Patents by Inventor Steven C. Fisher
Steven C. Fisher 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: 11944130Abstract: A vaporizer device includes various modular components. The vaporizer device includes a first subassembly. The first subassembly includes a cartridge connector that secures a vaporizer cartridge to the vaporizer device and includes at least two receptacle contacts that electrically communicate with the vaporizer cartridge. The vaporizer device includes a second subassembly. The second subassembly includes a skeleton defining a rigid tray that retains at least a power source. The vaporizer device also includes a third subassembly. The third subassembly includes a plurality of charging contacts that supply power to the power source, and an end cap that encloses an end of the vaporizer device.Type: GrantFiled: December 24, 2020Date of Patent: April 2, 2024Assignee: JUUL Labs, Inc.Inventors: Samuel C. Anderson, Wei-Ling Chang, Brandon Cheung, Steven Christensen, Joseph Chun, Joseph R. Fisher, Jr., Nicholas J. Hatton, Kevin Lomeli, James Monsees, Andrew L. Murphy, Claire O'Malley, John R. Pelochino, Hugh Pham, Vipul V. Rahane, Matthew J. Taschner, Val Valentine, Kenneth Wong
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Patent number: 8731745Abstract: A method of generating a test sequence diagram includes: linking a first action of the plurality of actions with a second action of the plurality of actions and generating a test sequence diagram which maintains the linking.Type: GrantFiled: July 1, 2008Date of Patent: May 20, 2014Assignee: Aerojet Rocketdyne of DE, Inc.Inventors: Steven C. Fisher, Tim Brodeur
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Patent number: 8141339Abstract: There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxidizer to the oxidizer manifolds is controlled by an oxidizer valve, which may comprise an integral valve. The oxidizer passes from the oxidizer manifolds into the oxidizer element and then into the combustion chamber. The multiple oxidizer manifolds allow the oxidizer to be provided through selective openings of the oxidizer element thus reducing the change in pressure drop across the oxidizer element to thereby reduce or eliminate combustion instability and other problems. Additionally, the injector assembly may also include a lift-off seal or a filler fluid source to fill any temporarily unused oxidizer manifolds with an oxidizer or filler fluid.Type: GrantFiled: November 6, 2009Date of Patent: March 27, 2012Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: James J. Fang, Steven C. Fisher, Robert J. Jensen
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Patent number: 8122703Abstract: A bi-propellant injector includes first and second injector elements and a spark exciter assembly. The first injector element has a conductive layer electrically connected to the spark exciter assembly and a nonconductive layer disposed on an exterior portion of the conductive layer. The second injector element comprises a conductive material and has an opening therethrough in fluid communication with a combustion chamber. An end of the first injector element is positioned at or near the opening in the second injector element. The spark exciter assembly can generate an electrical arc between the conductive layer of the first injector element and the second injector element.Type: GrantFiled: April 28, 2006Date of Patent: February 28, 2012Assignee: United Technologies CorporationInventor: Steven C. Fisher
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Publication number: 20100043391Abstract: There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxidizer to the oxidizer manifolds is controlled by an oxidizer valve, which may comprise an integral valve. The oxidizer passes from the oxidizer manifolds into the oxidizer element and then into the combustion chamber. The multiple oxidizer manifolds allow the oxidizer to be provided through selective openings of the oxidizer element thus reducing the change in pressure drop across the oxidizer element to thereby reduce or eliminate combustion instability and other problems. Additionally, the injector assembly may also include a lift-off seal or a filler fluid source to fill any temporarily unused oxidizer manifolds with an oxidizer or filler fluid.Type: ApplicationFiled: November 6, 2009Publication date: February 25, 2010Inventors: James J. Fang, Steven C. Fisher, Robert J. Jensen
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Publication number: 20100017055Abstract: A method of generating a test sequence diagram includes: linking a first action of the plurality of actions with a second action of the plurality of actions and generating a test sequence diagram which maintains the linking.Type: ApplicationFiled: July 1, 2008Publication date: January 21, 2010Inventors: Steven C. Fisher, Tim Brodeur
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Patent number: 7640726Abstract: There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxidizer to the oxidizer manifolds is controlled by an oxidizer valve, which may comprise an integral valve. The oxidizer passes from the oxidizer manifolds into the oxidizer element and then into the combustion chamber. The multiple oxidizer manifolds allow the oxidizer to be provided through selective openings of the oxidizer element thus reducing the change in pressure drop across the oxidizer element to thereby reduce or eliminate combustion instability and other problems. Additionally, the injector assembly may also include a lift-off seal or a filler fluid source to fill any temporarily unused oxidizer manifolds with an oxidizer or filler fluid.Type: GrantFiled: September 28, 2005Date of Patent: January 5, 2010Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: James J. Fang, Steven C. Fisher, Robert J. Jensen
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Publication number: 20090320447Abstract: A bi-propellant injector includes first and second injector elements and a spark exciter assembly. The first injector element has a conductive layer electrically connected to the spark exciter assembly and a nonconductive layer disposed on an exterior portion of the conductive layer. The second injector element comprises a conductive material and has an opening therethrough in fluid communication with a combustion chamber. An end of the first injector element is positioned at or near the opening in the second injector element. The spark exciter assembly can generate an electrical arc between the conductive layer of the first injector element and the second injector element.Type: ApplicationFiled: April 28, 2006Publication date: December 31, 2009Applicant: United Technologies CorporationInventor: Steven C. Fisher
