Patents by Inventor Steven C. Vise
Steven C. Vise 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: 11906165Abstract: An engine can utilize a combustor to combust fuel to drive 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. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.Type: GrantFiled: April 11, 2022Date of Patent: February 20, 2024Assignee: General Electric CompanyInventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Publication number: 20230366550Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.Type: ApplicationFiled: July 20, 2023Publication date: November 16, 2023Inventors: Perumallu Vukanti, Varun S. Lakshmanan, Michael T. Bucaro, Pradeep Naik, Steven C. Vise, Michael A. Benjamin
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Publication number: 20230366551Abstract: An engine can utilize a combustor to combust fuel to drive 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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: ApplicationFiled: July 11, 2023Publication date: November 16, 2023Inventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
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Publication number: 20230358170Abstract: A diffuser for a combustor of a turbomachine engine. The diffuser includes a body having a first annular surface and a second annular surface that define a passage, the passage being configured to cause air to flow along the passage to a first component of the combustor. The first annular surface includes an opening that is configured to cause air to flow in a direction away from the passage to a second component of the combustor.Type: ApplicationFiled: May 9, 2022Publication date: November 9, 2023Inventors: Juntao Zhang, Nicholas R. Overman, Steven C. Vise, Andrew Wickersham, Michael A. Benjamin
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Publication number: 20230296250Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. A combustor in the combustion section can include a combustor liner at least partially defining a combustion chamber. The combustor liner can include at least one aperture fluidly coupled to the combustion chamber.Type: ApplicationFiled: May 10, 2022Publication date: September 21, 2023Inventors: Manampathy G. Giridharan, Michael T. Bucaro, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
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Patent number: 11747019Abstract: A combustor liner has an annular outer liner and an annular inner liner that define a combustion chamber therebetween, the combustion chamber having a dilution zone. The annular outer liner and the annular inner liner each has a converging-diverging section extending into the dilution zone of the combustion chamber that form a throat between them. Each of the converging-diverging sections includes at least one dilution opening defined through the respective converging-diverging section at the throat for providing a flow of an oxidizer through a respective liner to the dilution zone of the combustion chamber.Type: GrantFiled: September 2, 2022Date of Patent: September 5, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Hiranya Nath, Ravindra Shankar Ganiger, Michael A. Benjamin, Steven C. Vise, Perumallu Vukanti, Sripathi Mohan, Rimple Rangrej
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Patent number: 11747018Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.Type: GrantFiled: January 28, 2022Date of Patent: September 5, 2023Assignee: General Electric CompanyInventors: Perumallu Vukanti, Varun S. Lakshmanan, Michael T. Bucaro, Pradeep Naik, Steven C. Vise, Michael A. Benjamin
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Publication number: 20230266002Abstract: A swirler assembly includes a swirler having a primary swirler with a primary swirler venturi, a swirler ferrule plate connected upstream to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an annular pressure drop cavity with oxidizer inlet orifices in fluid communication with the swirler, and at least one outlet orifice in fluid communication with the primary swirler venturi. A second flow of oxidizer to the swirler incurs a first pressure drop, a third flow of the oxidizer from the swirler to the annular pressure drop cavity incurs a second pressure drop, and a fourth flow of the oxidizer from the annular pressure drop cavity to the primary swirler venturi incurs a third pressure drop.Type: ApplicationFiled: February 18, 2022Publication date: August 24, 2023Inventors: Pradeep Naik, Shai Birmaher, Kwanwoo Kim, Saket Singh, Perumallu Vukanti, Karthikeyan Sampath, Steven C. Vise, Nicholas R. Overman, Michael A. Benjamin
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Publication number: 20230266006Abstract: A swirler assembly includes a swirler having primary swirler with a primary swirler venturi, a swirler ferrule plate connected to the primary swirler, and a fuel nozzle disposed in the swirler ferrule plate. The swirler ferrule plate has an aft wall, an annular conical wall, and an annular cavity wall that together form an annular cavity. The annular cavity includes a plurality of inlet orifices, and at least one outlet orifice. A flow of oxidizer through the plurality of inlet orifices into the annular cavity incurs a first pressure drop from a first pressure of a pressure plenum to a second pressure lower than the first pressure, and a flow of the oxidizer from the annular cavity through the at least one outlet orifice into the primary swirler venturi incurs a second pressure drop from the second pressure to a third pressure lower than the second pressure.Type: ApplicationFiled: February 18, 2022Publication date: August 24, 2023Inventors: Pradeep Naik, Shai Birmaher, Kwanwoo Kim, Saket Singh, Perumallu Vukanti, Karthikeyan Sampath, Steven C. Vise, Nicholas R. Overman, Michael A. Benjamin
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Patent number: 11725819Abstract: An engine can utilize a combustor to combust fuel to drive 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, which can supply a primary fuel supply and a secondary fuel supply. Increasing efficiency and reducing emission require the use of alternative fuels, which combust at higher temperatures or burn at faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: GrantFiled: February 28, 2022Date of Patent: August 15, 2023Assignee: General Electric CompanyInventors: Perumallu Vukanti, Pradeep Naik, Clayton S. Cooper, Michael A. Benjamin, Michael T. Bucaro, Manampathy G. Giridharan, Steven C. Vise, Ajoy Patra, Saket Singh, R Narasimha Chiranthan
