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公开(公告)号：US20200248906A1
公开(公告)日：2020-08-06
申请号：US16267469
申请日：2019-02-05
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi , Joel Meier Haynes , Venkat Eswarlu Tangirala , Meghan Borz
Abstract: 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.
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公开(公告)号：US20180252410A1
公开(公告)日：2018-09-06
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：US20170009993A1
公开(公告)日：2017-01-12
申请号：US14791684
申请日：2015-07-06
Applicant: General Electric Company
Inventor： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
CPC classification number: F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
Abstract: A combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two annular trapped vortex cavities are located on the combustor liner and staged axially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities spaced apart from a radially outer wall and extending between an aft wall and a forward wall of each cavity. A plurality of injectors are configured tangentially relative to the circular radially outer wall to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid. A gas turbine engine including the combustor assembly is disclosed.
Abstract translation: 一种燃烧器组件，其包括在其中限定用于主流体的下游流动的燃烧室的燃烧器衬套。 至少两个环形的被捕获的涡流腔位于燃烧器衬套上并且沿轴向间隔分开。 空腔开口位于与径向外壁间隔开并在每个空腔的后壁和前壁之间延伸的至少两个环形捕获涡流腔中的每一个的径向内端。 多个喷射器相对于圆形径向外壁切向配置，以提供空气和燃料的喷射，以在相应的环形捕获的涡流空腔内形成燃料和空气混合物的环形旋转捕获涡流。 空腔开口处的燃料和空气混合物的环形旋转捕获的涡流基本上垂直于主流体的下游流动。 公开了一种包括燃烧器组件的燃气涡轮发动机。
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公开(公告)号：US20150000290A1
公开(公告)日：2015-01-01
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
IPC: F02C3/04
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.
Abstract translation: 提供了一种涡轮机系统和操作方法。 该系统包括被配置为产生压缩的低氧空气流的压缩机和构造成接收压缩的低氧空气流并燃烧燃料流以产生后燃气流的燃烧器。 涡轮机系统还包括用于接收后燃烧气体流以产生低NOx排气流的涡轮机;被配置为接收低NOx排气流并产生冷却空气流的热回收系统和配置成 产生氧气和水蒸气不足的冷却和压缩空气流。 氧气和水蒸气不足的冷却和压缩空气流的一部分被引导到燃烧器，以在燃烧器的暴露部分上产生氧和H 2 O缺乏膜，并且另一部分被引导到涡轮以提供冷却流。
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公开(公告)号：US11536456B2
公开(公告)日：2022-12-27
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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Patent Agency Ranking
公开(公告)号：US11255544B2
公开(公告)日：2022-02-22
申请号：US16701521
申请日：2019-12-03
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Thomas Michael Lavertu , Sarah Marie Monahan , Kapil Kumar Singh , Venkat Eswarlu Tangirala , Joel Meier Haynes
IPC: F02C9/26 , F23R7/00 , F02C5/02 , F23R3/28 , F02C3/04 , F02C7/22 , F23R3/00 , F02C7/224 , F02C9/28
Abstract: 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.
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公开(公告)号：US20210285370A1
公开(公告)日：2021-09-16
申请号：US17332504
申请日：2021-05-27
Applicant: General Electric Company
IPC: 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 , F23R3/14
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：US20210164660A1
公开(公告)日：2021-06-03
申请号：US16701521
申请日：2019-12-03
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Thomas Michael Lavertu , Sarah Marie Monahan , Kapil Kumar Singh , Venkat Eswarlu Tangirala , Joel Meier Haynes
Abstract: 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.
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公开(公告)号：US20190128529A1
公开(公告)日：2019-05-02
申请号：US15795894
申请日：2017-10-27
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Narendra Digamber Joshi
Abstract: 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. A combustion chamber is defined downstream of the upstream wall and radially inward of the outer wall. The radial wall is coupled to the outer wall and the upstream wall. A fluid injection opening is defined through at least one of the radial wall or the outer wall adjacent to the combustion chamber.
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公开(公告)号：US20190086086A1
公开(公告)日：2019-03-21
申请号：US15711742
申请日：2017-09-21
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Anthony Dean , Narendra Digamber Joshi , Sarah Monahan
Abstract: A cavity stabilized detonation combustor assembly for a rotating detonation engine includes opposing inner and outer walls that are radially spaced apart from each other and that both extend around a center axis of the rotating detonation engine. Detonations in the rotating detonation engine rotate around the center axis of the rotating detonation engine. The assembly also includes opposing leading and trailing cavity walls that are coupled with the inner and outer walls and which radially extend away from the center axis, and an axial wall that is coupled with and connects the leading and trailing cavity walls with each other. The axial wall and the leading and trailing cavity walls define a detonation stabilizing cavity in which detonations of the rotating detonation engine occur and are stabilized.
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