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Publication number: 20080302335Abstract: There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxidizer to the oxidizer manifolds is controlled by an oxidizer valve, which may comprise an integral valve. The oxidizer passes from the oxidizer manifolds into the oxidizer element and then into the combustion chamber. The multiple oxidizer manifolds allow the oxidizer to be provided through selective openings of the oxidizer element thus reducing the change in pressure drop across the oxidizer element to thereby reduce or eliminate combustion instability and other problems. Additionally, the injector assembly may also include a lift-off seal or a filler fluid source to fill any temporarily unused oxidizer manifolds with an oxidizer or filler fluid.Type: ApplicationFiled: September 28, 2005Publication date: December 11, 2008Inventors: James J. Fang, Steven C. Fisher, Robert J. Jensen
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Patent number: 6966769Abstract: A gaseous oxygen resonance igniter includes a body with a first inlet for gaseous oxygen incorporating a supersonic nozzle. An outlet from the body incorporates an orifice of predetermined size to maintain a desired pressure in the body. An aperture in the body opposite the first inlet provides a port to a ceramic resonance cavity. A ceramic bleed disc is engaged at a second end of the resonance cavity. An end cap incorporates a plenum adapted to receive high temperature oxygen flow from the resonance cavity through the bleed disc. An exhaust port is connected to the plenum for the high temperature oxygen which flows to a mixing chamber which introduces pilot fuel for ignition as a combustion initiation torch.Type: GrantFiled: April 5, 2004Date of Patent: November 22, 2005Assignee: The Boeing CompanyInventors: Joshua E. Elvander, Steven C. Fisher, Shinjiro Miyata
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Patent number: 6918243Abstract: A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-holding zone igniter (74) is adjacent to and ignites recirculation of at least a portion of the first propellant (69) and at least a portion of the second propellant (71) within a flame-holding zone (76).Type: GrantFiled: May 19, 2003Date of Patent: July 19, 2005Assignee: The Boeing CompanyInventor: Steven C. Fisher
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Publication number: 20040231318Abstract: A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-holding zone igniter (74) is adjacent to and ignites recirculation of at least a portion of the first propellant (69) and at least a portion of the second propellant (71) within a flame-holding zone (76).Type: ApplicationFiled: May 19, 2003Publication date: November 25, 2004Inventor: Steven C. Fisher
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Patent number: 6688100Abstract: A combustion apparatus including a structural jacket, a forward liner, and an aft liner, and an associated method of constructing the same are provided. The structural jacket defines a passage including a first end, a second end, and a neck. The neck is positioned between and separates the first and second ends of the passage. The forward liner is positioned within the first end of the passage and has a throat fitted within the neck of the passage. The aft liner is positioned within the second end of the passage and has an upstream potion abutting the throat of the forward liner. The forward and aft liners are brazed together, and are bonded to the passage of the structural jacket, to form a longitudinal combustion chamber so that combustion of the propellant is contained and directed through the combustion chamber from the forward liner to the aft liner.Type: GrantFiled: July 16, 2002Date of Patent: February 10, 2004Assignee: The Boeing CompanyInventors: Brian Leigh Wherley, Steven C. Fisher, Amardeep Litt
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Publication number: 20040011023Abstract: A combustion apparatus including a structural jacket, a forward liner, and an aft liner, and an associated method of constructing the same are provided. The structural jacket defines a passage including a first end, a second end, and a neck. The neck is positioned between and separates the first and second ends of the passage. The forward liner is positioned within the first end of the passage and has a throat fitted within the neck of the passage. The aft liner is positioned within the second end of the passage and has an upstream potion abutting the throat of the forward liner. The forward and aft liners are brazed together, and are bonded to the passage of the structural jacket, to form a longitudinal combustion chamber so that combustion of the propellant is contained and directed through the combustion chamber from the forward liner to the aft liner.Type: ApplicationFiled: July 16, 2002Publication date: January 22, 2004Applicant: The Boeing CompanyInventors: Brian Leigh Wherley, Steven C. Fisher, Amardeep Litt
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Patent number: 6253539Abstract: A method for using an injector to combust a first fluid and a second fluid comprises a directing the first fluid step and a shrouding step. The directing step comprises directing the first fluid in a central coaxial flow generally perpendicularly through a first fluid passage that extends through an injector faceplate, and into a combustion chamber. In the shrouding step, a length of the central coaxial flow adjacent to the injector faceplate is shrouded with an outer coaxial flow. The shroud is formed by directing a portion of the second fluid through an annular/conical passage in the injector faceplate that surrounds the first fluid passage. The annular/conical passage is arranged such that the outer coaxial flow is directed radially inward and impinges on the central coaxial flow a distance after the central coaxial flow has exited the first fluid passage and after the outer coaxial flow has exited the annular/conical passage.Type: GrantFiled: July 7, 1999Date of Patent: July 3, 2001Assignee: Boeing North America Inc.Inventors: Shahram Farhangi, James M. McKinnon, Steven C. Fisher, James J. Fang
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Patent number: 5701670Abstract: A method of fabricating a rocket engine combustion chamber comprising assembling a liner having cooling channels, a plurality of throat support sections, and a structural jacket having inlet and outlet manifolds. Then heating the assembly in a pressurized furnace to bond the assembled parts to each other.Type: GrantFiled: June 23, 1994Date of Patent: December 30, 1997Assignee: Boeing North American, Inc.Inventors: Steven C. Fisher, Theodore C. Adams, Maynard L. Stangeland, Jacob Rietdyk, Paul R. Winans