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公开(公告)号：US11149948B2
公开(公告)日：2021-10-19
申请号：US15681990
申请日：2017-08-21
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , Randall Charles Boehm
Abstract: The present disclosure is directed to a combustor system including a fuel nozzle comprising a main fuel injector defining an angled main injection port. Each angled main injection port defines an inlet end and an outlet end. The outlet end is oriented downstream relative to the inlet end at an angle relative to a centerline axis of the fuel nozzle. The angled main injection port permits egress of fuel from a main fuel circuit to the combustion chamber. The fuel nozzle further defines a radial main injection port. The outlet end is oriented along an axial direction approximately equal relative to the inlet end and radially outward thereof relative to the centerline axis. The radial main injection port is extended perpendicular relative to the centerline axis.
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公开(公告)号：US20190063753A1
公开(公告)日：2019-02-28
申请号：US15684083
申请日：2017-08-23
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , Randall Charles Boehm , Michael Anthony Benjamin , Beverly Stephenson Duncan , Jeffrey Lyal Powell
Abstract: Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.
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公开(公告)号：US11561008B2
公开(公告)日：2023-01-24
申请号：US15684083
申请日：2017-08-23
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , Randall Charles Boehm , Michael Anthony Benjamin , Beverly Stephenson Duncan , Jeffrey Lyal Powell
Abstract: Fuel nozzle assemblies are provided. For example, a fuel nozzle assembly for a combustor system comprises a fuel nozzle having a pilot swirler and an outlet defined in an outlet end, as well as a main mixer attached to the outlet end and extending about the outlet. A total combustor airflow through the combustor system comprises a pilot swirler airflow that is greater than about 14% and a main mixer airflow that is less than about 50% of the total combustor airflow. In further embodiments, the fuel nozzle also comprises main and pilot fuel injectors that each are configured to receive a portion of a fuel flow to the fuel nozzle. The fuel nozzle provides less than about 80% of the fuel flow to the main fuel injector at a high power operating condition of a gas turbine engine in which the fuel nozzle assembly is installed.
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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：US11480338B2
公开(公告)日：2022-10-25
申请号：US15684066
申请日：2017-08-23
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , David Louis Burrus
Abstract: Combustor systems are provided. For example, a combustor system comprises a combustor having forward and aft ends and including annular inner and outer liners that each extend generally along an axial direction and define a combustion chamber therebetween. The combustor system also comprises a fuel nozzle having an outlet defined in an outlet end of the fuel nozzle and including a pilot swirler. The outlet is positioned at the forward end of the combustor to direct a fuel-air mixture into the combustion chamber. The combustor system further comprises a main mixer attached to the outlet end of the fuel nozzle and extending about the outlet. A total combustor airflow through the combustor comprises a pilot swirler airflow that is greater than about 14% of the total combustor airflow and a main mixer airflow that is less than about 50% of the total combustor airflow.
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公开(公告)号：US20190056110A1
公开(公告)日：2019-02-21
申请号：US15681990
申请日：2017-08-21
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , Randall Charles Boehm
IPC: F23R3/06
Abstract: The present disclosure is directed to a combustor system including a fuel nozzle comprising a main fuel injector defining an angled main injection port. Each angled main injection port defines an inlet end and an outlet end. The outlet end is oriented downstream relative to the inlet end at an angle relative to a centerline axis of the fuel nozzle. The angled main injection port permits egress of fuel from a main fuel circuit to the combustion chamber. The fuel nozzle further defines a radial main injection port. The outlet end is oriented along an axial direction approximately equal relative to the inlet end and radially outward thereof relative to the centerline axis. The radial main injection port is extended perpendicular relative to the centerline axis.
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公开(公告)号：US11002300B2
公开(公告)日：2021-05-11
申请号：US16262283
申请日：2019-01-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jeffrey Rambo , Sarah Anne Edwards , David Perveiler , Mark David Durbin , Erich Fitzpatrick
Abstract: A flow conditioning system for a duct. The flow conditioning system includes a preconditioner that modifies upstream fluid flow that is maldistributed, providing predictable downstream flow to fluid flowing within the duct. The directional flow conditioner also includes a stationary flow geometry structure downstream of the preconditioner. The stationary flow geometry structure further conditions the upstream fluid flow from the preconditioner to provide a downstream flow with a substantially uniform flow profile. The flow conditioning system transforms upstream fluids having a maldistributed flow profile such as may be caused by a component, structure or obstruction within the duct to a substantially uniform flow profile downstream of the flow conditioning system within the available axial duct length so that the fluid may interact efficiently with equipment such as heat exchangers positioned within the duct downstream of the flow conditioning system.
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公开(公告)号：US20200240447A1
公开(公告)日：2020-07-30
申请号：US16262283
申请日：2019-01-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jeffrey Rambo , Sarah Anne Edwards , David Perveiler , Mark David Durbin , Erich Fitzpatrick
IPC: F15D1/06
Abstract: A flow conditioning system for a duct. The flow conditioning system includes a preconditioner that modifies upstream fluid flow that is maldistributed, providing predictable downstream flow to fluid flowing within the duct. The directional flow conditioner also includes a stationary flow geometry structure downstream of the preconditioner. The stationary flow geometry structure further conditions the upstream fluid flow from the preconditioner to provide a downstream flow with a substantially uniform flow profile. The flow conditioning system transforms upstream fluids having a maldistributed flow profile such as may be caused by a component, structure or obstruction within the duct to a substantially uniform flow profile downstream of the flow conditioning system within the available axial duct length so that the fluid may interact efficiently with equipment such as heat exchangers positioned within the duct downstream of the flow conditioning system.
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公开(公告)号：US20190063752A1
公开(公告)日：2019-02-28
申请号：US15684066
申请日：2017-08-23
Applicant: General Electric Company
Inventor： Eric John Stevens , Mark David Durbin , David Louis Burrus
IPC: F23R3/14
Abstract: Combustor systems are provided. For example, a combustor system comprises a combustor having forward and aft ends and including annular inner and outer liners that each extend generally along an axial direction and define a combustion chamber therebetween. The combustor system also comprises a fuel nozzle having an outlet defined in an outlet end of the fuel nozzle and including a pilot swirler. The outlet is positioned at the forward end of the combustor to direct a fuel-air mixture into the combustion chamber. The combustor system further comprises a main mixer attached to the outlet end of the fuel nozzle and extending about the outlet. A total combustor airflow through the combustor comprises a pilot swirler airflow that is greater than about 14% of the total combustor airflow and a main mixer airflow that is less than about 50% of the total combustor airflow.
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