Patents by Inventor Joe Lanzino
Joe Lanzino 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: 11415015Abstract: An assembly for a gas turbine engine has a support structure and a tube configured to circulate lubricant and mounted to the support structure, a sacrificial sleeve extending around the tube and disposed between the support structure and the tube, the sacrificial sleeve welded to the support structure. A method of mounting a fluid carrying tube to a support structure in a gas turbine engine is provided.Type: GrantFiled: October 23, 2019Date of Patent: August 16, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Michael A. Fryer, Joe Lanzino
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Publication number: 20210123356Abstract: An assembly for a gas turbine engine has a support structure and a tube configured to circulate lubricant and mounted to the support structure, a sacrificial sleeve extending around the tube and disposed between the support structure and the tube, the sacrificial sleeve welded to the support structure. A method of mounting a fluid carrying tube to a support structure in a gas turbine engine is provided.Type: ApplicationFiled: October 23, 2019Publication date: April 29, 2021Inventors: Michael A. FRYER, Joe LANZINO
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Patent number: 10364823Abstract: A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.Type: GrantFiled: May 16, 2016Date of Patent: July 30, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: George Guglielmin, Joe Lanzino, Enzo Macchia, Barry Barnett, Andreas Eleftheriou, Thomas McDonough
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Patent number: 10060441Abstract: A stator airfoil of a gas turbine engine according to one embodiment includes at least two winglets projecting transversely from opposed sides of a stator airfoil, respectively. Each winglet includes a leading edge axially and outwardly extending from one of the opposed sides of the stator airfoil and a trailing edge extending from the stator airfoil to join with the leading edge of the winglet. The winglets therefore provide a wide trailing edge thereof to aerodynamically manage boundary layers and micro-shocks of a working fluid.Type: GrantFiled: May 26, 2015Date of Patent: August 28, 2018Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Enzo Macchia, George Guglielmin, Bhawan Patel, Joe Lanzino
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Patent number: 9587645Abstract: A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core.Type: GrantFiled: July 22, 2011Date of Patent: March 7, 2017Assignee: PRATT & WHITNEY CANADA CORP.Inventors: George Guglielmin, Joe Lanzino, Enzo Macchia, Barry Barnett, Andreas Eleftheriou, Thomas McDonough
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Publication number: 20160348694Abstract: A stator airfoil of a gas turbine engine according to one embodiment includes at least two winglets projecting transversely from opposed sides of a stator airfoil, respectively. Each winglet includes a leading edge axially and outwardly extending from one of the opposed sides of the stator airfoil and a trailing edge extending from the stator airfoil to join with the leading edge of the winglet. The winglets therefore provide a wide trailing edge thereof to aerodynamically manage boundary layers and micro-shocks of a working fluid.Type: ApplicationFiled: May 26, 2015Publication date: December 1, 2016Inventors: Enzo MACCHIA, George GUGLIELMIN, Bhawan PATEL, Joe LANZINO
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Publication number: 20160258443Abstract: A fan blade of a gas turbine engine is disclosed which is composed of an airfoil having a leading edge and a trailing edge, and a root with a platform and a blade fixing for engaging a fan hub. The fan blade is composed of a core substrate selected from the group consisting of composites and polymers, and an entirety of the airfoil and the root of the fan blade has a nanocrystalline metal outer layer thereon which forms an outer surface fully enveloping the fan blade. The nanocrystalline metal layer formed of a nanocrystalline metal coating has an average grain size of between 10 nm and 500 nm, and the nanocrystalline metal outer layer forms a structural element of the fan blade.Type: ApplicationFiled: May 16, 2016Publication date: September 8, 2016Inventors: George GUGLIELMIN, Joe LANZINO, Enzo MACCHIA, Barry BARNETT, Andreas ELEFTHERIOU, Thomas MCDONOUGH
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Patent number: 9429029Abstract: An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.Type: GrantFiled: July 22, 2011Date of Patent: August 30, 2016Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Enzo Macchia, Barry Barnett, Andreas Eleftheriou, Tom McDonough, George Guglielmin, Joe Lanzino
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Publication number: 20160153290Abstract: A method of protecting a blade of a gas turbine engine by applying a nanocrystalline metal coating to a portion of the blade root is disclosed, which includes preparing at least a portion of a dovetail of the blade root for coating; and then applying a nanocrystalline metal coating to said portion.Type: ApplicationFiled: October 31, 2014Publication date: June 2, 2016Inventors: Enzo MACCHIA, Barry BARNETT, Andreas ELEFTHERIOU, Tom McDONOUGH, George GUGLIELMIN, Joe LANZINO
