Patents by Inventor Ted Freeman
Ted Freeman 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).
-
Patent number: 11820716Abstract: A method of fabricating cooling features on a CMC component may comprise compressing a fabric preform within tooling including holes and/or recesses facing the fabric preform. During the compression, portions of the fabric preform are pushed into the holes and/or recesses. Gases are delivered through the tooling to deposit a matrix material on exposed surfaces of the fabric preform while the fabric preform is being compressed. The matrix material builds up on the portions of the fabric preform pushed into the holes and/or recesses, and a rigidized preform with surface protrusions is formed. The tooling is removed, and the rigidized preform is densified, thereby forming a CMC component including raised surface features.Type: GrantFiled: October 17, 2019Date of Patent: November 21, 2023Assignees: ROLLS ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC., ROLLS-ROYCE CORPORATIONInventors: Ted Freeman, Aaron Sippel, Robert Shinavski, Chris Barrett
-
Patent number: 11261750Abstract: A system and method for forming a ceramic matrix composite blade track is provided. The method may include stacking a plurality of first plies to form a first porous preform layer, the first plies including a plurality of first ceramic fibers. The method may further include stacking a plurality of second plies to form a second porous preform layer, the second plies including a plurality of second ceramic fibers. The method may further include combining the first porous preform layer and the second porous preform layer to form a unified porous preform. The method may further include forming a structural layer by infiltrating the first porous preform with a first ceramic matrix material, and forming an abradable layer by infiltrating the second porous preform with a second ceramic matrix material.Type: GrantFiled: March 26, 2018Date of Patent: March 1, 2022Assignees: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE CORPORATIONInventors: Sean Landwehr, Ted Freeman, Aaron Sippel
-
Patent number: 11008881Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.Type: GrantFiled: July 23, 2018Date of Patent: May 18, 2021Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
-
Patent number: 10989060Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: GrantFiled: April 10, 2020Date of Patent: April 27, 2021Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites Inc.Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
-
Publication number: 20210003024Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: ApplicationFiled: April 10, 2020Publication date: January 7, 2021Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
-
Publication number: 20200123067Abstract: A method of fabricating cooling features on a CMC component may comprise compressing a fabric preform within tooling including holes and/or recesses facing the fabric preform. During the compression, portions of the fabric preform are pushed into the holes and/or recesses. Gases are delivered through the tooling to deposit a matrix material on exposed surfaces of the fabric preform while the fabric preform is being compressed. The matrix material builds up on the portions of the fabric preform pushed into the holes and/or recesses, and a rigidized preform with surface protrusions is formed. The tooling is removed, and the rigidized preform is densified, thereby forming a CMC component including raised surface features.Type: ApplicationFiled: October 17, 2019Publication date: April 23, 2020Applicants: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Ted Freeman, Aaron Sippel, Robert Shinavski, Chris Barrett
-
Patent number: 10619503Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: GrantFiled: July 26, 2017Date of Patent: April 14, 2020Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
-
Publication number: 20190292931Abstract: A system and method for forming a ceramic matrix composite blade track is provided. The method may include stacking a plurality of first plies to form a first porous preform layer, the first plies including a plurality of first ceramic fibers. The method may further include stacking a plurality of second plies to form a second porous preform layer, the second plies including a plurality of second ceramic fibers. The method may further include combining the first porous preform layer and the second porous preform layer to form a unified porous preform. The method may further include forming a structural layer by infiltrating the first porous preform with a first ceramic matrix material, and forming an abradable layer by infiltrating the second porous preform with a second ceramic matrix material.Type: ApplicationFiled: March 26, 2018Publication date: September 26, 2019Applicants: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Sean Landwehr, Ted Freeman, Aaron Sippel
-
