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公开(公告)号：US20180179961A1
公开(公告)日：2018-06-28
申请号：US15390035
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Thomas Michael Lavertu, Jr. , Kapil Kumar Singh , Venkat Eswarlu Tangirala , Michael John Bowman , Joel Meier Haynes , Anthony John Dean
CPC classification number: F02C9/40 , F02C3/16 , F02C3/165 , F02C3/22 , F02C3/305 , F02C5/00 , F02C5/04 , F02C6/18 , F02C7/22 , F05D2220/32 , F05D2240/35 , F23R3/00 , F23R3/56 , F23R7/00
Abstract: A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture formed at least partially from a primary fuel including methane. The assembly also includes a fuel reformer configured to produce a secondary fuel, wherein the fuel reformer is further configured to channel a flow of secondary fuel towards the rotating detonation combustor such that the fuel-air mixture further includes the secondary fuel.
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公开(公告)号：US20150323184A1
公开(公告)日：2015-11-12
申请号：US14706679
申请日：2015-05-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
CPC classification number: F02C3/14 , F01D9/023 , F04D27/0246 , F04D29/542 , F04D29/544 , F04D29/563 , F05D2240/35 , F23R3/002 , F23R3/04 , F23R3/12 , F23R3/26 , F23R3/28 , F23R3/34 , F23R3/44 , F23R3/50
Abstract: 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.
Abstract translation: 本文提供了一种用于燃气涡轮发动机的燃烧器的实施例。 在一些实施例中，用于燃气涡轮发动机的燃烧室可以包括具有至少部分地由前壁限定的内部容积的燃烧器，其中所述壁包括多个小面，每个小面具有流体连接到内部体积的通孔， 并且其中所述多个小面被定向成使得所述多个小面中的每一个的轴线偏离所述燃烧器的中心轴线一个角度。
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公开(公告)号：US11415080B2
公开(公告)日：2022-08-16
申请号：US15979217
申请日：2018-05-14
Applicant: General Electric Company
Inventor： Nicholas William Rathay , Timothy John Sommerer , Narendra Digamber Joshi , Venkat Eswarlu Tangirala
Abstract: 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.
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公开(公告)号：US20210372624A1
公开(公告)日：2021-12-02
申请号：US17392514
申请日：2021-08-03
Applicant: General Electric Company
Abstract: 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.
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公开(公告)号：US11105511B2
公开(公告)日：2021-08-31
申请号：US16220783
申请日：2018-12-14
Applicant: General Electric Company
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US20210164405A1
公开(公告)日：2021-06-03
申请号：US16701574
申请日：2019-12-03
Applicant: General Electric Company
Inventor： Joel Meier Haynes , Sarah Marie Monahan , Thomas Michael Lavertu , Venkat Eswarlu Tangirala , Kapil Kumar Singh
Abstract: 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.
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公开(公告)号：US10969107B2
公开(公告)日：2021-04-06
申请号：US15705954
申请日：2017-09-15
Applicant: General Electric Company
Inventor： Owen James Sullivan Rickey , Venkat Eswarlu Tangirala , Narendra Digamber Joshi , Shashank Yellapantula
Abstract: 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.
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公开(公告)号：US10712002B2
公开(公告)日：2020-07-14
申请号：US14801962
申请日：2015-07-17
Applicant: General Electric Company
Inventor： Matthieu Marc Masquelet , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Sarah Marie Monahan
Abstract: 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.
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29.发明申请公开(公告)号：US20190120492A1
公开(公告)日：2019-04-25
申请号：US16164474
申请日：2018-10-18
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
Abstract: 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.
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公开(公告)号：US10082076B2
公开(公告)日：2018-09-25
申请号：US14706679
申请日：2015-05-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
IPC: F23R3/04 , F02C3/14 , F23R3/14 , F02C3/04 , F04D29/54 , B23P15/04 , F23R3/00 , F23R3/34 , F23R3/44 , F23R3/12 , F23R3/26 , F23R3/28 , F23R3/50 , F01D9/02 , F04D27/02 , F04D29/56
CPC classification number: F02C3/14 , B23P15/04 , F01D9/023 , F02C3/04 , F04D27/0246 , F04D29/542 , F04D29/544 , F04D29/563 , F05D2240/35 , F23R3/002 , F23R3/04 , F23R3/12 , F23R3/14 , F23R3/26 , F23R3/28 , F23R3/34 , F23R3/44 , F23R3/50 , Y10T29/49323
Abstract: 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.
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