Patents by Inventor Kevin L. Rugg
Kevin L. Rugg 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: 10823406Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.Type: GrantFiled: November 2, 2017Date of Patent: November 3, 2020Assignee: Raytheon Technologies CorporationInventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
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Patent number: 10801351Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.Type: GrantFiled: April 17, 2018Date of Patent: October 13, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Kevin L. Rugg, Winston Gregory Smiddy
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Publication number: 20190316481Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a sealing portion that extends from an engagement portion. The sealing portion has a seal face that extends circumferentially between first and second mate faces. The engagement portion defines an internal cavity that extends circumferentially between the first and second mate faces, and the engagement portion has an impingement face opposite the seal face that defines an elongated opening to the internal cavity. A method of sealing is also disclosed.Type: ApplicationFiled: April 17, 2018Publication date: October 17, 2019Inventors: Kevin L. Rugg, Winston Gregory Smiddy
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Patent number: 10385774Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.Type: GrantFiled: September 19, 2016Date of Patent: August 20, 2019Assignee: United Technologies CorporationInventors: Daniel Bernard Kupratis, Tania Bhatia Kashyap, Mark F. Zelesky, Arthur W. Utay, Gabriel L. Suciu, Thomas N. Slavens, Kevin L. Rugg, Brian Merry
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Patent number: 10364041Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.Type: GrantFiled: July 25, 2016Date of Patent: July 30, 2019Assignee: United Technologies CorporationInventors: Daniel Bernard Kupratis, Arthur W. Utay, Tania Bhatia Kashyap, Thomas N. Slavens, Kevin L. Rugg, Mark F. Zelesky, Brian D. Merry, Gabriel L. Suciu
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Patent number: 10358929Abstract: An airfoil includes a core with a first Young's Modulus; and an outer section at least partially surrounding the core with a second Young's Modulus, wherein the first Young's Modulus is higher than the second Young's Modulus.Type: GrantFiled: July 1, 2014Date of Patent: July 23, 2019Assignee: United Technologies CorporationInventors: Michael G. McCaffrey, Greg C. Ojard, Kevin L. Rugg
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Patent number: 10174624Abstract: A blade for a gas turbine engine includes composite layers that include a uni-directional layer and a fabric compliant wedge layer that are arranged adjacent to the uni-directional layer. The fabric compliant wedge layer has a reduced compressive Young's modulus compared to the uni-directional layer.Type: GrantFiled: May 26, 2015Date of Patent: January 8, 2019Assignee: United Technologies CorporationInventors: Michael G. McCaffrey, Kevin L. Rugg, Michael G. Abbott
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Publication number: 20180156456Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.Type: ApplicationFiled: November 2, 2017Publication date: June 7, 2018Inventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
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Publication number: 20180080373Abstract: A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.Type: ApplicationFiled: September 19, 2016Publication date: March 22, 2018Inventors: Daniel Bernard Kupratis, Tania Bhatia Kashyap, Mark F. Zelesky, Arthur W. Utay, Gabriel L. Suciu, Thomas N. Slavens, Kevin L. Rugg, Brian Merry
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Patent number: 9890953Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.Type: GrantFiled: January 2, 2015Date of Patent: February 13, 2018Assignee: United Technologies CorporationInventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
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Publication number: 20180023576Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.Type: ApplicationFiled: July 25, 2016Publication date: January 25, 2018Applicant: United Technologies CorporationInventors: Daniel Bernard Kupratis, Arthur W. Utay, Tania Bhatia Kashyap, Thomas N. Slavens, Kevin L. Rugg, Mark F. Zelesky, Brian D. Merry, Gabriel L. Suciu
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Patent number: 9664389Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first attachment member including an opening, a second attachment member including a loop at least partially extending through the opening, and a pin between the first attachment member and the loop.Type: GrantFiled: December 12, 2014Date of Patent: May 30, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
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Publication number: 20160252248Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first attachment member including an opening, a second attachment member including a loop at least partially extending through the opening, and a pin between the first attachment member and the loop.Type: ApplicationFiled: December 12, 2014Publication date: September 1, 2016Inventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
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Publication number: 20160160658Abstract: An airfoil includes a core with a first Young's Modulus; and an outer section at least partially surrounding the core with a second Young's Modulus, wherein the first Young's Modulus is higher than the second Young's Modulus.Type: ApplicationFiled: July 1, 2014Publication date: June 9, 2016Inventors: Michael G. McCaffrey, Greg C. Ojard, Kevin L. Rugg
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Patent number: 9334743Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.Type: GrantFiled: May 26, 2011Date of Patent: May 10, 2016Assignee: United Technologies CorporationInventors: Ioannis Alvanos, Gabriel L. Suciu, Douglas M. Berczik, John D. Riehl, Kevin L. Rugg
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Publication number: 20160069199Abstract: Disclosed is a gas turbine engine that includes a plurality of stator vanes. Each of the stator vanes includes an airfoil section and a platform provided at an end of the airfoil section. The platforms are provided with flanges on opposed ends thereof, and the flanges are fastened to corresponding flanges of an adjacent one of the plurality of stator vanes.Type: ApplicationFiled: April 11, 2014Publication date: March 10, 2016Inventors: Shelton O. Duelm, Kevin L. Rugg
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Publication number: 20150345790Abstract: A combined liner and panel for use in a gas turbine engine comprise a ceramic matrix composite panel having a plurality of extending members extending away from a face of ceramic matrix composite panel which will face hot products of combustion. A liner includes a plurality of spring members that apply a bias force biasing the extending members. The spring members bias the extending members on the panel in a direction away from the face of the panel which will face the hot products of combustion. A gas turbine engine, and a method of attaching a ceramic matrix composite panel to a liner are also disclosed.Type: ApplicationFiled: January 2, 2015Publication date: December 3, 2015Inventors: Jose E. Ruberte Sanchez, Timothy J. McAlice, Kevin L. Rugg
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Publication number: 20120301315Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.Type: ApplicationFiled: May 26, 2011Publication date: November 29, 2012Inventors: Ioannis Alvanos, Gabriel L. Suciu, Douglas M. Berczik, John D. Riehl, Kevin L. Rugg