Patent number: 10400612Abstract: An airfoil and a method of manufacturing an airfoil may be provided, where the airfoil comprises a core and a shell. The core comprises core ceramic fibers extending along a span of the airfoil. The shell surrounds the core and includes shell ceramic fibers. Substantially all of the core ceramic fibers are arranged in a radial direction. The airfoil may also be a ceramic matrix composite formed by infiltrating the core and the shell with a matrix material.Type: GrantFiled: December 6, 2016Date of Patent: September 3, 2019Assignee: Rolls-Royce CorporationInventors: Ted Freeman, Todd Engel, Adam Chamberlain, Aaron Sippel, Sean Landwehr
-
Patent number: 10253639Abstract: The disclosure describes a gas turbine engine blade that includes a dovetail portion comprising a first ceramic matrix composite, an airfoil portion comprising the first ceramic matrix composite, a transition portion between the airfoil portion and the dovetail portion, and a platform portion that substantially surrounds the transition portion. The airfoil portion may define a capture feature that is configured to engage with and mechanically restrain the platform portion from moving beyond the capture feature toward a tip of the airfoil portion.Type: GrantFiled: February 4, 2016Date of Patent: April 9, 2019Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce CorporationInventors: Aaron Sippel, Daniel Kent Vetters, Ted Freeman, Joseph Pan Lamusga
-
Patent number: 10221713Abstract: A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.Type: GrantFiled: May 26, 2015Date of Patent: March 5, 2019Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES INC., ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES INC.Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert
-
Publication number: 20180328213Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.Type: ApplicationFiled: July 23, 2018Publication date: November 15, 2018Applicants: Rolls-Royce Corporation, Rolls-Royce Notth American Technologies Inc., Rolls-Royce High Temperature Composites Inc.Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
-
Publication number: 20180311934Abstract: A system may include a first component that includes a substrate including a ceramic or a CMC, a bond coat on the substrate, and a seal coating including at least one rare earth silicate on the bond coat. The system also includes a second component that defines a surface. The surface of the second component contacts the seal coating, and the first component and the second component are substantially stationary relative to each other.Type: ApplicationFiled: April 28, 2017Publication date: November 1, 2018Inventors: Brian J. Shoemaker, Aaron Sippel, Ted Freeman
-
Patent number: 10087770Abstract: A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.Type: GrantFiled: May 26, 2015Date of Patent: October 2, 2018Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
-
Patent number: 9963990Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: GrantFiled: May 26, 2015Date of Patent: May 8, 2018Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation, Rolls-Royce High Temperature Composites, Inc.Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
-
Publication number: 20170321567Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: ApplicationFiled: July 26, 2017Publication date: November 9, 2017Applicants: ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC., ROLLS-ROYCE CORPORATION, ROLLS-ROYCE HIGH TEMPERATURE COMPOSITES, INC.Inventors: Daniel K. Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert, Douglas D. Dierksmeier, Jun Shi, Todd Engel, Matt Brandt
-
Publication number: 20170298745Abstract: An airfoil and a method of manufacturing an airfoil may be provided, where the airfoil comprises a core and a shell. The core comprises core ceramic fibers extending along a span of the airfoil. The shell surrounds the core and includes shell ceramic fibers. Substantially all of the core ceramic fibers are arranged in a radial direction. The airfoil may also be a ceramic matrix composite formed by infiltrating the core and the shell with a matrix material.Type: ApplicationFiled: December 6, 2016Publication date: October 19, 2017Inventors: Ted Freeman, Todd Engel, Adam Chamberlain, Aaron Sippel, Sean Landwehr
-
Patent number: 9664699Abstract: This disclosure concerns plants, plant materials, and the oil characteristics thereof. In embodiments, compositions and methods for determining the total oil content of plant materials are provided. Such methods and compositions may in some embodiments allow for the characterization and screening of oil traits and sub-traits that are difficult or impossible to distinguish by conventional techniques.Type: GrantFiled: May 25, 2016Date of Patent: May 30, 2017Assignee: Dow AgroSciences LLCInventors: Thomas G. Patterson, Ted Freeman, Joshua A. Flook
-
Publication number: 20160348528Abstract: A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.Type: ApplicationFiled: May 26, 2015Publication date: December 1, 2016Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Douglas David Dierksmeier, Jun Shi, Todd Engel
-
Publication number: 20160348526Abstract: A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.Type: ApplicationFiled: May 26, 2015Publication date: December 1, 2016Inventors: Daniel Kent Vetters, David J. Thomas, Ted Freeman, Joseph Lamusga, Rick Uskert