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公开(公告)号：US20150276225A1
公开(公告)日：2015-10-01
申请号：US14227640
申请日：2014-03-27
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai
CPC classification number: F23R3/286 , F23C2900/07001 , F23R3/14 , Y10T29/49432
Abstract: A premixing fuel nozzle assembly including a plurality of premixers for use in a combustor section of a turbine engine is provided. Each of the premixers of the pre-mixing fuel nozzle assembly including an annular outer ring, an annular inner hub, configured co-annular with the outer ring, a plurality of swirler vanes, a plurality of fuel injection orifices formed in each vane and an air-assist orifice formed about at least one of the plurality of fuel injection orifices. The plurality of swirler vanes extend radially outward from the annular inner hub toward the annular outer ring. The air-assist orifice generating a co-annular air-assist jacket about a fuel jet injected via the fuel injection orifice to provide additional momentum and thus mixing of the fuel jet with a downstream crossflow of fluid. A combustor section including the pre-mixing fuel nozzle assembly and method of assembling the pre-mixing fuel nozzle are additionally disclosed.
Abstract translation: 提供了一种预混燃料喷嘴组件，其包括用于涡轮发动机的燃烧器部分中的多个预混合器。 预混合燃料喷嘴组件的每个预混合器包括环形外圈，与外圈共同环形的环形内毂，多个旋流叶片，形成在每个叶片中的多个燃料喷射孔和 空气辅助孔形成在多个燃料喷射孔中的至少一个上。 多个旋流器叶片从环形内轮毂径向向外延伸到环形外圈。 空气辅助孔围绕经由燃料喷射孔喷射的燃料喷流产生共同环形的空气辅助护套，以提供额外的动量，从而使燃料射流与流体的下游交叉流混合。 还公开了一种包括预混合燃料喷嘴组件和组装预混合燃料喷嘴的燃烧器部分。
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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：US20180340688A1
公开(公告)日：2018-11-29
申请号：US15434830
申请日：2017-02-16
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai , Jin Yan , Anthony John Dean
IPC: F23R3/28
Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
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Patent Agency Ranking
公开(公告)号：US10054314B2
公开(公告)日：2018-08-21
申请号：US14973375
申请日：2015-12-17
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai , Wei Zhao , Shivakumar Srinivasan
CPC classification number: F23R3/36 , F02C3/14 , F02C3/20 , F02C7/222 , F05D2220/32 , F05D2260/60 , F23R3/286 , F23R3/346
Abstract: An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an interior surface thereof. Each outlet of the plurality of outlets includes a secondary fuel conduit in fluid communication with a secondary fuel source, and includes a first wall that defines a secondary fuel path. The secondary compressed air conduit is in fluid communication with a compressed air source, and includes a second wall disposed about the first wall in a substantially coannular arrangement, wherein the first wall and the second wall define a secondary compressed air flow path. Each outlet is configured to inject a secondary fuel and compressed air into the primary compressed air flow path in a direction transverse to the primary compressed air flow path forming a fuel-air mixture.
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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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公开(公告)号：US10415833B2
公开(公告)日：2019-09-17
申请号：US15434830
申请日：2017-02-16
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai , Jin Yan , Anthony John Dean
Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
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公开(公告)号：US20170176015A1
公开(公告)日：2017-06-22
申请号：US14973375
申请日：2015-12-17
Applicant: General Electric Company
Inventor： Sravan Kumar Dheeraj Kapilavai , Wei Zhao , Shivakumar Srinivasan
CPC classification number: F23R3/36 , F02C3/14 , F02C3/20 , F02C7/222 , F05D2220/32 , F05D2260/60 , F23R3/286 , F23R3/346
Abstract: An axial fuel staging injector for a gas turbine includes a body. The body includes an upstream end and a downstream end. The body defines a primary compressed air flow path through which compressed air flows from a compressed air source to a transition duct of a gas turbine combustor. The body includes a plurality of outlets disposed on an interior surface thereof. Each outlet of the plurality of outlets includes a secondary fuel conduit in fluid communication with a secondary fuel source, and includes a first wall that defines a secondary fuel path. The secondary compressed air conduit is in fluid communication with a compressed air source, and includes a second wall disposed about the first wall in a substantially coannular arrangement, wherein the first wall and the second wall define a secondary compressed air flow path. Each outlet is configured to inject a secondary fuel and compressed air into the primary compressed air flow path in a direction transverse to the primary compressed air flow path forming a fuel-air mixture.
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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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