Patents by Inventor Venkat Eswarlu Tangirala
Venkat Eswarlu Tangirala 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: 11898757Abstract: A propulsion system includes at least one rotating detonation actuator comprising: a flow path extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the flow path; an outer wall defining a radially outer boundary of the flow path; and at least one aircraft wing. The rotating detonation actuator is disposed in the aircraft wing. At least one rotating detonation wave travels through the flow path from the inlet end to the outlet end.Type: GrantFiled: August 3, 2021Date of Patent: February 13, 2024Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Patent number: 11572840Abstract: A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.Type: GrantFiled: December 3, 2019Date of Patent: February 7, 2023Assignee: GENERAL ELECTRIC COMPANYInventors: Joel Meier Haynes, Sarah Marie Monahan, Thomas Michael Lavertu, Venkat Eswarlu Tangirala, Kapil Kumar Singh
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Patent number: 11536456Abstract: A fuel and air injection handling system for a rotating detonation engine is provided. The system includes a compressor configured to compress air received via a compressor inlet and configured to output the air that is compressed as swirling, compressed air through a compressor outlet. The system also includes an annular rotating detonation combustor fluidly coupled with the compressor outlet. The annular rotating detonation combustor has a detonation cavity that extends around an annular axis, the annular rotating detonation combustor configured to combust the compressed air from the compressor in detonations that rotate within the detonation cavity around the annular axis of the annular rotating detonation combustor. The annular rotating detonation combustor is fluidly and directly coupled with the compressor outlet.Type: GrantFiled: October 18, 2018Date of Patent: December 27, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi
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Publication number: 20220364528Abstract: An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.Type: ApplicationFiled: July 14, 2022Publication date: November 17, 2022Inventors: Nicholas William Rathay, Timothy John Sommerer, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Patent number: 11415080Abstract: An engine includes an inlet tube introducing air to a combustion process and a first plurality of fuel injectors disposed in the inlet tube and used for scram-jet engine operation. The engine includes a second plurality of fuel injectors used for ram-jet engine operation. The second plurality of fuel injectors is upstream from the first plurality of fuel injectors and is disposed in the inlet tube. The engine includes a combustor swirl zone downstream of and adjacent to the first plurality of fuel injectors.Type: GrantFiled: May 14, 2018Date of Patent: August 16, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Timothy John Sommerer, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Patent number: 11255544Abstract: A rotating detonation combustion (RDC) system is provided. The RDC includes a first outer wall and a second outer wall each extended around a centerline axis, and a detonation chamber formed radially inward of the second outer wall. A fuel passage extended between the first outer wall and the second outer wall, the fuel passage including a first inlet opening proximate to the aft end through which a flow of fuel is received into the fuel passage. The flow of fuel is provided through the fuel passage from the aft end to the forward end of the RDC system and to the detonation chamber.Type: GrantFiled: December 3, 2019Date of Patent: February 22, 2022Assignee: GENERAL ELECTRIC COMPANYInventors: Thomas Earl Dyson, Thomas Michael Lavertu, Sarah Marie Monahan, Kapil Kumar Singh, Venkat Eswarlu Tangirala, Joel Meier Haynes
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Publication number: 20210372624Abstract: A propulsion system includes at least one rotating detonation actuator comprising: a flow path extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the flow path; an outer wall defining a radially outer boundary of the flow path; and at least one aircraft wing. The rotating detonation actuator is disposed in the aircraft wing. At least one rotating detonation wave travels through the flow path from the inlet end to the outlet end.Type: ApplicationFiled: August 3, 2021Publication date: December 2, 2021Inventors: Nicholas William Rathay, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Patent number: 11149954Abstract: A rotating detonation combustion system is generally provided. The rotating detonation combustion system includes an outer wall, an upstream wall, and a radial wall. The outer wall is defined circumferentially around a combustor centerline extended along a lengthwise direction. The outer wall defines a first radius portion generally upstream along the outer wall. A second radius portion is defined generally downstream along the outer wall and a transition portion is defined between the first and second radius portions. The first radius portion defines a first radius greater than a second radius at the second radius portion. The transition portion defines a generally decreasing radius from the first radius portion to the second radius portion. The upstream wall is defined circumferentially around the combustor centerline and is extended along the lengthwise direction and inward radially of the first radius portion of the outer wall. An oxidizer passage is defined within the upstream wall.Type: GrantFiled: October 27, 2017Date of Patent: October 19, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi
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Publication number: 20210285370Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.Type: ApplicationFiled: May 27, 2021Publication date: September 16, 2021Inventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Peter Daniel Silkowski
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Patent number: 11105511Abstract: A propulsion system includes at least one rotating detonation actuator comprising: a flow path extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the flow path; an outer wall defining a radially outer boundary of the flow path; and at least one aircraft wing. The rotating detonation actuator is disposed in the aircraft wing. At least one rotating detonation wave travels through the flow path from the inlet end to the outlet end.Type: GrantFiled: December 14, 2018Date of Patent: August 31, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Nicholas William Rathay, Narendra Digamber Joshi, Venkat Eswarlu Tangirala
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Patent number: 11053844Abstract: Embodiments of a combustor for a gas turbine engine are provided herein. In some embodiments, a combustion chamber for a gas turbine engine comprising may include a combustor having an inner volume defined at least partially by a front wall, wherein the wall comprises a plurality of facets each having a through hole fluidly coupled to the inner volume, and wherein the plurality of facets are oriented such that an axis of each of the plurality of facets is offset from a central axis of the combustor by an angle.Type: GrantFiled: September 17, 2018Date of Patent: July 6, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Venkat Eswarlu Tangirala, Narendra Digamber Joshi, Peter Daniel Silkowski
