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公开(公告)号：US20180179953A1
公开(公告)日：2018-06-28
申请号：US15390105
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Andrew Maxwell Peter , Kapil Kumar Singh , Keith Robert McManus , Joel Haynes , Anthony Dean
CPC classification number: F02C5/02 , F02C3/04 , F02C3/14 , F02C3/16 , F02C3/165 , F02C5/00 , F02C5/10 , F02C7/264 , F02K7/075 , F02K7/08 , F05D2220/32 , F05D2240/35 , F23R3/286 , F23R3/34 , F23R3/42 , F23R3/56 , F23R7/00
Abstract: A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.
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2.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：US11371708B2
公开(公告)日：2022-06-28
申请号：US17043004
申请日：2018-04-06
Applicant: General Electric Company
Inventor： Mathew Paul Thariyan , Manampathy Gangadharan Giridharan , Kapil Kumar Singh , Sravan Kumar Dheeraj Kapilavai , Keith Robert McManus , Gregory Allen Boardman , Mark David Durbin
Abstract: A premixer for a gas turbine combustor includes a centerbody, a swirler assembly, and a mixing duct. The swirler assembly includes an inner swirler with vanes that rotate air in a first direction and an outer swirler with vanes that rotate air in an opposite direction. The inner swirler vanes and the outer swirler vanes are separated by an annular splitter. The outer swirler vanes define an outlet plane, and the inner swirler vanes each have a trailing edge that is disposed at an acute angle relative to the outlet plane. In one aspect, the inner swirler is axially offset from the outer swirler. The mixing duct may also define fuel passages that deliver fuel to fuel outlets on the downstream end of the mixing duct. The premixer is designed for operation on gaseous fuel or liquid fuel.
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Patent Agency Ranking
公开(公告)号：US10221763B2
公开(公告)日：2019-03-05
申请号：US15390105
申请日：2016-12-23
Applicant: General Electric Company
Inventor： Venkat Eswarlu Tangirala , Andrew Maxwell Peter , Kapil Kumar Singh , Keith Robert McManus , Joel Haynes , Anthony Dean
IPC: F02C5/02 , F02C3/16 , F02C7/264 , F23R7/00 , F02C3/04 , F02K7/08 , F02K7/075 , F02C5/10 , F02C5/00 , F02C3/14 , F23R3/34 , F23R3/42 , F23R3/28 , F23R3/56
Abstract: A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.
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公开(公告)号：US20170102147A1
公开(公告)日：2017-04-13
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
CPC classification number: F23R3/14 , F02C3/04 , F02C7/222 , F05D2220/32 , F05D2260/14 , F23C2900/07001 , F23D11/107 , F23D11/383 , F23D2900/14021 , F23R3/286 , F23R3/30 , Y02T50/675
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：US09534788B2
公开(公告)日：2017-01-03
申请号：US14243951
申请日：2014-04-03
Applicant: General Electric Company
Inventor： Suhui Li , Narendra Digamber Joshi , Keith Robert McManus
Abstract: A system for premixing fuel and air prior to combustion in a gas turbine engine includes a mixing duct, a centerbody fuel injector located along a central axis of the mixing duct an outer annular swirler located adjacent an upstream end of the mixing duct for swirling air flowing therethrough in a first swirl direction and an inner annular swirler located adjacent of the mixing duct upstream end for swirling air flowing therethrough in a second swirl direction. The system includes a hub separating the inner and outer annular swirlers to permit independent rotation of an air stream therethrough and multiple hollow paths located radially outward around the centerbody fuel injector and at a radially inward side of the inner annular swirler for allowing a flow of sweeping air over the surface of the centerbody fuel injector.
Abstract translation: 用于在燃气涡轮发动机中燃烧之前预混合燃料和空气的系统包括混合管道，沿着混合管道的中心轴线定位的中心体燃料喷射器，位于混合管道的上游端附近的外部环形旋流器，用于旋转空气流动 在第一旋转方向穿过并且位于邻近混合管道上游端的内部环形旋流器，用于在第二旋转方向上流过其中的涡流。 该系统包括分隔内环形旋流器和外环形旋流器的毂，以允许空气流独立旋转，以及位于中心体燃料喷射器周围径向向外的多个中空路径，以及内环形旋流器的径向内侧， 空心在中心体燃油喷射器的表面上。
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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：US20150285503A1
公开(公告)日：2015-10-08
申请号：US14243951
申请日：2014-04-03
Applicant: General Electric Company
Inventor： Suhui Li , Narendra Digamber Joshi , Keith Robert McManus
Abstract: A system for premixing fuel and air prior to combustion in a gas turbine engine includes a mixing duct, a centerbody fuel injector located along a central axis of the mixing duct, an outer annular swirler located adjacent an upstream end of the mixing duct for swirling air flowing therethrough in a first swirl direction and an inner annular swirler located adjacent of the mixing duct upstream end for swirling air flowing therethrough in a second swirl direction. The system includes a hub separating said inner and outer annular swirlers to permit independent rotation of an air stream therethrough and multiple hollow paths located radially outward around the centerbody fuel injector and at a radially inward side of the inner annular swirler for allowing a flow of sweeping air over the surface of the centerbody fuel injector.
Abstract translation: 用于在燃气涡轮发动机燃烧之前预混合燃料和空气的系统包括混合管道，沿着混合管道的中心轴线定位的中心体燃料喷射器，位于混合管道的上游端附近的外部环形旋流器，用于旋转空气 在第一旋转方向上流过其中，并且位于邻近混合管道上游端的内环形旋流器，用于在第二旋流方向上流过其中的涡流。 该系统包括：分隔所述内环形旋流器和外环形旋流器的轮毂，以允许空气流独立旋转;以及围绕中心体燃料喷射器径向向外定位的多个中空路径，以及在内环形旋流器的径向内侧， 空心在中心体燃油喷射器的表面上。
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