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公开(公告)号：US11187415B2
公开(公告)日：2021-11-30
申请号：US15838172
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , James Harper , Matthew Bernard Wilson , Robert Wade Clifford , Yon Han Chong , Benjamin Robert Ryan , Gilbert Otto Kraemer
Abstract: An injection assembly for a gas turbine combustor having a liner defining a combustion zone and a secondary combustion zone and a forward casing circumferentially surrounding at least a portion of the liner is provided. The injection assembly includes a thimble assembly and an injector unit. The thimble assembly, which is mounted to the liner, includes a thimble that extends through a thimble aperture in the liner. The injector unit, which is mounted to and extends through the forward casing, includes an injector blade that extends into the thimble. The injection assembly introduces a flow of fuel into a flow of air flowing through the thimble, such that fuel and air are injected into the secondary combustion zone in a direction transverse to a flow of combustion products from the primary combustion zone.
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公开(公告)号：US11137144B2
公开(公告)日：2021-10-05
申请号：US15838149
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Matthew Bernard Wilson , James Harper , Yon Han Chong , Charlie Edmond Jones
Abstract: A gas turbine combustor includes: a head end comprising a primary fuel nozzle; a liner defining a primary combustion zone proximate the head end and a downstream secondary combustion zone; a forward casing radially outward of and surrounding at least a portion of the liner; and an axial fuel staging system. The axial fuel staging system includes a plurality of fuel injection assemblies. Each fuel injection assembly includes a thimble assembly mounted to the liner, and an injector unit attached to the forward casing. A thimble of the thimble assembly extends through a thimble aperture in the liner. The injector unit extends through the forward casing, such that a portion of the injector unit is disposed within the thimble, and a fuel line fitting is disposed outward of the forward casing. The injector unit introduces fuel into air flowing through the thimble for injection into the secondary combustion zone.
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公开(公告)号：US10415479B2
公开(公告)日：2019-09-17
申请号：US15058418
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Bryan Wesley Romig , Yon Han Chong
Abstract: A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.
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公开(公告)号：US20190186749A1
公开(公告)日：2019-06-20
申请号：US15845338
申请日：2017-12-18
Applicant: General Electric Company
Inventor： James Harper , Neal William Grooms , Yon Han Chong , Benjamin Robert Ryan
CPC classification number: F23R3/286 , F02C3/30 , F05D2240/35 , F05D2260/212 , F23D14/58 , F23R3/343
Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
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公开(公告)号：US20160252018A1
公开(公告)日：2016-09-01
申请号：US15151978
申请日：2016-05-11
Applicant: General Electric Company
Inventor： Yon Han Chong , Dereck Joseph Ouellet
CPC classification number: F02C7/222 , F05D2220/32 , F23D2900/14701 , F23R3/14 , F23R3/286
Abstract: The present application provides a fuel nozzle for use with a flow of air and a flow of fuel in a gas turbine engine. The fuel nozzle may include a plenum, a mixing tube element positioned within the plenum, and an enhanced mixing feature positioned within the mixing tube element so as to promote mixing of the flow of air and the flow of fuel. The enhanced mixing feature may include a swirler.
Abstract translation: 本申请提供了一种与燃气涡轮发动机中的空气流和燃料流一起使用的燃料喷嘴。 燃料喷嘴可以包括集气室，位于集气室内的混合管元件，以及设置在混合管元件内的增强的混合特征，以促进空气流与燃料流的混合。 增强的混合特征可以包括旋流器。
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Patent Agency Ranking
公开(公告)号：US20160178202A1
公开(公告)日：2016-06-23
申请号：US14580315
申请日：2014-12-23
Applicant: General Electric Company
Inventor： Carolyn Ashley Antoniono , Yon Han Chong
IPC: F23R3/10
CPC classification number: F23R3/10 , F23R3/286 , F23R2900/03043 , Y02T50/675
Abstract: A system for utilizing cooling air within a combustor includes a fuel nozzle having an axially extending center body, a burner tube that circumferentially surrounds at least a portion of the center body and a premix passage defined between the center body and the burner tube. The system further includes a combustor cap assembly having a first cooling air plenum defined between a cap plate and a first partitioning plate, a second cooling air plenum defined upstream from the first cooling air plenum between a second partitioning plate and the first partitioning plate, and a tube that provides for fluid communication from the first cooling air plenum, through the second cooling air plenum and through the second partitioning plate. The system provides a method for utilizing the cooling air within the combustor.