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Publication number: 20230243311Abstract: A fuel supply system for a combustion section of a turbine engine. The turbine engine including a heat source. The fuel supply system comprising a first fuel supply having a liquid fuel, a second fuel supply having a first gaseous fuel, and a heat exchanger fluidly coupled to the first fuel supply and the heat source. The heat exchanger producing a heat sufficient to change the liquid fuel to a second gaseous fuel that is the same type of fuel as the first gaseous fuel.Type: ApplicationFiled: February 1, 2022Publication date: August 3, 2023Inventors: David Justin Brady, Mirko Gernone, Michael A. Benjamin, Steven C. Vise
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Publication number: 20230220802Abstract: A turbine engine and method of operation with a combustor as shown and described. The turbine engine including a combustor comprising an annular array of rich cups and an annular array of lean cups. A method for controlling nitrogen oxides including injecting a fuel/air mixture from the lean cups and the rich cups.Type: ApplicationFiled: April 11, 2022Publication date: July 13, 2023Inventors: Michael T. Bucaro, Manampathy G. Giridharan, Pradeep Naik, Sripathi Mohan, Michael A. Benjamin, Steven C. Vise, Ajoy Patra, Perumallu Vukanti, R Narasimha Chiranthan
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Publication number: 20230212984Abstract: An engine can utilize a combustor to combust fuel to drive 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. Varying the geometry of the swirler can provide for improved supply of air, which can improve efficiency and flame control.Type: ApplicationFiled: March 11, 2022Publication date: July 6, 2023Inventors: Steven C. Vise, Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, Ajoy Patra, R Narasimha Chiranthan, Michael A. Benjamin, Manampathy G. Giridharan, Hiranya Kumar Nath
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Publication number: 20230213191Abstract: A gas turbine engine including a compressor section and a combustion section in serial flow arrangement along an engine centerline, the combustion section having a combustor liner, a dome wall coupled to the combustor liner, and a dome inlet located in the dome wall, a fuel injector fluidly coupled to the dome inlet, a combustion chamber fluidly coupled to the fuel injector and defined at least in part by the combustor liner and the dome wall, and at least one set of dilution openings located in the dome wall and fluidly coupled to the combustion chamber.Type: ApplicationFiled: January 28, 2022Publication date: July 6, 2023Inventors: Perumallu Vukanti, Varun S. Lakshmanan, Michael T. Bucaro, Pradeep Naik, Steven C. Vise, Michael A. Benjamin
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Publication number: 20230204215Abstract: An engine can utilize a combustor to combust fuel to drive 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. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.Type: ApplicationFiled: February 18, 2022Publication date: June 29, 2023Inventors: Pradeep Naik, Ajoy Patra, Michael T. Bucaro, Perumallu Vukanti, Steven C. Vise, Michael A. Benjamin, Manampathy G. Giridharan, Saket Singh, Clayton S. Cooper
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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
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Publication number: 20230194093Abstract: An engine can utilize a combustor to combust fuel to drive 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. The fuel nozzle can include both a primary and secondary fuel passage, and an additional air passage to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.Type: ApplicationFiled: April 11, 2022Publication date: June 22, 2023Inventors: Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Manampathy G. Giridharan, Krishnakumar Venkatesan
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Publication number: 20230194095Abstract: An engine can utilize a combustor to combust fuel to drive 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 emission needs require the use of alternative fuels, which combust at higher temperatures and faster burn speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: ApplicationFiled: March 22, 2022Publication date: June 22, 2023Inventors: Perumallu Vukanti, Pradeep Naik, Michael T. Bucaro, Ajoy Patra, Manampathy G. Giridharan, Steven C. Vise, R Narasimha Chiranthan, Michael A. Benjamin, Clayton S. Cooper
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Publication number: 20230194092Abstract: An engine can utilize a combustor to combust fuel to drive 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 meeting emission needs can be met with the use of alternative fuels, which combust at higher temperatures or higher speeds than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.Type: ApplicationFiled: February 28, 2022Publication date: June 22, 2023Inventors: Pradeep Naik, Perumallu Vukanti, Michael T. Bucaro, Steven C. Vise, Ajoy Patra, R Narasimha Chiranthan, Manampathy G. Giridharan, Michael A. Benjamin, Clayton S. Cooper, Dharmaraj Pachaiappan
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Publication number: 20230194088Abstract: A turbine engine and method for controlling nitrogen oxides present within a combustor of the turbine engine. The turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement along an engine centerline. The combustion section having a combustor liner having a first end, a second end, opposing the first end, and at least partially defining a combustion chamber extending between the first and second ends. A dome assembly is mounted to the combustor liner at the first end and defines a dome inlet of the combustion chamber. There are multiple sets of dilution holes including a first set of dilution holes provided in the combustor liner downstream from the dome inlet and a second set of dilution holes provided in the combustor liner between the first set of dilution holes and the dome inlet.Type: ApplicationFiled: March 4, 2022Publication date: June 22, 2023Inventors: Manampathy G. Giridharan, Clayton S. Cooper, Michael A. Benjamin, Steven C. Vise, Michael T. Bucaro, Ajoy Patra, Pradeep Naik, Perumallu Vukanti, R Narasimha Chiranthan