Patents by Inventor Jeffry Fint
Jeffry Fint 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: 8127443Abstract: A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.Type: GrantFiled: November 16, 2008Date of Patent: March 6, 2012Assignee: United Technologies CorporationInventors: Jeffry A. Fint, Michael B. Hankins, Myron L. Jew, Donald G. Ulmer, Brian L. Wherley, William D. Romine, Frederick M. Kuck, Douglas S. Ades
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Patent number: 7596940Abstract: A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.Type: GrantFiled: March 22, 2005Date of Patent: October 6, 2009Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Jeffry A. Fint, Michael B. Hankins, Myron L. Jew, Donald G. Ulmer, Brian L. Wherley, William D. Romine, Frederick M. Kuck, Douglas S. Ades
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Publication number: 20090100678Abstract: A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.Type: ApplicationFiled: November 16, 2008Publication date: April 23, 2009Inventors: Jeffry A. Fint, Michael B. Hankins, Myron L. Jew, Donald G. Ulmer, Brian L. Wherley, William D. Romine, Frederick M. Kuck, Douglas S. Ades
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Patent number: 7306710Abstract: A tank is utilized for containing a plating solution. A rotatable support assembly rotatably supports a combustion chamber component relative to the tank for providing partial immersion of the combustion chamber component within the plating solution. An anode is positioned within the tank proximate a surface of the combustion chamber component to be electroplated. A current source is connected to the anode and in electrical contact with the combustion chamber component. When the combustion chamber component is rotated, the submerged portions are deposited with metal from the plating solution.Type: GrantFiled: November 8, 2002Date of Patent: December 11, 2007Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: Chad M. Schepel, Jeffry A. Fint, Steve J. Evans, Cecil E. Flowers
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Publication number: 20060213182Abstract: A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.Type: ApplicationFiled: March 22, 2005Publication date: September 28, 2006Applicant: THE BOEING COMPANYInventors: Jeffry Fint, Michael Hankins, Myron Jew, Donald Ulmer, Brian Wherley, William Romine, Frederick Kuck, Douglas Ades
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Publication number: 20050183562Abstract: A channel cutting tool may include an arbor that connects to a rotating spindle of a machining tool or a similar spinning part of a machining tool. Two slot cutting blades may be fixedly mounted to the arbor. An inner washer may be fixedly mounted on the arbor between the cutting blades and establish the blade spacing. An outer washer may be rotationally mounted to the inner washer with a smaller thickness to facilitate rotation relative to the two cutting blades. The arbor rotates about a longitudinal rotation axis, which may also the rotation axis for the cutting blades, the inner washer, and the outer washer. The outer washer functions as a depth-limiting safeguard for the channel cutting tool.Type: ApplicationFiled: February 25, 2004Publication date: August 25, 2005Applicant: THE BOEING COMPANYInventors: Anthony Morris, Michael Hankins, Frederick Kuck, Kenneth Smith, David Campbell, Douglas Coutts, Richard Folster, Jeffry Fint, Chad Schepel
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Patent number: 6829884Abstract: In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.Type: GrantFiled: November 19, 2002Date of Patent: December 14, 2004Assignee: The Boeing CompanyInventors: Jeffry A. Fint, Douglas S. Ades, Michael B. Hankins, Maynard L. Stangeland
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Publication number: 20040093852Abstract: In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.Type: ApplicationFiled: November 19, 2002Publication date: May 20, 2004Inventors: Jeffry A. Fint, Douglas S. Ades, Michael B. Hankins, Maynard L. Stangeland
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Publication number: 20040089554Abstract: A tank is utilized for containing a plating solution. A rotatable support assembly rotatably supports a combustion chamber component relative to the tank for providing partial immersion of the combustion chamber component within the plating solution. An anode is positioned within the tank proximate a surface of the combustion chamber component to be electroplated. A current source is connected to the anode and in electrical contact with the combustion chamber component. When the combustion chamber component is rotated, the submerged portions are deposited with metal from the plating solution.Type: ApplicationFiled: November 8, 2002Publication date: May 13, 2004Inventors: Chad M. Schepel, Jeffry A. Fint, Steve J. Evans, Cecil E. Flowers