Patents by Inventor Timothy S. Snyder
Timothy S. Snyder 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: 11963691Abstract: A surgical instrument, has an end effector that includes an ultrasonic blade, and a clamp arm that moves relative to the ultrasonic blade from an opened position toward an intermediate position and a closed position. The clamp arm is offset from the ultrasonic blade to define a predetermined gap in the intermediate position between the opened position and the closed position. A clamp arm actuator connects to the clamp arm and moves from an opened configuration to a closed configuration to direct the clamp arm from the opened position toward the intermediate position and the closed position. A spacer connects with the clamp arm to inhibit movement of the clamp arm from the intermediate position toward the closed position for maintaining the predetermined gap between the clamp arm and the ultrasonic blade.Type: GrantFiled: December 21, 2020Date of Patent: April 23, 2024Assignee: Cilag GmbH InternationalInventors: Ryan M. Asher, Brian D. Black, John E. Brady, Joseph Dennis, Geni M. Giannotti, Bryce L. Heitman, Timothy S. Holland, Joseph E. Hollo, Andrew Kolpitcke, Amy M. Krumm, Jason R. Lesko, Matthew C. Miller, David A. Monroe, Ion V. Nicolaescu, Rafael J. Ruiz Ortiz, Matthew S. Schneider, Richard C. Smith, Shawn C. Snyder, Sarah A. Worthington, Monica L. Rivard, Fajian Zhang
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Patent number: 11959420Abstract: A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.Type: GrantFiled: January 8, 2020Date of Patent: April 16, 2024Assignee: RTX CORPORATIONInventor: Timothy S. Snyder
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Patent number: 11920525Abstract: Fuel injectors for gas turbine engines include an inner housing having a center body installed within the inner housing, an intermediate housing arranged radially outward from the inner housing, and an outer housing arranged radially outward from the intermediate housing. The center body is a hollow body structure defining a center body airflow passage therethrough, a first fluid passage is partially defined between an outer surface of the inner housing and an inner surface of the intermediate housing, a second fluid passage is partially defined within the intermediate housing, and a third fluid passage comprises the center body airflow passage, an inner airflow passage defined between an exterior surface of the center body and an interior surface of the inner housing, and an outer airflow passage that is defined by the outer housing and radially outward from the intermediate housing.Type: GrantFiled: August 5, 2022Date of Patent: March 5, 2024Assignee: RTX CORPORATIONInventor: Timothy S. Snyder
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Patent number: 11920524Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.Type: GrantFiled: April 15, 2021Date of Patent: March 5, 2024Assignee: RTX CORPORATIONInventors: Lance L. Smith, Timothy S. Snyder, Jeffrey M. Cohen, Peter Cocks, Sean C. Emerson
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Publication number: 20240044496Abstract: Fuel injectors for gas turbine engines include a housing and a tube defining a portion of a first fluid passage therein and a second fluid passage is defined between an exterior surface of the tube and an interior surface of the housing. An inner airflow tube is arranged having an inflow vane assembly and a central air passage. A portion of the first fluid passage extends axially at a position radially outward from the inner airflow tube, and the third fluid passage extends axially at a position radially outward from the first fluid passage. A nozzle outlet is configured to receive first, second, and thirds fluids from the respective fluid passages to cause mixing thereof. The inflow vane assembly comprises a number of vanes, with each vane angled relative to a nozzle axis at an angle between 20° and 40°.Type: ApplicationFiled: August 5, 2022Publication date: February 8, 2024Inventor: Timothy S. Snyder
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Publication number: 20240044494Abstract: An assembly is provided which includes a swirler and a fuel nozzle. The swirler includes an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is radially between the inner wall and the outer wall. The inner passage is radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle includes a plurality of fuel outlets and a plurality of air outlets. The fuel outlets are axially aligned with the inner wall. The air outlets are axially upstream of and radially outboard of the fuel outlets.Type: ApplicationFiled: August 4, 2023Publication date: February 8, 2024Inventors: Timothy S. Snyder, Baris A. Sen, Dennis M. Moura, Scott A. Liljenberg
