Patents by Inventor Jonathan Lemoine
Jonathan Lemoine 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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Publication number: 20180328209Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.Type: ApplicationFiled: July 12, 2018Publication date: November 15, 2018Inventors: Jonathan Lemoine, Steven D. Porter
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Patent number: 10107118Abstract: An interface within a gas turbine engine includes a sealing surface defined by a portion of a vane platform. A seal is in contact with said sealing surface. A barrier is transverse to the sealing surface.Type: GrantFiled: June 27, 2014Date of Patent: October 23, 2018Assignee: United Technologies CorporationInventors: John T Ols, Richard N Allen, Paul K Sanchez, Steven D Porter, Jonathan Lemoine
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Publication number: 20180298823Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.Type: ApplicationFiled: June 19, 2018Publication date: October 18, 2018Inventors: Kevin Zacchera, Matthew Andrew Hough, Jonathan Lemoine, Christopher Treat, Alberto A. Mateo
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Publication number: 20180292089Abstract: A combustor panel of a combustor may include a combustion facing surface and a cooling surface opposite the combustion facing surface. An attachment feature may extend from the cooling surface. The attachment feature may define a first channel extending through the attachment feature to the combustion facing surface. The combustor channel may be formed by additive manufacturing.Type: ApplicationFiled: April 5, 2017Publication date: October 11, 2018Applicant: United Technologies CorporationInventors: Steven D. Porter, Jonathan Lemoine, Kevin Zacchera
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Publication number: 20180283690Abstract: A combustor panel may include a combustion facing surface, a cooling surface opposite the combustion facing surface, a first heat transfer pin extending from the cooling surface having a first geometric specification, and a second heat transfer pin extending from the cooling surface having a second geometric specification. The first geometric specification may be different than the second geometric specification. The first geometric specification may be a first height of the first pin and the second geometric specification may be a second height of the second pin.Type: ApplicationFiled: March 29, 2017Publication date: October 4, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: JONATHAN LEMOINE, KEVIN ZACCHERA, JONATHAN JEFFERY EASTWOOD
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Patent number: 10087785Abstract: A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.Type: GrantFiled: February 9, 2015Date of Patent: October 2, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Alexander Broulidakis, Anthony P. Cherolis, Jonathan Lemoine, Kalpendu J. Parekh, Steven W. Trinks, Christopher Treat, Kevin Zacchera, Alberto A. Mateo
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Patent number: 10047623Abstract: A compliant seal assembly that may be for an MTF of a gas turbine engine includes a housing orientated about an axis with a circumferentially extending groove in the housing opened radially outward. An annular carrier of the assembly is constructed and arranged to move radially within the groove, and includes a circumferentially extending channel that is opened radially outward for receipt of a piston ring that may seal to a surrounding cylindrical wall. In operation, the carrier moves radially with respect to the housing to compensate for radial displacement between the housing and the wall, and the piston ring moves axially along the wall to compensate for axial displacement between the housing and the wall.Type: GrantFiled: November 11, 2015Date of Patent: August 14, 2018Assignee: United Technologies CorporationInventors: Jonathan Lemoine, Steven D. Porter
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Patent number: 10036503Abstract: Aspects of the disclosure are directed to a tube of an engine of an aircraft configured to transfer a fluid, a boss of the engine, and a shim coupled to at least one of the tube and the boss that is configured to maintain a gap between the tube and the boss when the engine is assembled.Type: GrantFiled: April 13, 2015Date of Patent: July 31, 2018Assignee: United Technologies CorporationInventors: Anthony P. Cherolis, Alexander Broulidakis, Matthew A. Hough, Jonathan Lemoine, Christopher Treat
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Patent number: 10030582Abstract: A cooling structure for a gas turbine engine comprises a gas turbine engine structure defining a cooling cavity. A cooling component is configured to direct cooling flow in a desired direction into the cooling cavity. A bracket supports the cooling component and has an attachment interface to fix the bracket to the gas turbine engine structure. A first orientation feature associated with the bracket. A second orientation feature is associated with the gas turbine engine structure. The first and second orientation features cooperate with each other to ensure that the cooling component is only installed in one orientation relative to the gas turbine engine structure. A gas turbine engine and a method of installing a cooling structure are also disclosed.Type: GrantFiled: February 9, 2015Date of Patent: July 24, 2018Assignee: United Technologies CorporationInventors: Kevin Zacchera, Matthew Andrew Hough, Jonathan Lemoine, Christopher Treat, Alberto A. Mateo
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Patent number: 9995171Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.Type: GrantFiled: January 16, 2015Date of Patent: June 12, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Andrew D. Burdick, Anthony P. Cherolis, Christopher Treat, Jonathan Lemoine, Robert Russell Mayer, Jorge I. Farah, John H. Mosley
