inventor Daniel K. Vetters

Daniel K. Vetters 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 shroud assembly with multi-piece seals
    Patent number: 10480337
    Abstract: An assembly adapted for use in a gas turbine engine has a carrier component, a supported component, and a seal adapted to resist the flow of gasses between the supported component and the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for resisting gasses from passing over turbine blades included in the gas turbine engine.
    Type: Grant
    Filed: April 18, 2017
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Daniel K. Vetters
  • Gas turbine engine with health monitoring system
    Patent number: 10480342
    Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.
    Type: Grant
    Filed: January 19, 2016
    Date of Patent: November 19, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
  • Variable pitch fan for a gas turbine engine
    Patent number: 10473111
    Abstract: A gas turbine engine includes a fan having a plurality of fan blades configured to rotate about a central axis of the gas turbine engine. Each fan blade is configured to pivot about a pitch axis that extends radially away from the central axis to vary a pitch of the fan blade.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: November 12, 2019
    Assignee: Rolls-Royce Corporation
    Inventor: Daniel K. Vetters
  • 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
  • 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
  • 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
  • Turbine shroud with forward case and full hoop blade track
    Patent number: 10415415
    Abstract: A gas turbine engine includes a turbine shroud assembly arranged around a turbine wheel assembly. The turbine shroud assembly includes an annular turbine case, a blade track, and a forward case. The turbine case is arranged around a central axis of the turbine assembly. The blade track is located radially between the turbine case and the central axis. The forward case is coupled to the turbine case and is arranged to block axial movement of the blade track relative to the turbine case.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: September 17, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Edward C Rice, Daniel K Vetters
  • ACTIVELY COOLED ENGINE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190264572
    Abstract: An actively cooled assembly adapted for use in a gas turbine engine is disclosed herein. In illustrative embodiments, the assembly includes at least one ceramic matrix composite component with an attachment feature.
    Type: Application
    Filed: February 23, 2018
    Publication date: August 29, 2019
    Inventors: Jeffrey A. Walston, Daniel K. Vetters
  • Turbine shroud segment with side perimeter seal
    Patent number: 10385718
    Abstract: A turbine shroud segment of a turbine shroud for use in a turbine of a gas turbine engine is disclosed herein. The turbine shroud segment includes a carrier segment and a blade track segment. The carrier segment includes metallic materials. The blade track segment includes ceramic matrix composite materials. A seal is arranged between the carrier segment and the blade track segment.
    Type: Grant
    Filed: June 7, 2016
    Date of Patent: August 20, 2019
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Mark O'Leary, Daniel K. Vetters
  • KEYSTONED BLADE TRACK
    Publication number: 20190242268
    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: Application
    Filed: April 16, 2019
    Publication date: August 8, 2019
    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
  • Composite keystoned blade track
    Patent number: 10316682
    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 1, 2016
    Date of Patent: June 11, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce plc
    Inventors: Daniel K. Vetters, Paul A. Davis, Simon L. Jones, Steven Hillier, Peter Broadhead
  • Seal assembly for gas turbine engine components
    Patent number: 10301955
    Abstract: A gas turbine engine assembly includes adjacent components and a seal assembly. The seal assembly being configured to block gasses from passing through the interface of the adjacent components.
    Type: Grant
    Filed: November 29, 2016
    Date of Patent: May 28, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Aaron D. Sippel
  • AIRFOIL FOR A GAS TURBINE ENGINE HAVING INSULATING MATERIALS
    Publication number: 20190153879
    Abstract: An airfoil adapted for use in a gas turbine engine is disclosed. The airfoil may include components made from ceramic materials. The airfoil may include insulating material to thermally isolate portions of the airfoil.
    Type: Application
    Filed: November 20, 2017
    Publication date: May 23, 2019
    Inventors: Daniel K. Vetters, Ted J. Freeman
  • TURBINE SHROUD ASSEMBLY WITH SEALS
    Publication number: 20190153886
    Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a strip seal.
    Type: Application
    Filed: November 21, 2017
    Publication date: May 23, 2019
    Inventors: Daniel K. Vetters, Jeffrey Walston, David J. Thomas
  • Gas turbine engine with compliant layer for turbine shroud mounts
    Patent number: 10294809
    Abstract: A turbine shroud for use in a gas turbine engine includes a carrier, a blade track segment, and a load-distribution system. The carrier is arranged around a central axis of the turbine shroud. The blade track segment is configured to be supported by the carrier. The load-distribution system is positioned between the carrier and the blade track segment to distribute loads transmitted between the carrier and the blade track segment.
    Type: Grant
    Filed: March 9, 2016
    Date of Patent: May 21, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jack D. Petty
  • Turbine shroud with full hoop ceramic matrix composite blade track and seal system
    Patent number: 10287906
    Abstract: A gas turbine engine includes a blade track, a support assembly, and a seal system. The blade track is arranged around a central axis of the gas turbine engine to direct gasses through the gas turbine engine. The support assembly is arranged around the blade track to support the blade track relative to the central axis. The seal system is configured to block fluid communication between pressurized cavities formed in the support assembly.
    Type: Grant
    Filed: May 24, 2016
    Date of Patent: May 14, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Edward C. Rice, Daniel K. Vetters
  • Gas turbine engine with compliant layer for turbine vane assemblies
    Patent number: 10273818
    Abstract: A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.
    Type: Grant
    Filed: April 15, 2016
    Date of Patent: April 30, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Jack D. Petty
  • CERAMIC MATRIX COMPOSITE ASSEMBLY WITH COMPLIANT PIN ATTACHMENT FEATURES
    Publication number: 20190112947
    Abstract: An assembly adapted for use in a gas turbine engine. The assembly includes a support component comprising metallic materials, a supported component comprising ceramic matrix composite materials, and an attachment pin configured to couple the supported component to the support component. The attachment pin includes compliant features to distributes loads applied to the supported component.
    Type: Application
    Filed: October 18, 2017
    Publication date: April 18, 2019
    Inventors: Jeffrey A. Walston, Daniel K. Vetters
  • VARIABLE PITCH FAN FOR A GAS TURBINE ENGINE
    Publication number: 20190113049
    Abstract: A gas turbine engine includes a fan having a plurality of fan blades configured to rotate about a central axis of the gas turbine engine. Each fan blade is configured to pivot about a pitch axis that extends radially away from the central axis to vary a pitch of the fan blade.
    Type: Application
    Filed: October 18, 2017
    Publication date: April 18, 2019
    Inventor: Daniel K. Vetters