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公开(公告)号：US20180187888A1
公开(公告)日：2018-07-05
申请号：US15398496
申请日：2017-01-04
Applicant: General Electric Company
CPC classification number: F23R3/002 , F23R3/06 , F23R3/58 , F23R2900/03042
Abstract: A combustor for use in a turbine engine that includes an inner combustion liner and an outer combustion liner. An interior is defined between the inner combustion liner and the outer combustion liner, and the interior includes a cavity portion and a main portion extending radially inward from the cavity portion. The cavity portion includes a flow inlet and the main portion includes a flow outlet. A plurality of film cooling holes are formed in at least one of the inner combustion liner and the outer combustion liner. The plurality of film cooling holes are configured such that cooling airflow discharged therefrom flows helically relative to a centerline of the turbine engine and towards the flow outlet.
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32.发明申请公开(公告)号：US20180179951A1
公开(公告)日：2018-06-28
申请号：US15390112
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Keith Robert McManus , Michael Bowman , Narendra Joshi , Joel Haynes , Anthony Dean
CPC classification number: F02C3/16 , F02C3/34 , F02C5/02 , F23R2900/03341
Abstract: A turbine engine includes at least one compressor configured to increase pressure of a fluid flow and a primary combustor coupled in flow communication with the at least one compressor. The primary combustor is configured to receive pressurized fluid flow from the at least one compressor. The primary combustor includes a housing defining at least one combustion chamber. The primary combustor is configured for a rotating detonation process to occur within said at least one combustion chamber. The turbine engine also includes at least one supplemental combustor coupled in flow communication with the primary combustor. The at least one supplemental combustor is configured to receive combustion products and perform a combustion operation. The turbine engine further includes a turbine assembly coupled in flow communication with the at least one supplemental combustor. The turbine assembly is configured to receive combustion products from the at least one supplemental combustor.
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公开(公告)号：US09599017B2
公开(公告)日：2017-03-21
申请号：US13930122
申请日：2013-06-28
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Joel Meier Haynes , Venkat Eswarlu Tangirala , Christian Lee Vandervort
CPC classification number: F02C3/30 , F01K23/10 , F02C3/34 , F02C6/003 , F02C7/16 , F02C9/18 , F05D2260/61 , F23R3/34 , F23R2900/03341 , Y02E20/16 , Y02E20/18
Abstract: A turbine system and method of operating is provided. The system includes a compressor configured to generate a compressed low-oxygen air stream and a combustor configured to receive the compressed low-oxygen air stream and to combust a fuel stream to generate a post combustion gas stream. The turbine system also includes a turbine for receiving the post combustion gas stream to generate a low-NOx exhaust gas stream, a heat recovery system configured to receive the low-NOx exhaust gas stream and generate a cooled air stream and an auxiliary compressor configured to generate an oxygen and water vapor deficient cooled and compressed air stream. A portion of the oxygen and water vapor deficient cooled and compressed air stream is directed to the combustor to generate an Oxygen and H2O deficient film on exposed portions of the combustor, and another portion is directed to the turbine to provide a cooling flow.
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34.发明申请COMBUSTOR ASSEMBLY FOR USE IN A GAS TURBINE ENGINE AND METHOD OF ASSEMBLING 审中-公开用于燃气涡轮发动机的燃烧器组件和组装方法公开(公告)号：US20170016620A1
公开(公告)日：2017-01-19
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.
Abstract translation: 提供了一种用于燃气涡轮发动机的燃烧器组件。 燃烧器组件包括圆顶组件，联接到圆顶组件的燃料喷嘴和整流罩组件。 整流罩组件包括联接到圆顶组件的径向内部整流罩，以及包括第一整流罩构件和每个围绕燃料喷嘴定位的第二整流罩构件的径向外罩。 第一和第二整流罩构件基本上对准以限定基本上连续的流动路径，其构造成引导围绕圆顶组件的空气流。
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公开(公告)号：US11898757B2
公开(公告)日：2024-02-13
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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Patent Agency Ranking
公开(公告)号：US20220364528A1
公开(公告)日：2022-11-17
申请号：US17812573
申请日：2022-07-14
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：US11053844B2
公开(公告)日：2021-07-06
申请号：US16133362
申请日：2018-09-17
Applicant: General Electric Company
IPC: F23R3/14 , F02C3/14 , F23R3/00 , F23R3/34 , F23R3/44 , F04D29/54 , F01D9/02 , F04D27/02 , F04D29/56 , F23R3/04 , F23R3/12 , F23R3/26 , F23R3/28 , F23R3/50 , B23P15/04 , F02C3/04
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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公开(公告)号：US10823418B2
公开(公告)日：2020-11-03
申请号：US15447847
申请日：2017-03-02
Applicant: General Electric Company
Inventor： Joseph Zelina , Sarah Marie Monahan , Michael Anthony Benjamin , Venkat Eswarlu Tangirala , Sibtosh Pal , William Thomas Ross
Abstract: 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.
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公开(公告)号：US20190226398A1
公开(公告)日：2019-07-25
申请号：US16133362
申请日：2018-09-17
Applicant: General Electric Company
IPC: F02C3/14 , B23P15/04 , F23R3/12 , F01D9/02 , F23R3/50 , F23R3/44 , F23R3/34 , F23R3/28 , F23R3/26 , F23R3/14 , F23R3/04 , F23R3/00 , F04D29/56 , F04D29/54 , F04D27/02 , F02C3/04
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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公开(公告)号：US10280760B2
公开(公告)日：2019-05-07
申请号：US14870853
申请日：2015-09-30
Applicant: General Electric Company
Inventor： Narendra Digamber Joshi , Christian Lee Vandervort , Krishan Lal Luthra , Ronald Scott Bunker , Joel Meier Haynes , Venkat Eswarlu Tangirala
IPC: F02C1/00 , F02C3/34 , F02C1/08 , F01D5/18 , F23R3/00 , F02C6/00 , F02C7/18 , F23C9/08 , F01D25/32
Abstract: A turbine assembly is provided. The turbine assembly includes a gas turbine engine including at least one hot gas path component formed at least partially from a ceramic matrix composite material. The turbine assembly also includes a treatment system positioned to receive a flow of exhaust gas from the gas turbine engine. The treatment system is configured to remove water from the flow of exhaust gas to form a flow of treated exhaust gas, and to channel the flow of treated exhaust gas towards the at least one hot gas path component. The at least one hot gas path component includes a plurality of cooling holes for channeling the flow of treated exhaust gas therethrough, such that a protective film is formed over the at least one hot gas path component.
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