Abstract translation: 用于在燃烧室内利用冷却空气的系统包括具有轴向延伸的中心体的燃料喷嘴，周向围绕中心体的至少一部分的燃烧器管以及限定在中心体与燃烧管之间的预混通道。 该系统还包括燃烧器盖组件，其具有限定在盖板和第一分隔板之间的第一冷却空气室，在第二分隔板和第一分隔板之间限定从第一冷却空气室的上游的第二冷却空气室，以及 提供从第一冷却空气室，第二冷却空气室和第二分隔板流体连通的管。 该系统提供了利用燃烧器内的冷却空气的方法。
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公开(公告)号：US11371706B2
公开(公告)日：2022-06-28
申请号：US15845338
申请日：2017-12-18
Applicant: General Electric Company
Inventor： James Harper , Neal William Grooms , Yon Han Chong , Benjamin Robert Ryan
Abstract: The premixed pilot nozzle includes axially elongated tubes defined within a plenum between an outer shroud and a first shroud disposed radially inward of the outer shroud. The tubes extend between tube inlets defined through a forward face and tube outlets defined through an aft face. A second shroud is disposed radially inward of the first shroud, thereby defining a fuel plenum between the first shroud and the second shroud, and the fuel plenum is in communication with a gaseous fuel supply. A fuel injection port, which is positioned between the tube inlet and the tube outlet of each tube, is in fluid communication with the fuel plenum. An air supply configured to fluidly communicate with the tube inlet of each tube. The second shroud defines a second plenum therein, the second plenum being coupled to a source of a non-combustible fluid.
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公开(公告)号：US10816203B2
公开(公告)日：2020-10-27
申请号：US15838193
申请日：2017-12-11
Applicant: General Electric Company
Inventor： Charlie Edmond Jones , James Harper , Matthew Bernard Wilson , Robert Wade Clifford , Yon Han Chong , Gilbert Otto Kraemer
Abstract: A thimble assembly, which directs fluid flow through a combustor liner, includes a thimble boss and a thimble. The thimble boss is mounted an outer surface of the liner and surrounds a liner opening, thus defining a thimble boss passage. The thimble is disposed through the passage and the liner opening. The thimble wall extends from an inlet portion to an outlet of the thimble. The inlet portion has a greater diameter than the outlet and defines an inlet plane and a parallel intermediate plane. A terminal plane, parallel to the intermediate plane, includes an array of points most distant from a corresponding array of points defining the intermediate plane. The thimble wall has a non-uniform length, such that the outlet of the thimble is oriented at an oblique angle relative to the terminal plane. The thimble wall may have an arcuate shape defined as one-fourth of an ellipse.
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公开(公告)号：US10443854B2
公开(公告)日：2019-10-15
申请号：US15188163
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Neal William Grooms , James Harper , Yon Han Chong
Abstract: A premix pilot nozzle is disclosed herein. The premix pilot nozzle includes a nozzle body. The nozzle body includes a forward wall, an aft wall, an outer band that extends between the forward wall and the aft wall and a tip portion that extends axially downstream from the aft wall. The nozzle body further defines a fuel inlet plenum that extends coaxially within the nozzle body, a fuel distribution plenum that is defined within the nozzle body radially outwardly from and in fluid communication with the fuel inlet plenum, a plurality of premix passages that extend helically around the fuel inlet plenum within the fuel distribution plenum and a plurality of air passages annularly arranged around the plurality of premix passages. One or more premix passages of the plurality of premix passages are in fluid communication with the fuel distribution plenum.
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公开(公告)号：US20170363294A1
公开(公告)日：2017-12-21
申请号：US15188190
申请日：2016-06-21
Applicant: General Electric Company
Inventor： Neal William Grooms , James Harper , Yon Han Chong
CPC classification number: F23R3/286 , F02C7/22 , F02C7/222 , F05D2220/32 , F23R3/28 , F23R3/283 , F23R3/343 , F23R2900/03343
Abstract: A premix pilot nozzle and fuel nozzle assembly are disclosed herein. The premix pilot nozzle includes a nozzle body having a forward wall axially spaced from an aft wall and an outer band that extends axially between the forward wall and the aft wall. An air tube extends coaxially within the nozzle body and defines a cooling air plenum within the nozzle body. A fuel tube extends coaxially within the nozzle body and circumferentially surrounds the air tube so as to define a fuel inlet plenum therebetween. A fuel distribution plenum is defined within the nozzle body and is in fluid communication with the fuel inlet plenum. The nozzle body further includes a plurality of premix tubes. Each premix tube extends helically around the fuel tube within the fuel distribution plenum. One or more of the premix tubes is in fluid communication with the fuel distribution plenum.
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