Patents by Inventor Russell Deibel
Russell Deibel 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: 11085305Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: GrantFiled: May 17, 2019Date of Patent: August 10, 2021Assignee: Raytheon Technologies CorporationInventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Patent number: 10815803Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port. A method of cooling a component is also disclosed.Type: GrantFiled: July 25, 2019Date of Patent: October 27, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Scott D. Lewis, Dominic J. Mongillo, Jr., Mark F. Zelesky, Bret M. Teller, Russell Deibel, Matthew S. Gleiner
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Publication number: 20200291790Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: ApplicationFiled: May 17, 2019Publication date: September 17, 2020Inventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Publication number: 20190383153Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port. A method of cooling a component is also disclosed.Type: ApplicationFiled: July 25, 2019Publication date: December 19, 2019Inventors: Scott D. Lewis, Dominic J. Mongillo, JR., Mark F. Zelesky, Bret M. Teller, Russell Deibel, Matthew S. Gleiner
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Patent number: 10408071Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.Type: GrantFiled: August 26, 2014Date of Patent: September 10, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Scott D. Lewis, Dominic J. Mongillo, Jr., Mark F. Zelesky, Bret M. Teller, Russell Deibel, Matthew S. Gleiner
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Patent number: 10370980Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: GrantFiled: November 20, 2014Date of Patent: August 6, 2019Assignee: United Technologies CorporationInventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Patent number: 10053991Abstract: A component for a gas turbine engine includes a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.Type: GrantFiled: October 23, 2017Date of Patent: August 21, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Lawrence J. Willey, Matthew S. Gleiner, Russell Deibel
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Patent number: 9957894Abstract: An airfoil component is described herein. The airfoil component may include an OD platform comprising a gaspath face and a non-gaspath face coupled together via a plurality of cooling holes. The airfoil component may include an airfoil extending in from the outer diameter platform. The plurality of cooling holes comprises a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of the airfoil and a pressure side of the airfoil.Type: GrantFiled: February 20, 2015Date of Patent: May 1, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Russell Deibel, Matthew S. Gleiner
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Publication number: 20180058227Abstract: A component for a gas turbine engine includes a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.Type: ApplicationFiled: October 23, 2017Publication date: March 1, 2018Inventors: Lawrence J. WILLEY, Matthew S. GLEINER, Russell DEIBEL
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Patent number: 9845687Abstract: A component for a gas turbine engine includes a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.Type: GrantFiled: February 29, 2016Date of Patent: December 19, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Lawrence J. Willey, Matthew S. Gleiner, Russell Deibel
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Publication number: 20170022822Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: ApplicationFiled: November 20, 2014Publication date: January 26, 2017Inventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Publication number: 20160245096Abstract: A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.Type: ApplicationFiled: February 29, 2016Publication date: August 25, 2016Inventors: Lawrence J. WILLEY, Matthew S. GLEINER, Russell DEIBEL
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Publication number: 20160245093Abstract: An airfoil component is described herein. The airfoil component may include an OD platform comprising a gaspath face and a non-gaspath face coupled together via a plurality of cooling holes. The airfoil component may include an airfoil extending in from the outer diameter platform. The plurality of cooling holes comprises a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of the airfoil and a pressure side of the airfoil.Type: ApplicationFiled: February 20, 2015Publication date: August 25, 2016Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Russell Deibel, Matthew S. Gleiner
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Publication number: 20160230577Abstract: A vane according to an exemplary aspect of the present disclosure includes, among other things, a platform extending from an edge face and between spaced apart lateral faces and an airfoil extending outwardly from the platform. The platform includes at least one ejection port in the edge face and at least one passage connected to the at least one ejection port.Type: ApplicationFiled: August 26, 2014Publication date: August 11, 2016Applicant: United Technologies CorporationInventors: Scott D. Lewis, Dominic J. Mongillo, JR., Mark F. Zelesky, Bret M. Teller, Russell Deibel, Matthew S. Gleiner
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Patent number: 9303518Abstract: A component for a gas turbine engine according to an exemplary embodiment can include a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.Type: GrantFiled: July 2, 2012Date of Patent: April 5, 2016Assignee: United Technologies CorporationInventors: Lawrence J. Willey, Matthew S. Gleiner, Russell Deibel
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Publication number: 20140003961Abstract: A component for a gas turbine engine according to an exemplary embodiment of the present disclosure can include a platform having an outer surface and an inner surface. A cover plate can be positioned adjacent to the outer surface of the platform. The outer surface of the platform can include a pocket and the cover plate is positioned relative to the pocket to establish a platform cooling channel therebetween.Type: ApplicationFiled: July 2, 2012Publication date: January 2, 2014Inventors: Lawrence J. Willey, Matthew S. Gleiner, Russell Deibel