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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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Publication number: 20210164660Abstract: A rotating detonation combustion (RDC) system is provided. The RDC includes a first outer wall and a second outer wall each extended around a centerline axis, and a detonation chamber formed radially inward of the second outer wall. A fuel passage extended between the first outer wall and the second outer wall, the fuel passage including a first inlet opening proximate to the aft end through which a flow of fuel is received into the fuel passage. The flow of fuel is provided through the fuel passage from the aft end to the forward end of the RDC system and to the detonation chamber.Type: ApplicationFiled: December 3, 2019Publication date: June 3, 2021Inventors: Thomas Earl Dyson, Thomas Michael Lavertu, Sarah Marie Monahan, Kapil Kumar Singh, Venkat Eswarlu Tangirala, Joel Meier Haynes
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Publication number: 20210164405Abstract: A computer-implemented method for multi-mode operation of a combustion system, a combustion system, and a heat engine are provided. The method includes initializing combustion of a fuel/oxidizer mixture, determining whether conditions at the combustion system meet or exceed a first threshold operating parameter, transitioning to detonation combustion of the fuel/oxidizer mixture if conditions at the combustion system meet or exceed the first threshold operating parameter, and maintaining or increasing fuel flow through a deflagrative fuel circuit if conditions at the combustion system do not meet or exceed the first threshold operating parameter.Type: ApplicationFiled: December 3, 2019Publication date: June 3, 2021Inventors: Joel Meier Haynes, Sarah Marie Monahan, Thomas Michael Lavertu, Venkat Eswarlu Tangirala, Kapil Kumar Singh
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Publication number: 20210108801Abstract: Systems for rotating detonation combustion are provided herein. The system includes an inner wall and an outer wall each extended around a centerline axis, wherein a detonation chamber is defined between the inner wall and the outer wall, and an iterative structure positioned at one or both of the inner wall or the outer wall. The iterative structure includes a first threshold structure corresponding to a first pressure wave attenuation and a second threshold structure corresponding to a second pressure wave attenuation. The iterative structure provides for pressure wave strengthening along a first circumferential direction in the detonation chamber or pressure wave weakening along a second circumferential direction opposite of the first circumferential direction. The first circumferential direction corresponds to a desired direction of pressure wave propagation in the detonation chamber.Type: ApplicationFiled: October 14, 2019Publication date: April 15, 2021Inventors: Kapil Kumar Singh, Thomas Michael Lavertu, Thomas Earl Dyson, Sarah Marie Monahan, Venkat Eswarlu Tangirala, Joel Meier Haynes
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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: 10823418Abstract: A combustor for a turbine engine includes an inner combustion liner and an outer combustion liner together defining at least in part an interior. The interior includes a combustion chamber and a main portion. The combustor also includes an inlet combustion liner at least partially defining the combustion chamber of the interior and including an inlet assembly. The inlet assembly includes at least two cavity air tubes arranged along the axial direction, each cavity air tube extending between an inlet and an outlet, the outlet of each cavity air tube in airflow communication with the combustion chamber for providing the combustion chamber with a flow of air.Type: GrantFiled: March 2, 2017Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Joseph Zelina, Sarah Marie Monahan, Michael Anthony Benjamin, Venkat Eswarlu Tangirala, Sibtosh Pal, William Thomas Ross
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Publication number: 20200248906Abstract: A rotating detonation combustor includes an annular combustion passage that is non-circular. Specifically, the present rotating detonation combustor includes a forward wall, a radially inner wall, and a radially outer wall. The radially inner wall and the radially outer wall extend downstream from the forward wall around a longitudinal axis of the combustor, thus defining an annular passage between the radially inner wall and the radially outer wall. An air inlet and a fuel inlet are disposed proximate to the forward wall and in fluid communication with the annular passage. The cross-section of the annular passage, which can be elliptical or polygonal, is defined by arcuate and/or straight sides of the inner and outer walls.Type: ApplicationFiled: February 5, 2019Publication date: August 6, 2020Applicant: General Electric CompanyInventors: Kapil Kumar Singh, Narendra Digamber Joshi, Joel Meier Haynes, Venkat Eswarlu Tangirala, Meghan Borz
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Patent number: 10712002Abstract: A combustor assembly for use in a gas turbine engine is provided. The combustor assembly includes a dome assembly, a fuel nozzle coupled to the dome assembly, and a cowl assembly. The cowl assembly includes a radially inner cowl coupled to the dome assembly, and a radially outer cowl including a first cowl member and a second cowl member each positioned about the fuel nozzle. The first and second cowl members substantially align to define a substantially continuous flow path configured to direct a flow of air about the dome assembly.Type: GrantFiled: July 17, 2015Date of Patent: July 14, 2020Assignee: General Electric CompanyInventors: Matthieu Marc Masquelet, Narendra Digamber Joshi, Venkat Eswarlu Tangirala, Sarah Marie Monahan
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Publication number: 20200191398Abstract: A flow control system includes at least one flow surface; and at least one rotating detonation actuator including: an annulus extending from an inlet end to an outlet end; an inner wall defining a radially inner boundary of the annulus; and an outer wall defining a radially outer boundary of the annulus. At least one rotating detonation wave travels through the annulus from the inlet end to the outlet end. Combustion gas from the at least one rotating detonation actuator modifies at least one flow characteristic at the flow surface.Type: ApplicationFiled: December 14, 2018Publication date: June 18, 2020Applicant: General Electric CompanyInventors: Nicholas William Rathay, Narendra Digamber Joshi, Venkat Eswarlu Tangirala