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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：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：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：US20150101340A1
公开(公告)日：2015-04-16
申请号：US14051474
申请日：2013-10-11
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Sherif Hatem Abdulla Mohamed
Abstract: A gas turbine engine is presented. The gas turbine engine includes a control unit having a first bypass channel that is coupled between an outlet of a first turbine and an inlet of a second turbine. Further, the control unit includes a second bypass channel coupled between a first outlet of a compressor unit and the inlet of the second turbine. Additionally, the control unit includes a first control valve coupled to the first bypass channel and configured to direct at least a first portion of exhaust gas from the first turbine to the inlet of the second turbine via the first bypass channel. Furthermore, the control unit includes a second control valve coupled to the second bypass channel and configured to direct at least a first portion of compressed air from the compressor unit to the inlet of the second turbine via the second bypass channel.
Abstract translation: 提出了一种燃气轮机。 燃气涡轮发动机包括控制单元，其具有联接在第一涡轮机的出口和第二涡轮机的入口之间的第一旁通通道。 此外，控制单元包括耦合在压缩机单元的第一出口和第二涡轮机的入口之间的第二旁通通道。 另外，控制单元包括耦合到第一旁路通道并被构造成经由第一旁通通道将至少第一部分废气从第一涡轮引导到第二涡轮机的入口的第一控制阀。 此外，控制单元包括联接到第二旁通通道并被配置成经由第二旁通通道将压缩机单元的至少第一部分压缩空气引导到第二涡轮机的入口的第二控制阀。
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公开(公告)号：US11371711B2
公开(公告)日：2022-06-28
申请号：US16203335
申请日：2018-11-28
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi
Abstract: A combustion system includes an annular tube disposed between an inner wall and an outer wall, the annular tube extending from an inlet end to an outlet end; at least one annulus inlet disposed in the annular tube proximate the inlet end, the annulus inlet providing a conduit through which fluid flows into the annular tube; at least one outlet disposed in the annular tube proximate the outlet end; at least one inlet fluid plenum disposed upstream of the annulus inlet; and at least one fluid inlet disposed upstream of the inlet fluid plenum. The fluid inlet is linearly offset from the annulus inlet.
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Patent Agency Ranking
公开(公告)号：US20210108801A1
公开(公告)日：2021-04-15
申请号：US16601012
申请日：2019-10-14
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Thomas Michael Lavertu , Thomas Earl Dyson , Sarah Marie Monahan , Venkat Eswarlu Tangirala , Joel Meier Haynes
Abstract: 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.
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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：US10352567B2
公开(公告)日：2019-07-16
申请号：US14879793
申请日：2015-10-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Liangyu Wang , Anthony John Dean , Keith Robert McManus , Kapil Kumar Singh , Suhui Li , Sravan Kumar Dheeraj Kapilavai , Mathew Paul Thariyan , Owen Graham
Abstract: The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOx emissions.
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公开(公告)号：US09534541B2
公开(公告)日：2017-01-03
申请号：US14051474
申请日：2013-10-11
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Sherif Hatem Abdulla Mohamed
Abstract: A gas turbine engine is presented. The gas turbine engine includes a control unit having a first bypass channel that is coupled between an outlet of a first turbine and an inlet of a second turbine. Further, the control unit includes a second bypass channel coupled between a first outlet of a compressor unit and the inlet of the second turbine. Additionally, the control unit includes a first control valve coupled to the first bypass channel and configured to direct at least a first portion of exhaust gas from the first turbine to the inlet of the second turbine via the first bypass channel. Furthermore, the control unit includes a second control valve coupled to the second bypass channel and configured to direct at least a first portion of compressed air from the compressor unit to the inlet of the second turbine via the second bypass channel.
Abstract translation: 提出了一种燃气轮机。 燃气涡轮发动机包括控制单元，其具有联接在第一涡轮机的出口和第二涡轮机的入口之间的第一旁通通道。 此外，控制单元包括耦合在压缩机单元的第一出口和第二涡轮机的入口之间的第二旁通通道。 另外，控制单元包括耦合到第一旁路通道并被构造成经由第一旁通通道将至少第一部分废气从第一涡轮引导到第二涡轮机的入口的第一控制阀。 此外，控制单元包括联接到第二旁通通道并被配置成经由第二旁通通道将压缩机单元的至少第一部分压缩空气引导到第二涡轮机的入口的第二控制阀。
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公开(公告)号：US20200248905A1
公开(公告)日：2020-08-06
申请号：US16267473
申请日：2019-02-05
Applicant: General Electric Company
Inventor： Kapil Kumar Singh , Narendra Digamber Joshi
Abstract: The present disclosure is directed to a rotating detonation combustor that includes a forward wall, a radially inner wall, and a radially outer wall. The forward wall is disposed at an inlet end of the rotating detonation combustor. The radially inner wall surrounds a longitudinal axis and extends downstream from the forward wall to an outlet end of the rotating detonation combustor. The radially outer wall extends downstream from the forward wall to the outlet end and surrounds the radially inner wall to define at least one annular plenum between the radially inner wall and the radially outer wall. At least one partition is proximate to the inlet end and defines at least two mixing zones. A plurality of oxidizer inlets and a plurality of fuel inlets are disposed at the inlet end in fluid communication with the at least two mixing zones.
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