Patents by Inventor Joseph Zelina
Joseph Zelina 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).
-
Patent number: 11970994Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.Type: GrantFiled: October 24, 2022Date of Patent: April 30, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Patent number: 11970993Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.Type: GrantFiled: September 27, 2022Date of Patent: April 30, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Publication number: 20240133556Abstract: A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.Type: ApplicationFiled: May 8, 2023Publication date: April 25, 2024Inventors: Ravindra Shankar Ganiger, Hiranya Nath, Michael A. Benjamin, Daniel D. Brown, Sibtosh Pal, Joseph Zelina
-
Patent number: 11959441Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.Type: GrantFiled: October 24, 2022Date of Patent: April 16, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Patent number: 11906168Abstract: A combustor assembly is generally provided. The combustor assembly includes a volute wall extended annularly around a combustor centerline. The volute wall is extended at least partially as a spiral curve from a circumferential reference line around the combustor centerline. The volute wall defines a combustion chamber therewithin. An annular inner wall is extended at least partially along a lengthwise direction from the volute wall. An annular outer wall is extended at least partially along the lengthwise direction from the volute wall. The inner wall and the outer wall are each separated along a radial direction from the combustor centerline. A primary flow passage is defined between the inner wall and the outer wall in fluid communication from the combustion chamber.Type: GrantFiled: March 10, 2021Date of Patent: February 20, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Pradeep Naik, Joseph Zelina, Clayton Stuart Cooper
-
Publication number: 20240053013Abstract: A combustor for a turbine engine. The combustor includes a fuel injector and a fluid injection system in fluid communication with the combustor. The fuel injector includes a mixer assembly with a pilot mixer and a main mixer. The pilot mixer and the main mixer operate during high power operation of the turbine engine. The fluid injection system injects a fluid into the combustor during high power operation of the turbine engine. The fluid is shut off during low power operation of the turbine engine and during mid-level power operation of the turbine engine.Type: ApplicationFiled: August 12, 2022Publication date: February 15, 2024Inventors: Joseph Zelina, Shai Birmaher, Sibtosh Pal, Clayton S. Cooper
-
Patent number: 11885498Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.Type: GrantFiled: January 31, 2022Date of Patent: January 30, 2024Assignee: General Electric CompanyInventors: Narendra D. Joshi, Lawrence B. Kool, Joseph Zelina
-
Publication number: 20230408098Abstract: A combustor for a gas turbine includes a combustor liner having an outer liner and an inner liner defining a combustion chamber therebetween. At least one of the outer liner and the inner liner includes a dilution fence arranged in a dilution zone of the combustion chamber. The dilution fence extends into the combustion chamber and has at least one secondary fuel nozzle opening therethrough, and at least one secondary fuel nozzle is arranged through the at least one secondary fuel nozzle opening.Type: ApplicationFiled: May 25, 2022Publication date: December 21, 2023Inventors: Saket Singh, Rimple Rangrej, Pradeep Naik, Michael A. Benjamin, Joseph Zelina
-
Patent number: 11774103Abstract: A Brayton cycle engine including an inner wall assembly defining a detonation combustion region upstream thereof extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath. A method for operating the engine includes flowing an oxidizer through the gas flowpath; capturing a portion of the flow of oxidizer via the inner wall; flowing a first flow of fuel to the captured flow of oxidizer; producing a rotating detonation gases via a mixture of the first flow of fuel and the captured flow of oxidizer; flowing at least a portion of the detonation gases downstream to mix with the flow of oxidizer; flowing a second flow of fuel to the mixture of detonation gases and oxidizer; and burning the mixture of the second flow of fuel and the detonation gases/oxidizer mixture.Type: GrantFiled: April 11, 2022Date of Patent: October 3, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Publication number: 20230243505Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a fuel system fluidly coupled to the combustion section, the fuel system comprising a fuel supply, a primary fuel line fluidly coupling the fuel supply to the combustion section, and a reformer fluidly coupled to the fuel supply.Type: ApplicationFiled: January 31, 2022Publication date: August 3, 2023Inventors: Narendra D. Joshi, Lawrence B. Kool, Joseph Zelina
-
Publication number: 20230213193Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.Type: ApplicationFiled: October 24, 2022Publication date: July 6, 2023Inventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Publication number: 20230213192Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.Type: ApplicationFiled: October 24, 2022Publication date: July 6, 2023Inventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Publication number: 20230204213Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: ApplicationFiled: March 10, 2022Publication date: June 29, 2023Inventors: Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, Ajoy Patra, Manampathy G. Giridharan, Steven C. Vise, Michael A. Benjamin, Sripathi Mohan, R Narasimha Chiranthan, Joseph Zelina
