Patents by Inventor Aaron Sippel
Aaron 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).
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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
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Publication number: 20230212086Abstract: In some examples, article used as a component for a turbine engine that operates in a high temperature environment. The article may include: a ceramic or ceramic matrix composite (CMC) substrate; and a coating on the ceramic or the CMC substrate, wherein the coating defines an outer surface of the article. The coating includes a plurality of surface features defining channels on the outer surface of the article. The channels are configured to modify a flow of molten Calcia-Magnesia-Alumina Silicate (CMAS) over the outer surface of the coating in a gas flow over the outer surface of the article to reduce accumulation of the molten CMAS on the outer surface of the article.Type: ApplicationFiled: December 30, 2021Publication date: July 6, 2023Inventors: Taylor K. Blair, Ted J. Freeman, Aaron Sippel
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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
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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
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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
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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
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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
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Publication number: 20190093499Abstract: A system may include a component including a substrate and a non-continuous abradable coating on the substrate. The non-continuous abradable coating may include a plurality of respective physical segments. Each respective physical segment may be separated from an adjacent respective physical segment by a respective channel. A respective width of the respective channel between each respective segment and the adjacent respective segment may be greater than a combined maximum thermal expansion of the respective physical segment and the adjacent respective segment toward each other at a maximum design temperature of the component.Type: ApplicationFiled: September 27, 2018Publication date: March 28, 2019Inventors: Aaron Sippel, Matthew R. Gold
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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
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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
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Publication number: 20160230568Abstract: 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: ApplicationFiled: February 4, 2016Publication date: August 11, 2016Inventors: Aaron Sippel, Daniel Kent Vetters, Ted Freeman, Joseph Pan Lamusga