Patents by Inventor Owen James Sullivan Rickey
Owen James Sullivan Rickey 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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Publication number: 20240162458Abstract: A combustion section includes a casing that defines a diffusion chamber. The combustion section further includes a combustion liner that is disposed within the diffusion chamber and that defines a combustion chamber. The combustion liner is spaced apart from the casing such that a passageway is defined between the combustion liner and the casing. The combustion section further includes a fuel cell assembly that is disposed in the passageway. The fuel cell assembly includes a fuel cell stack having a plurality of fuel cells. The plurality of fuel cells extend from an inlet end in fluid communication with the diffusion chamber to an outlet end extending through the combustion liner and in fluid communication with the combustion chamber.Type: ApplicationFiled: November 10, 2022Publication date: May 16, 2024Inventors: Seung-Hyuck Hong, Richard L. Hart, Honggang Wang, Anil Raj Duggal, Michael Anthony Benjamin, Owen James Sullivan Rickey, Narendra Digamber Joshi, Hendrik Pieter Jacobus de Bock
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Patent number: 11378277Abstract: A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.Type: GrantFiled: May 23, 2018Date of Patent: July 5, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Narendra Digamber Joshi, Shawn David Wehe, ShihYang Hsieh, Changjin Yoon, Owen James Sullivan Rickey, Joseph Douglas Monty
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Publication number: 20210190320Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.Type: ApplicationFiled: March 8, 2021Publication date: June 24, 2021Inventors: Owen James Sullivan Rickey, Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Shashank Yellapantula
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Patent number: 10969107Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.Type: GrantFiled: September 15, 2017Date of Patent: April 6, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Owen James Sullivan Rickey, Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Shashank Yellapantula
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Patent number: 10767866Abstract: A micromixer of a gas turbine has a plurality of tubes each having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor. At least some of the tubes have a liquid fuel injector, and the liquid fuel injector projects into one of the tubes. The liquid fuel injector has a ramped upstream surface and two converging side surfaces. The ramped upstream surface compresses the flow passing thereover, and a top surface of the liquid fuel injector comprises a liquid fuel outlet.Type: GrantFiled: July 11, 2018Date of Patent: September 8, 2020Assignee: General Electric CompanyInventors: Owen James Sullivan Rickey, Joel Meier Haynes, Su Cao, Shih-Yang Hsieh
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Patent number: 10724741Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.Type: GrantFiled: May 10, 2016Date of Patent: July 28, 2020Assignee: General Electric CompanyInventors: Shashank Yellapantula, Anthony John Dean, Narendra Digamber Joshi, Mehmet Muhittin Dede, Jin Yan, Owen James Sullivan Rickey
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Publication number: 20200018484Abstract: A micromixer of a gas turbine has a plurality of tubes each having an inlet and an outlet for receiving a flow and dispersing the flow to a combustor. At least some of the tubes have a liquid fuel injector, and the liquid fuel injector projects into one of the tubes. The liquid fuel injector has a ramped upstream surface and two converging side surfaces. The ramped upstream surface compresses the flow passing thereover, and a top surface of the liquid fuel injector comprises a liquid fuel outlet.Type: ApplicationFiled: July 11, 2018Publication date: January 16, 2020Applicant: General Electric CompanyInventors: Owen James Sullivan Rickey, Joel Meier Haynes, Su Cao, Shih-Yang Hsieh
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Publication number: 20190368738Abstract: A liquid fuel injection assembly for a gas turbine engine is provided. The liquid fuel injection assembly includes at least one micromixer, at least one liquid fuel injection nozzle, and at least one post. The at least one micromixer includes at least one wall defining a conduit. The at least one liquid fuel injection nozzle extends from the at least one wall into the conduit. The at least one liquid fuel injection nozzle has a first drag coefficient. The at least one liquid fuel injection nozzle is configured to inject a flow of liquid fuel into the flow of air. The at least one post extends from the at least one wall and circumscribes the at least one liquid fuel injection nozzle. The liquid fuel injection nozzle and post have a second drag coefficient. The first drag coefficient is greater than the second drag coefficient.Type: ApplicationFiled: June 1, 2018Publication date: December 5, 2019Inventors: Owen James Sullivan Rickey, Joel Meier Haynes, Shih-Yang Hsieh, Su Cao, Seung-Hyuck Hong
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Publication number: 20190309951Abstract: A combustor includes a circumferential main combustion chamber and a plurality of air inlets, the plurality of air inlets dispersing air into the circumferential main combustion chamber. The combustor also includes at least one swirl-stabilized pilot burner, which disperses combustion gases into the circumferential main combustion chamber. The air inlets and the swirl-stabilized pilot burner are aligned at least partially in a radial direction and at least partially in a circumferential direction.Type: ApplicationFiled: May 23, 2018Publication date: October 10, 2019Applicant: General Electric CompanyInventors: Narendra Digamber Joshi, Shawn David Wehe, ShihYang Hsieh, Changjin Yoon, Owen James Sullivan Rickey, Joseph Douglas Monty
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Patent number: 10352570Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.Type: GrantFiled: March 31, 2016Date of Patent: July 16, 2019Assignee: General Electric CompanyInventors: Krishnakumar Venkatesan, Michael Anthony Benjamin, Shih-Yang Hsieh, Yuxin Zhang, Owen James Sullivan Rickey, Nayan Vinodbhai Patel, Duane Douglas Thomsen, Kevin Vandevoorde
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Publication number: 20190086091Abstract: A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.Type: ApplicationFiled: September 15, 2017Publication date: March 21, 2019Inventors: Owen James Sullivan Rickey, Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Shashank Yellapantula
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Publication number: 20170328569Abstract: A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.Type: ApplicationFiled: May 10, 2016Publication date: November 16, 2017Inventors: Shashank Yellapantula, Anthony John Dean, Narendra Digamber Joshi, Mehmet Muhittin Dede, Jin Yan, Owen James Sullivan Rickey
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Publication number: 20170284678Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.Type: ApplicationFiled: March 31, 2016Publication date: October 5, 2017Inventors: Krishnakumar Venkatesan, Michael Anthony Benjamin, Shih-Yang Hsieh, Yuxin Zhang, Owen James Sullivan Rickey, Nayan Vinodbhai Patel, Duane Douglas Thomsen, Kevin Vandevoorde