Patents by Inventor Larry Lebel
Larry Lebel 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: 11506383Abstract: The gas turbine combustor liner can delimit a combustion chamber, and have at least one monolithic ceramic block having a first face exposed to the combustion chamber and a second face opposite the first face, and a 3D fabric of ceramic fibers partially embedded inside the monolithic ceramic block, and partially extending outside the second face of the monolithic ceramic block, away from the combustion chamber.Type: GrantFiled: October 9, 2020Date of Patent: November 22, 2022Assignee: PRATT & WHITNEY CANADA CORPInventor: Larry Lebel
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Publication number: 20220113028Abstract: The gas turbine combustor liner can delimit a combustion chamber, and have at least one monolithic ceramic block having a first face exposed to the combustion chamber and a second face opposite the first face, and a 3D fabric of ceramic fibers partially embedded inside the monolithic ceramic block, and partially extending outside the second face of the monolithic ceramic block, away from the combustion chamber.Type: ApplicationFiled: October 9, 2020Publication date: April 14, 2022Inventor: Larry LEBEL
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Publication number: 20210025280Abstract: A turbine rotor for an aircraft engine includes a plurality of blades compressed by a compression ring made of ceramic matrix composite (CMC). The CMC includes at least one of: monofilaments and silicon carbide fibers. A method of extracting energy from an airflow using a turbine rotor of an aircraft engine is also disclosed.Type: ApplicationFiled: April 1, 2020Publication date: January 28, 2021Inventors: Larry LEBEL, John E. HOLOWCZAK, Andrew J. LAZUR
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Patent number: 10247034Abstract: An internally cooled turbine vane for a gas turbine engine has coolant flow channels between the interior walls of the vane and an insert, where the channels serve to convey a portion of the cooling air flow from a pressure side chamber to a suction side chamber. The turbine vane defines a radially extending passage with a dividing wall defining a front section and a rear section; the rear section having interior walls spaced apart from an insert to define the pressure side chamber and the suction side chamber. The insert may receive cooling air and conveys the cooling air into the pressure side chamber and the suction side chamber. A front surface of the insert or a rear surface of the dividing wall may have a clearance gap and an air flow channel communicating between the pressure side chamber and the suction side chamber.Type: GrantFiled: July 30, 2015Date of Patent: April 2, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Michael Papple, Larry Lebel
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Patent number: 10094564Abstract: A combustor for a gas turbine engine including a combustor shell, a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween, a core dilution passageway extending through the combustor shell and the heat shield, and a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway. The sub-chamber is separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway. Impingement holes are formed through the combustor shell and in fluid communication with the sub-chamber. A method of cooling an area surrounding a dilution hole in a combustor is also presented.Type: GrantFiled: April 17, 2015Date of Patent: October 9, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventor: Larry Lebel
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Patent number: 10041675Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: an upstream rail and an downstream rail defining an intermediate groove therebetween, each rail having a sealing surface with a plurality of slots extending between an upstream wall surface and a downstream wall surface, the sealing surface conforming to the interior surface of the combustor shell and defining a leakage gap therebetween.Type: GrantFiled: June 4, 2014Date of Patent: August 7, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Larry Lebel, Michael Papple
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Publication number: 20170030218Abstract: An internally cooled turbine vane for a gas turbine engine has coolant flow channels between the interior walls of the vane and an insert, where the channels serve to convey a portion of the cooling air flow from a pressure side chamber to a suction side chamber. The turbine vane defines a radially extending passage with a dividing wall defining a front section and a rear section; the rear section having interior walls spaced apart from an insert to define the pressure side chamber and the suction side chamber. The insert may receive cooling air and conveys the cooling air into the pressure side chamber and the suction side chamber. A front surface of the insert or a rear surface of the dividing wall may have a clearance gap and an air flow channel communicating between the pressure side chamber and the suction side chamber.Type: ApplicationFiled: July 30, 2015Publication date: February 2, 2017Inventors: Michael PAPPLE, Larry LEBEL