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Publication number: 20240044495Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.Type: ApplicationFiled: May 15, 2023Publication date: February 8, 2024Inventors: Lawrence A. Binek, Timothy S. Snyder
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Publication number: 20240044293Abstract: Fuel injectors for gas turbine engines include an inner housing having a center body installed within the inner housing, an intermediate housing arranged radially outward from the inner housing, and an outer housing arranged radially outward from the intermediate housing. The center body is a hollow body structure defining a center body airflow passage therethrough, a first fluid passage is partially defined between an outer surface of the inner housing and an inner surface of the intermediate housing, a second fluid passage is partially defined within the intermediate housing, and a third fluid passage comprises the center body airflow passage, an inner airflow passage defined between an exterior surface of the center body and an interior surface of the inner housing, and an outer airflow passage that is defined by the outer housing and radially outward from the intermediate housing.Type: ApplicationFiled: August 5, 2022Publication date: February 8, 2024Inventor: Timothy S. Snyder
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Patent number: 11846421Abstract: A combustor for a gas turbine engine includes a combustor liner, a fuel swirler integral and conformal with the combustor liner to provide an outlet for fuel into the combustor, and a dilution chute surrounding the fuel swirler outlet and extending into the combustor to provide a wetting surface for fuel exiting the fuel swirler.Type: GrantFiled: February 14, 2020Date of Patent: December 19, 2023Assignee: RTX CORPORATIONInventors: Lawrence A. Binek, Timothy S. Snyder, Jesse R. Boyer
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Patent number: 11821368Abstract: A fuel delivery system for a combustor of a gas turbine engine including a primary fuel tank configured to store a primary fuel, a secondary fuel tank configured to store a secondary fuel, a swirler configured to produce a main flame within a combustion chamber of the combustor, and a fuel nozzle configured to produce a pilot flame within the combustion chamber of the combustor. The fuel nozzle includes a nozzle outlet that is located proximate to an end of the swirler or at the end of the swirler, the end of the swirler being located at an inlet of the combustor. The fuel delivery system also includes a primary fuel line fluidly connecting the primary fuel tank to the fuel nozzle and a secondary fuel line fluidly connecting the secondary fuel tank to the swirler.Type: GrantFiled: January 8, 2020Date of Patent: November 21, 2023Assignee: RTX CORPORATIONInventor: Timothy S. Snyder
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Patent number: 11808455Abstract: An assembly is provided for a gas turbine engine. This assembly includes a combustor and a fuel conduit. The combustor includes a combustor wall that forms a peripheral boundary of a combustion chamber within the combustor. The fuel conduit extends along and is formed integral with the combustor wall. The fuel conduit is disposed outside of the combustion chamber.Type: GrantFiled: November 24, 2021Date of Patent: November 7, 2023Assignee: RTX CORPORATIONInventors: Lawrence A. Binek, Timothy S. Snyder, Sean R. Jackson
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Patent number: 11754287Abstract: An apparatus is provided for a turbine engine. This apparatus includes a fuel conduit and a fuel nozzle. The fuel conduit includes a supply passage. The fuel nozzle includes a nozzle passage, an end wall and a nozzle orifice. The nozzle passage has a longitudinal centerline and extends longitudinally through the fuel nozzle along the longitudinal centerline from the end wall to the nozzle orifice. The nozzle passage is configured with a convergent portion and a throat portion. The nozzle passage converges radially inward towards the longitudinal centerline as the convergent portion extends longitudinally along the longitudinal centerline away from the end wall and towards the throat portion. The supply passage is fluidly coupled to the nozzle passage by a fuel aperture in the end wall. A centerline of the fuel aperture is angularly and laterally offset from the longitudinal centerline.Type: GrantFiled: September 11, 2020Date of Patent: September 12, 2023Assignee: Raytheon Technologies CorporationInventors: Lawrence A. Binek, Timothy S. Snyder
