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公开(公告)号：US20140338349A1
公开(公告)日：2014-11-20
申请号：US13662621
申请日：2012-10-29
Applicant: General Electric Company
Inventor： Daniel Gerritt Wegerif , Jonathan Dwight Berry , Carl Robert Barker
IPC: F23R3/00
CPC classification number: F23R3/04 , F23R3/283 , F23R3/286 , F23R2900/03044
Abstract: The present application provides a combustion nozzle for use with a gas turbine engine. The combustion nozzle may include a number of mixing tubes, an outer shell surrounding the mixing tubes, and a floating aft plate assembly. The floating plate assembly may enclose the outer shell. The mixing tubes may extend through the aft plate assembly.
Abstract translation: 本申请提供了一种与燃气涡轮发动机一起使用的燃烧喷嘴。 燃烧喷嘴可以包括多个混合管，围绕混合管的外壳和浮动的后板组件。 浮板组件可以封闭外壳。 混合管可以延伸穿过后板组件。
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公开(公告)号：US11828467B2
公开(公告)日：2023-11-28
申请号：US16731283
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Wei Zhao , Michael John Hughes
IPC: F23R3/28 , B01F25/312
CPC classification number: F23R3/286 , B01F25/31233
Abstract: A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum and that define injection holes therethrough. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. The mixing conduits fluidly couple the high-pressure plenum to the main passage, and the fluid from the fluid plenum is delivered with the high-pressure fluid to the main passage, where the fluids mix before being discharged from an outlet of the main passage. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.
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公开(公告)号：US11668242B2
公开(公告)日：2023-06-06
申请号：US17036745
申请日：2020-09-29
Applicant: General Electric Company
CPC classification number: F02C7/222 , F23D14/583 , F23R3/28 , F05D2240/35 , F05D2250/231
Abstract: Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.
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公开(公告)号：US11614233B2
公开(公告)日：2023-03-28
申请号：US17007108
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Jerome Walter Goike , Clay Thomas Griffis
Abstract: An integrated combustor nozzle includes a combustion liner that extends between an inner liner segment and an outer liner segment along a radial direction. The combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall. An impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement apertures that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel includes an inlet portion that extends from the impingement plate to a collection duct. The impingement panel further includes a plurality of supports spaced apart from one another. The plurality of supports extend between, and are coupled to, the inlet portion, the collection duct, and the impingement plate.
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公开(公告)号：US11460191B2
公开(公告)日：2022-10-04
申请号：US17007076
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: Integrated combustor nozzles and turbomachines are provided. An integrated combustor nozzle includes a cooling insert having a flange. The cooling insert further includes a first wall and a second wall that each define respective passages therein. The first wall and the second wall each extend from an open end defined within the flange to a closed end. The first wall and the second wall each include an impingement side spaced apart from a solid side. Each impingement side defines a plurality of impingement apertures configured to direct coolant from the respective passage towards a side wall of the combustion liner. The cooling inserts further includes a collection passageway that is defined between the solid sides of the first wall and the second wall.
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Patent Agency Ranking
公开(公告)号：US20220065453A1
公开(公告)日：2022-03-03
申请号：US17007068
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.
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公开(公告)号：US11187091B1
公开(公告)日：2021-11-30
申请号：US17136125
申请日：2020-12-29
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: Sealing arrangements and turbomachines are provided. A sealing arrangement includes a transition duct having an upstream end and a downstream end. The transition duct includes an aft frame that circumferentially surrounds the downstream end of the transition duct. A stage one nozzle is spaced apart from the aft frame and defines a gap therebetween. A sealing assembly extends across the gap and is magnetically coupled to both the aft frame and the stage one nozzle. The sealing assembly includes a first magnet coupled to the aft frame and a second magnet coupled to the stage one nozzle. The sealing assembly further includes a shell that is coupled to and at least partially surrounds the first magnet and the second magnet.
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公开(公告)号：US11156362B2
公开(公告)日：2021-10-26
申请号：US16715207
申请日：2019-12-16
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: A combustor with axially staged fuel injection includes an endcover and a fuel injector that extends axially downstream from the endcover. The fuel injector includes a cylindrical shell formed by an outer wall and an inner wall. A first plurality of outlets is circumferentially spaced across the inner wall. A first plurality of premix channels is defined between the outer wall and the inner wall. Each premix channel of the first plurality of premix channels is in fluid communication with a fuel supply, a compressed air supply and a respective outlet of the first plurality of outlets.
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公开(公告)号：US20210324754A1
公开(公告)日：2021-10-21
申请号：US17358691
申请日：2021-06-25
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Klara Sezer , Deepak Trivedi
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
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公开(公告)号：US10605459B2
公开(公告)日：2020-03-31
申请号：US15464419
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , Matthew Troy Hafner , Joseph Vincent Citeno
Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.
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