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 with mounted full hoop blade track
    Patent number: 10247040
    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: April 2, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
  • Full hoop blade track with interstage cooling air
    Patent number: 10240476
    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: March 26, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
  • Turbine shroud with axially separated pressure compartments
    Patent number: 10221715
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a blade track. One or more cavities are formed between the carrier and blade track to provide cooling air to the blade track.
    Type: Grant
    Filed: February 19, 2016
    Date of Patent: March 5, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Bruce E. Varney, Daniel K. Vetters
  • Turbine shroud segment with load distribution springs
    Patent number: 10196919
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: February 5, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • Turbine shroud segment with integrated cooling air distribution system
    Patent number: 10184352
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: January 22, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • IMPINGEMENT TUBES FOR GAS TURBINE ENGINE ASSEMBLIES WITH CERAMIC MATRIX COMPOSITE COMPONENTS
    Publication number: 20190017400
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Application
    Filed: September 20, 2018
    Publication date: January 17, 2019
    Inventors: Daniel K. Vetters, Peter Broadhead, Steven Hillier
  • Composite blades for gas turbine engines
    Patent number: 10180071
    Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed as a composite structure including a number of plies of ceramic-containing material. The blades each include a root to fit within dovetail slots of the rotor disk to couple the blades to the rotor disk.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: January 15, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Daniel K. Vetters
  • GAS TURBINE ENGINE WITH THERMOELECTRIC INTERCOOLER
    Publication number: 20190003393
    Abstract: A gas turbine engine includes a compressor, a cooling source, and a thermoelectric intercooler adapted for selective operation in response to operational states of the gas turbine engine.
    Type: Application
    Filed: February 3, 2017
    Publication date: January 3, 2019
    Inventors: Douglas D. Dierksmeier, Daniel K. Vetters, Michael A. Karam
  • CERAMIC MATRIX COMPOSITE JOINTS
    Publication number: 20180371947
    Abstract: An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.
    Type: Application
    Filed: May 30, 2018
    Publication date: December 27, 2018
    Inventors: Aaron D. Sippel, Ted J. Freeman, Joseph P. Lamusga, Daniel K. Vetters, Sean E. Landwehr, Bruce E. Varney
  • TURBINE SHROUD SEGMENT WITH BUFFER AIR SEAL SYSTEM
    Publication number: 20180371931
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Application
    Filed: August 21, 2018
    Publication date: December 27, 2018
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • Seal segment low pressure cooling protection system
    Patent number: 10132194
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling flow inserts direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: December 16, 2015
    Date of Patent: November 20, 2018
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventor: Daniel K. Vetters
  • TURBINE SHROUD SEGMENT WITH FLANGE-FACING PERIMETER SEAL
    Publication number: 20180328208
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Application
    Filed: July 11, 2018
    Publication date: November 15, 2018
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • TURBINE SHROUD ASSEMBLY WITH MULTI-PIECE SEAL
    Publication number: 20180298773
    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: Application
    Filed: April 18, 2017
    Publication date: October 18, 2018
    Inventor: Daniel K. Vetters
  • Impingement tubes for CMC seal segment cooling
    Patent number: 10100654
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: October 16, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Daniel K. Vetters, Peter Broadhead, Steven Hillier
  • TURBINE SHROUD WITH CLAMPED FLANGE ATTACHMENT
    Publication number: 20180291769
    Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The assembly also includes a retention assembly for coupling the supported component to the carrier.
    Type: Application
    Filed: June 11, 2018
    Publication date: October 11, 2018
    Inventors: Daniel K. Vetters, Todd Engel, Robert J. Shinavski
  • Turbine shroud segment with buffer air seal system
    Patent number: 10094234
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: October 9, 2018
    Assignees: Rolls-Royce North America Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman
  • TURBINE ENGINE ASSEMBLY WITH TUBULAR LOCATING INSERTS
    Publication number: 20180274382
    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: Application
    Filed: June 5, 2018
    Publication date: September 27, 2018
    Inventors: Daniel K. Vetters, Jun Shi, Jeffrey A. Walston, Aaron D. Sippel
  • TURBINE BLADE WITH CERAMIC MATRIX COMPOSITE MATERIAL CONSTRUCTION
    Publication number: 20180230826
    Abstract: A turbine-blade assembly for use in a gas turbine engine is disclosed. The turbine-blade assembly includes an attachment body, a heat shield, and a retainer. The heat shield surrounds a portion of the attachment body. The retainer is configured to retain the heat shield on the turbine-blade assembly.
    Type: Application
    Filed: November 1, 2016
    Publication date: August 16, 2018
    Inventors: Daniel K. Vetters, Ted J. Freeman, Jim Schwefel, Phil Bastnagel
  • TURBINE BLADE WITH CERAMIC MATRIX COMPOSITE MATERIAL CONSTRUCTION
    Publication number: 20180230823
    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: October 28, 2016
    Publication date: August 16, 2018
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Ted J. Freeman, David J. Thomas
  • Turbine shroud segment with flange-facing perimeter seal
    Patent number: 10047624
    Abstract: A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
    Type: Grant
    Filed: January 22, 2016
    Date of Patent: August 14, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Mark O'Leary, Daniel K. Vetters, Matthew R. Brandt, Ted J. Freeman