Patents by Inventor Jeffrey R. Lavin
Jeffrey R. Lavin 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: 10436063Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.Type: GrantFiled: August 17, 2012Date of Patent: October 8, 2019Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Kirk A. Shute, Jeffrey R. Lavin, Russell P. Parrish
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Patent number: 9803503Abstract: An exhaust liner assembly including an interface between moveable parts includes a seal liner having a plurality of slots. The size of each slot varies with the circumferential position of the liner assembly to provide a stable cavity pressure within the interface to create a stable barrier about the entire circumference of the exhaust liner assembly.Type: GrantFiled: April 4, 2012Date of Patent: October 31, 2017Assignee: United Technologies CorporationInventors: Jeffrey R. Lavin, Michael J. Murphy
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Patent number: 9719376Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.Type: GrantFiled: August 18, 2016Date of Patent: August 1, 2017Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Jeffrey R. Lavin
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Publication number: 20170152761Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.Type: ApplicationFiled: August 18, 2016Publication date: June 1, 2017Inventors: Shawn M. McMahon, Jeffrey R. Lavin
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Patent number: 9447700Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.Type: GrantFiled: February 13, 2014Date of Patent: September 20, 2016Assignee: United Technologies CorporationInventors: Shawn M. McMahon, Jeffrey R. Lavin
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Patent number: 9316315Abstract: A seal assembly seals an interface between adjacent liner sections. The seal assembly comprises a seal carrier mounted to a first plate, a seal body overlapping at least a portion of the seal carrier to define a plane of travel between the seal body and the seal carrier, and at least one resilient member configured to bias the seal body against a second plate. The seal carrier includes an indented portion that extends radially inward of the plane of travel.Type: GrantFiled: March 9, 2012Date of Patent: April 19, 2016Assignee: United Technologies CorporationInventors: Russell P. Parrish, Jeffrey R. Lavin
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Publication number: 20140230246Abstract: A system for connecting spaced components of a gas turbine engine includes connecting one end of a T-bar to each of the spaced components. One component is attached to the crossbar portion of the T-bar by trapping the crossbar between the component and a bracket. The second component is attached to the shaft portion using a hanger nut connected to the shaft portion of the T-bar and bolted to the second component. The system may be installed by attaching the crossbar portion, then advancing the first component towards the second component until the shaft portion passes through an aperture in the second component. The hanger nut is attached to the shaft portion and the second component.Type: ApplicationFiled: February 13, 2014Publication date: August 21, 2014Applicant: United Technologies CorporationInventors: Shawn M. McMahon, Jeffrey R. Lavin
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Publication number: 20140047850Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.Type: ApplicationFiled: August 17, 2012Publication date: February 20, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Shawn M. McMahon, Kirk A. Shute, Jeffrey R. Lavin, Russell P. Parrish
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Publication number: 20130234407Abstract: A seal assembly seals an interface between adjacent liner sections. The seal assembly comprises a seal carrier mounted to a first plate, a seal body overlapping at least a portion of the seal carrier to define a plane of travel between the seal body and the seal carrier, and at least one resilient member configured to bias the seal body against a second plate. The seal carrier includes an indented portion that extends radially inward of the plane of travel.Type: ApplicationFiled: March 9, 2012Publication date: September 12, 2013Inventors: Russell P. Parrish, Jeffrey R. Lavin
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Publication number: 20120207584Abstract: An exhaust liner assembly including an interface between moveable parts includes a seal liner having a plurality of slots. The size of each slot varies with the circumferential position of the liner assembly to provide a stable cavity pressure within the interface to create a stable barrier about the entire circumference of the exhaust liner assembly.Type: ApplicationFiled: April 4, 2012Publication date: August 16, 2012Inventors: Jeffrey R. Lavin, Michael J. Murphy
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Patent number: 8201413Abstract: An exhaust liner assembly including an interface between moveable parts includes a seal liner having a plurality of slots. The size of each slot varies with the circumferential position of the liner assembly to provide a stable cavity pressure within the interface to create a stable barrier about the entire circumference of the exhaust liner assembly.Type: GrantFiled: July 24, 2006Date of Patent: June 19, 2012Assignee: United Technologies CorporationInventors: Jeffrey R. Lavin, Michael J. Murphy
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Patent number: 8127526Abstract: A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.Type: GrantFiled: January 16, 2008Date of Patent: March 6, 2012Assignee: United Technologies CorporationInventors: Michael Joseph Murphy, Jeffrey R. Lavin
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Patent number: 7631481Abstract: A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.Type: GrantFiled: December 1, 2004Date of Patent: December 15, 2009Assignee: United Technologies CorporationInventors: Curtis C Cowan, Jorge I. Farah, Debora F. Kehret, Stanley Keysa, Jeffrey R. Lavin, Michael Murphy, Stephen A. Paul, Richard Scott
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Publication number: 20090178383Abstract: A gas turbine engine includes an exhaust liner having cold and hot sheets radially spaced from one another and interconnected by a band arranged in a cavity between the hot and cold sheets. In one example, the band is Z-shaped to permit thermal growth of the hot sheets relative to the cold sheets in the axial and radial directions. The hot sheets include axially adjacent portions that provide slots that are in fluid communication with the space. Cooling fluid is provided to the cavity through impingement jets in the cold sheet. The slots are arranged radially between the hot sheet portions.Type: ApplicationFiled: January 16, 2008Publication date: July 16, 2009Inventors: Michael Joseph Murphy, Jeffrey R. Lavin
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Publication number: 20080016871Abstract: An exhaust liner assembly including an interface between moveable parts includes a seal liner having a plurality of slots. The size of each slot varies with the circumferential position of the liner assembly to provide a stable cavity pressure within the interface to create a stable barrier about the entire circumference of the exhaust liner assembly.Type: ApplicationFiled: July 24, 2006Publication date: January 24, 2008Inventors: Jeffrey R. Lavin, Michael J. Murphy