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Patent number: 11725818Abstract: A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. A hood chamber is separated from the combustion chamber by a bulkhead extending between the inner shell and the outer shell. The bulkhead includes at least one opening extending between the hood chamber and the combustion chamber. A fuel injector extends through the at least one opening. The fuel injector includes a primary fuel passage including a primary fuel outlet located within the combustion chamber. The fuel injector further includes a secondary fuel passage including a plurality of secondary fuel outlets located within the hood chamber.Type: GrantFiled: December 6, 2019Date of Patent: August 15, 2023Assignee: Raytheon Technologies CorporationInventor: Timothy S. Snyder
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Publication number: 20230228419Abstract: A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel.Type: ApplicationFiled: November 9, 2022Publication date: July 20, 2023Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Timothy S. Snyder, James B. Hoke
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Publication number: 20230160574Abstract: An assembly is provided for a gas turbine engine. This assembly includes a combustor and a fuel conduit. The combustor includes a combustor wall that forms a peripheral boundary of a combustion chamber within the combustor. The fuel conduit extends along and is formed integral with the combustor wall. The fuel conduit is disposed outside of the combustion chamber.Type: ApplicationFiled: November 24, 2021Publication date: May 25, 2023Inventors: Lawrence A. Binek, Timothy S. Snyder, Sean R. Jackson
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Patent number: 11649964Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a monolithic body. The monolithic body includes a splash plate and a fuel nozzle. The splash plate includes a splash plate surface. The fuel nozzle includes a nozzle orifice. The fuel nozzle is configured to direct fuel out of the nozzle orifice to impinge against the splash plate surface.Type: GrantFiled: December 1, 2020Date of Patent: May 16, 2023Assignee: Raytheon Technologies CorporationInventors: Lawrence A. Binek, Timothy S. Snyder
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Patent number: 11525577Abstract: A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel.Type: GrantFiled: April 27, 2020Date of Patent: December 13, 2022Assignee: Raytheon Technologies CorporationInventors: Timothy S. Snyder, James B. Hoke
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Patent number: 11506390Abstract: A method for operating a fuel injector of a gas turbine engine includes injecting a hydrogen-based primary fuel from a primary fuel passage of the fuel injector directly into a combustion chamber. The primary fuel passage includes a primary fuel outlet located within the combustion chamber. The method further includes injecting a second fuel, different than the hydrogen-based primary fuel, from a secondary fuel passage of the fuel injector into a hood chamber separated from the combustion chamber by a bulkhead. The secondary fuel passage includes a plurality of secondary fuel outlets located within the hood chamber.Type: GrantFiled: December 6, 2019Date of Patent: November 22, 2022Assignee: Raytheon Technologies CorporationInventor: Timothy S. Snyder
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Publication number: 20220333534Abstract: An assembly is provided for a turbine engine with a flowpath. This turbine engine assembly includes a fuel injection system. The fuel injection system includes a first fuel injector and a second fuel injector. The fuel injection system is configured to provide the first fuel injector with first fuel and provide the second fuel injector with second fuel. The first fuel may be or include ammonia. The second fuel is different than the first fuel. The second fuel may be or include hydrogen gas. The first fuel injector is configured to direct the first fuel into the flowpath for combustion. The second fuel injector is configured to direct the second fuel into the flowpath for combustion.Type: ApplicationFiled: April 15, 2021Publication date: October 20, 2022Inventors: Lance L. Smith, Timothy S. Snyder, Jeffrey M. Cohen, Peter Cocks, Sean C. Emerson
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Publication number: 20220316400Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a fuel nozzle. The fuel nozzle includes a nozzle passage and a nozzle orifice. The nozzle passage extends longitudinally along a centerline within the fuel nozzle to the nozzle orifice. The nozzle passage has a solid polygonal cross-sectional geometry at the nozzle orifice.Type: ApplicationFiled: April 2, 2021Publication date: October 6, 2022Inventors: Lawrence A. Binek, Sean R. Jackson, Timothy S. Snyder, Anthony Van, Randolph T. Lyda, Brandon P. Williams