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Publication number: 20160305663Abstract: A combustor for a gas turbine engine including a combustor shell, a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween, a core dilution passageway extending through the combustor shell and the heat shield, and a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway. The sub-chamber is separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway. Impingement holes are formed through the combustor shell and in fluid communication with the sub-chamber. A method of cooling an area surrounding a dilution hole in a combustor is also presented.Type: ApplicationFiled: April 17, 2015Publication date: October 20, 2016Inventor: Larry LEBEL
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Publication number: 20150354818Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: an upstream rail and an downstream rail defining an intermediate groove therebetween, each rail having a sealing surface with a plurality of slots extending between an upstream wall surface and a downstream wall surface, the sealing surface conforming to the interior surface of the combustor shell and defining a leakage gap therebetween.Type: ApplicationFiled: June 4, 2014Publication date: December 10, 2015Applicant: Pratt & Whitney Canada Corp.Inventors: LARRY LEBEL, MICHAEL PAPPLE
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Patent number: 8568085Abstract: A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.Type: GrantFiled: July 19, 2010Date of Patent: October 29, 2013Assignee: Pratt & Whitney Canada CorpInventors: Franco Di Paola, Larry Lebel, François Doyon
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Publication number: 20120014809Abstract: A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, third and fourth sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13, PA-1 to PA-9, and SA-1 to SA-3, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y Cartesian coordinate values set forth in Table 3.Type: ApplicationFiled: July 19, 2010Publication date: January 19, 2012Inventors: Franco DI PAOLA, Larry Lebel, François Doyon
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Patent number: 7278826Abstract: An internal metering structure permits the exit apertures of a cooled airfoil to be sized to provide for easy manufacturability.Type: GrantFiled: August 18, 2004Date of Patent: October 9, 2007Assignee: Pratt & Whitney Canada Corp.Inventors: Timothy Blaskovich, Larry Lebel, Ricardo Trindade
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Patent number: 7097418Abstract: A gas turbine engine vane assembly provides double impingement cooling of a vane platform. An impingement structure disposed adjacent the vane platform defines at least first and second plenums in fluid flow communication, respectively defined in part by the vane platform. The vane platform has first and second surfaces defined within the first and second plenums, and which are cooled by successive impingement of secondary cooling air flow through the impingement structure.Type: GrantFiled: June 18, 2004Date of Patent: August 29, 2006Assignee: Pratt & Whitney Canada Corp.Inventors: Ricardo Trindade, Dan Que Pham, Larry Lebel
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Publication number: 20060099073Abstract: A dimple for use on a heat transfer surface exposed to a flowing gas, for use for example in a gas turbine engine, the dimple having an aspherical shape.Type: ApplicationFiled: November 5, 2004Publication date: May 11, 2006Inventors: Toufik Djeridane, Timothy Blaskovich, Sri Sreekanth, Ricardo Trindade, Michael Clyde Papple, Olivier Bibor, Larry Lebel, Phillip Ligrani
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Publication number: 20060039786Abstract: An internal metering structure permits the exit apertures of a cooled airfoil to be sized to provide for easy manufacturability.Type: ApplicationFiled: August 18, 2004Publication date: February 23, 2006Inventors: Timothy Blaskovich, Larry Lebel, Ricardo Trindade
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Publication number: 20050281663Abstract: A gas turbine engine vane assembly provides double impingement cooling of a vane platform. An impingement structure disposed adjacent the vane platform defines at least first and second plenums in fluid flow communication, respectively defined in part by the vane platform. The vane platform has first and second surfaces defined within the first and second plenums, and which are cooled by successive impingement of secondary cooling air flow through the impingement structure.Type: ApplicationFiled: June 18, 2004Publication date: December 22, 2005Inventors: Ricardo Trindade, Dan Pham, Larry Lebel