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Patent number: 9951624Abstract: A fastener assembly includes a first component including a first fastener opening that has a cylindrical portion and a conical portion. A second component includes a second fastener opening. A fastener for extending through the first fastener opening and the second fastener opening and a clinch nut for attaching to the fastener is included.Type: GrantFiled: February 9, 2015Date of Patent: April 24, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Alexander Broulidakis, Jonathan Lemoine, Joseph J. Sedor, Patrick Michael Nadeau
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Publication number: 20180087406Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. Multiple spokes protrude radially outward from the inner frame case, and at least one service line is connected to the inner frame case.Type: ApplicationFiled: December 4, 2017Publication date: March 29, 2018Inventors: Jeffrey J. Lienau, Dustin W. Davis, Jonathan Lemoine, Kevin Zacchera
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Patent number: 9926797Abstract: According to one embodiment of the present invention, a sealing arrangement includes a turbine static structure with an inner case and a seal ring each having contact surfaces. The sealing arrangement also has a bearing compartment with a contact surface. A piston seal is positioned between the inner case, the seal ring, and the bearing compartment and is configured to contact the contact surfaces.Type: GrantFiled: January 22, 2015Date of Patent: March 27, 2018Assignee: United Technologies CorporationInventors: Steven D. Porter, Jonathan Lemoine, Kevin Zacchera
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Patent number: 9885254Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case defining a sealed torque box cavity. The mid-turbine frame also includes multiple spokes protruding radially outward from the inner frame case. The mid-turbine frame also includes at least one service line connected to the inner frame case.Type: GrantFiled: April 24, 2015Date of Patent: February 6, 2018Assignee: United Technologies CorporationInventors: Jeffrey J. Lienau, Dustin W. Davis, Jonathan Lemoine, Kevin Zacchera
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Publication number: 20180017260Abstract: A combustor assembly for a gas turbine engine comprises a vane support ring; an annular combustor extending around a central axis and being located radially inwards of the vane support ring, the annular combustor including an aft end, a forward end with at least one opening through which at least one fuel nozzle is received, and an annular outer shell and an annular inner shell that define an annular combustion chamber there between, the annular outer shell including a radially-outwardly extending flange including at least one scallop cut; and a stop member integrally formed with the vane support ring.Type: ApplicationFiled: July 14, 2016Publication date: January 18, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Thomas E. Clark, Harvey C. Lee, Brian C. McLaughlin, Jonathan Lemoine
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Publication number: 20170336074Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield having an annular shape. A first groove may be formed circumferentially along an inner surface of the heat shield. A support lock may have a second groove extending radially inward from a distal surface of the support lock. A retention ring may be configured to fit within the first groove of the heat shield and the second groove of the support lock.Type: ApplicationFiled: May 17, 2016Publication date: November 23, 2017Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: David J. Sander, Jonathan Lemoine
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Publication number: 20170292702Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape and a groove formed circumferentially along an inner surface of the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The groove in the heat shield may be configured to retain the tab of the support lock.Type: ApplicationFiled: April 12, 2016Publication date: October 12, 2017Applicant: United Technologies CorporationInventors: DAVID J. SANDER, JONATHAN LEMOINE
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Publication number: 20170292704Abstract: A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape. The heat shield may define an aperture extending through the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The aperture in the heat shield may be configured to retain the tab of the support lock.Type: ApplicationFiled: April 12, 2016Publication date: October 12, 2017Applicant: United Technologies CorporationInventors: DAVID J. SANDER, JONATHAN LEMOINE
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Publication number: 20170276355Abstract: A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.Type: ApplicationFiled: March 22, 2016Publication date: September 28, 2017Inventors: David J. Sander, Jonathan Lemoine, Harvey C. Lee, Dalton C. Petrillo
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Patent number: 9732628Abstract: A mid-turbine frame for a gas turbine engine includes an inner frame case. A bearing support member is located adjacent the inner frame case. At least one spoke is attached to the inner frame case. A passage extends through at least one spoke, the inner frame case, and the bearing support member.Type: GrantFiled: March 20, 2015Date of Patent: August 15, 2017Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anthony P. Cherolis, Joshua Daniel Winn, Jonathan Lemoine