-
Patent number: 11674476Abstract: The present disclosure is directed to a rotating detonation combustion system for a propulsion system including a plurality of combustors in adjacent arrangement along the circumferential direction. Each combustor defines a combustor centerline extended through each combustor, and each combustor comprises an outer wall defining a combustion chamber and a combustion inlet. Each combustion chamber is defined by an annular gap and a combustion chamber length together defining a volume of each combustion chamber. Each combustor defines a plurality of nozzle assemblies each disposed at the combustion inlet in adjacent arrangement around each combustor centerline. Each nozzle assembly defines a nozzle wall extended along a lengthwise direction, a nozzle inlet, a nozzle outlet, and a throat therebetween, and each nozzle assembly defines a converging-diverging nozzle. A first array of combustors defines a first volume and a second array of combustors defines a second volume different from the first volume.Type: GrantFiled: June 9, 2017Date of Patent: June 13, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Steven Clayton Vise, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Sibtosh Pal
-
Patent number: 11578869Abstract: A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.Type: GrantFiled: May 20, 2021Date of Patent: February 14, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Joseph Zelina, Clayton S. Cooper, Michael T. Bucaro, Steven C. Vise, John Thomas Herbon
-
Patent number: 11578871Abstract: A gas turbine engine with a compressor section, a turbine section, and a combustion section located downstream from the compressor section and upstream from the turbine section, the combustion section including: a dome inlet, a combustor outlet fluidly coupled to the turbine section, a liner and a dome assembly together at least partially defining a combustion chamber extending between the dome inlet and the combustor outlet, a primary fuel injector fluidly coupled to the dome inlet, and a second fuel injector fluidly coupled to the combustion chamber.Type: GrantFiled: January 28, 2022Date of Patent: February 14, 2023Assignee: General Electric CompanyInventors: Narendra D. Joshi, Joseph Zelina
-
Publication number: 20230020803Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.Type: ApplicationFiled: September 27, 2022Publication date: January 19, 2023Inventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Publication number: 20220373181Abstract: A combustor for a turbine engine is provided, the combustor includes an outer liner, an inner liner and a dome that together define a combustion chamber; a diffuser positioned upstream of the combustion chamber, the diffuser being configured to receive air flow from a compressor section and to provide a flow of compressed air to the combustion chamber; and an outer cowl and an inner cowl located upstream of the combustion chamber, the outer cowl and the inner cowl being configured to direct a portion of air flow from the diffuser to the combustion chamber. The diffuser is configured to output air flow having an amount of air pressure maximized at a center of the air flow so as to optimize total air pressure fed to the combustion chamber through the dome.Type: ApplicationFiled: May 20, 2021Publication date: November 24, 2022Inventors: Joseph Zelina, Clayton S. Cooper, Michael T. Bucaro, Steven C. Vise, John Thomas Herbon
-
Patent number: 11486579Abstract: A Brayton cycle engine including a longitudinal wall extended along a lengthwise direction. The longitudinal wall defines a gas flowpath of the engine. An inner wall assembly is extended from the longitudinal wall into the gas flowpath. The inner wall assembly defines a detonation combustion region in the gas flowpath upstream of the inner wall assembly.Type: GrantFiled: February 26, 2018Date of Patent: November 1, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina
-
Patent number: 11473780Abstract: A Brayton cycle engine and method for operation. The engine includes an inner wall assembly and an upstream wall assembly each extended from a longitudinal wall into a gas flowpath. An actuator adjusts a depth of the detonation combustion region into the gas flowpath between the inner wall assembly and the upstream wall assembly. The engine flows an oxidizer through the gas flowpath and the inner wall captures a portion of the oxidizer. The engine further adjusts the captured flow of oxidizer via the upstream wall and flows a first flow of fuel to the captured flow of oxidizer to produce rotating detonation gases. The engine flows the detonation gases downstream and to mix with the flow of oxidizer, and flows and burns a second flow of fuel to the detonation gases/oxidizer mixture to produce thrust.Type: GrantFiled: February 26, 2018Date of Patent: October 18, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Sibtosh Pal, Steven Clayton Vise, Arthur Wesley Johnson, Clayton Stuart Cooper, Joseph Zelina