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Publication number: 20140238038Abstract: A laser ignition system for a gas turbine engine includes a combustion chamber. The system comprises a laser source for generating a continuous laser beam during an ignition process of the combustion chamber; and a dynamic laser focus apparatus positioned outside of the combustion chamber and focusing the laser beam into a continuously varying focal point to generate a laser kernel moving within a spray of air/fuel mixture injected into the combustion chamber.Type: ApplicationFiled: February 22, 2013Publication date: August 28, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Enzo MACCHIA, George GUGLIELMIN, Joe LANZINO, Bhawan PATEL
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Publication number: 20130255277Abstract: A nose cone for a turbofan gas turbine engine includes a central tip, an outer perimeter and a substantially conical outer wall extending therebetween which encloses a cavity therewithin. The outer wall includes an inner substrate layer facing the cavity and an outer layer which overlies and at least partially encloses the inner substrate layer. The outer layer is composed entirely of a nanocrystalline metal forming an outer surface of the nose cone.Type: ApplicationFiled: March 30, 2012Publication date: October 3, 2013Inventors: Enzo Macchia, Andreas Eleftheriou, Thomas Peter McDonough, George Guglielmin, Joe Lanzino, Barry Barnett
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Publication number: 20120082556Abstract: An airfoil for a gas turbine engine comprising a root, a tip, and leading and trailing edges extending between the root and the tip. The airfoil has a non-metallic core which is composed of a composite material, and a metallic coating disposed on at least a portion of the composite core, such as along the leading edge of the airfoil for example. The metallic coating is composed of a nanocrystalline metal, and forms an outer surface of the portion of the airfoil onto which the coating is applied.Type: ApplicationFiled: July 22, 2011Publication date: April 5, 2012Inventors: Enzo Macchia, Andreas Eleftheriou, George Guglielmin, Barry Bamett, Joe Lanzino, Thomas McDonough
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Publication number: 20120082551Abstract: An airfoil blade of a gas turbine engine includes a root configured for mating attachment with a cooperating rotor hub and an airfoil extending away from the root. The root is composed of a first metal and has a nanocrystalline metal coating, composed of a second metal, over at least a portion thereof. A method of protecting such a blade by applying a nanocrystalline metal coating to a portion of the blade root is also disclosed.Type: ApplicationFiled: July 22, 2011Publication date: April 5, 2012Inventors: Enzo Macchia, Barry Barnett, Andreas Eleftheriou, Tom McDonough, George Guglielmin, Joe Lanzino
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Publication number: 20120082541Abstract: An engine casing for a gas turbine engine, such as, but not limited to, a gas turbine engine fan case, is disclosed which includes an annular case shell formed of a substrate material that is at least partially coated by a nanocrystalline metal coating. A method of manufacturing such an engine casing is also provided. The present engine casing provides improved containment capability in the event of a blade release or other failure during operation of the engine.Type: ApplicationFiled: July 22, 2011Publication date: April 5, 2012Inventors: Enzo Macchia, Barry Barnett, Andreas Eleftheriou, Tom McDonough, George Guglielmin, Joe Lanzino
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Publication number: 20120082553Abstract: A hybrid vane airfoil for a gas turbine engine, such as a vane of a compressor stator, is disclosed which includes a non-metallic core, and an outer metallic shell at least partially covering the non-metallic core and which defines an outer surface of the airfoil. The non-metallic core is composed for example of a polymer, and the metallic outer shell is composed of a nanocrystalline metallic coating.Type: ApplicationFiled: July 22, 2011Publication date: April 5, 2012Inventors: Andreas Eleftheriou, Barry Barnett, Joe Lanzino, Tom McDonough, George Guglelmin, Enzo Macchia, Melinda Bissinger
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Publication number: 20120082559Abstract: A fan blade of a gas turbine engine, and a method of producing same, is disclosed which is composed of a core substrate and a nanocrystalline metal coating provided on at least a portion of the airfoil of the fan blade. The method includes the steps of providing a fan blade core having an airfoil and then applying a nanocrystalline metal coating over at least a portion of the fan blade core.Type: ApplicationFiled: July 22, 2011Publication date: April 5, 2012Inventors: George Guglielmin, Joe Lanzino, Enzo Macchia, Barry Barnett, Andreas Eleftheriou, Thomas McDonough