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1. 发明公开

US20230288066A1 COMBUSTION LINER 审中-公开
公开(公告)号：US20230288066A1
公开(公告)日：2023-09-14
申请号：US18320529
申请日：2023-05-19
申请人： General Electric Company
发明人： Pradeep Naik , Shai Birmaher , Saket Singh , Krishnendu Chakraborty
IPC分类号： F23R3/06 , F23R3/04 , F23R3/00
CPC分类号： F23R3/06 , F23R3/045 , F23R3/002 , F23R2900/03043
摘要： A liner for a combustor in a gas turbine engine and a related method. The liner includes a liner body having a cold side and a hot side. The liner includes a dilution array having a plurality of dilution passages, each dilution passage of the plurality of dilution passages having a concatenated geometry repeating in a predetermined pattern and extending circumferentially around the liner body. The dilution passage integrates a first dilution air flow flowing through the dilution passage from the cold side to the hot side and a second dilution air flow flowing through the dilution passage from the cold side to the hot side into an integrated dilution air flow and injects the integrated dilution air flow into a core primary combustion zone of the combustor to attain a predetermined combustion state of the combustor. The dilution array is repeated along an axial length of the liner body.

2. 发明授权

US11754287B2 Fuel injector assembly for a turbine engine 有权
公开(公告)号：US11754287B2
公开(公告)日：2023-09-12
申请号：US17018561
申请日：2020-09-11
申请人： Raytheon Technologies Corporation
发明人： Lawrence A. Binek , Timothy S. Snyder
IPC分类号： F23R3/30 , F23R3/04
CPC分类号： F23R3/30 , F23R3/045 , F05D2220/323
摘要： An apparatus is provided for a turbine engine. This apparatus includes a fuel conduit and a fuel nozzle. The fuel conduit includes a supply passage. The fuel nozzle includes a nozzle passage, an end wall and a nozzle orifice. The nozzle passage has a longitudinal centerline and extends longitudinally through the fuel nozzle along the longitudinal centerline from the end wall to the nozzle orifice. The nozzle passage is configured with a convergent portion and a throat portion. The nozzle passage converges radially inward towards the longitudinal centerline as the convergent portion extends longitudinally along the longitudinal centerline away from the end wall and towards the throat portion. The supply passage is fluidly coupled to the nozzle passage by a fuel aperture in the end wall. A centerline of the fuel aperture is angularly and laterally offset from the longitudinal centerline.

3. 发明公开

US20230250957A1 COMBUSTOR NOZZLE AND GAS TURBINE INCLUDING THE SAME 审中-公开
公开(公告)号：US20230250957A1
公开(公告)日：2023-08-10
申请号：US18161568
申请日：2023-01-30
申请人： DOOSAN ENERBILITY CO., LTD.
发明人： Han Jin JEONG , Seong Hwi JO , Chea Hong CHOI
IPC分类号： F23R3/28 , F23R3/04 , F02C7/22
CPC分类号： F23R3/286 , F02C7/222 , F23R3/045
摘要： Disclosed herein is a combustor nozzle that includes at least one cluster composed of a plurality of tubes through which air and fuel flow, wherein the cluster includes a main tube through which air and fuel flow, a sub-tube disposed to surround the main tube, a fuel supply part positioned inside the main tube to supply fuel, and a plurality of wing parts protruding radially from the fuel supply part, each having one end coupled to the fuel supply part and the other end in contact with an inner peripheral surface of the main tube.

4. 发明授权

US11680526B2 Gas turbine system 有权
公开(公告)号：US11680526B2
公开(公告)日：2023-06-20
申请号：US17692257
申请日：2022-03-11
申请人： HONDA MOTOR CO., LTD.
发明人： Shunichiro Tamada
IPC分类号： F02C7/14 , F23R3/04 , F23R3/16
CPC分类号： F02C7/14 , F23R3/045 , F23R3/16
摘要： The gas turbine system includes: a first gas turbine element 2; a second gas turbine element 3; a single combustor 4; a first supply pipe 61 which connects the first compressor 21 to the combustor 4; a second supply pipe 62 which connects the second compressor 31 to the combustor 4; a first discharge pipe 66 and a second discharge pipe 67 which discharge a fluid discharged from the combustor 4 to the outside; and a heat exchanger 5. The heat exchanger 5 allows each of a low-temperature fluid flowing through the first supply pipe 61 and the second supply pipe 62 and a high-temperature fluid flowing through the first discharge pipe 66 and the second discharge pipe 67 to flow therethrough and exchanges heat between the low-temperature fluid and the high-temperature fluid.

5. 发明申请

US20180266330A1 Gas Turbine with Extraction-Air Conditioner 审中-公开
公开(公告)号：US20180266330A1
公开(公告)日：2018-09-20
申请号：US15460301
申请日：2017-03-16
申请人： General Electric Company
发明人： Stanley Kevin Widener
IPC分类号： F02C9/18 , F02C3/04 , F02C7/18 , F23R3/04 , F23R3/26
CPC分类号： F02C9/18 , F02C6/08 , F02C7/18 , F05D2260/601 , F23R3/045 , F23R3/06 , F23R3/26
摘要： The present disclosure is directed to a gas turbine including a primary compressor, a combustion section disposed downstream from the primary compressor and a turbine disposed downstream from the combustion section. A pipe assembly defines an extraction-air circuit between an extraction port of the primary compressor and an inlet port of the turbine. The gas turbine further includes an extraction-air conditioning system. The extraction-air conditioning system includes a secondary compressor having an inlet and an outlet. Both the inlet and the outlet are fluidly coupled to the extraction-air circuit at respective locations defined along the pipe assembly between the extraction port of the primary compressor and the inlet port of the turbine.

6. 发明授权

US10072846B2 Trapped vortex cavity staging in a combustor 有权
公开(公告)号：US10072846B2
公开(公告)日：2018-09-11
申请号：US14791684
申请日：2015-07-06
申请人： General Electric Company
发明人： Sarah Marie Monahan , Narendra Digamber Joshi , Venkat Eswarlu Tangirala , Matthieu Marc Masquelet
IPC分类号： F23R3/28 , F23R3/34 , F23C5/08 , F23R3/58 , F23R3/12 , F23R3/04 , F23C5/00 , F23R3/42 , F23C5/32 , F23R3/02 , F23R3/10 , F23C5/24 , F23R3/06
CPC分类号： F23R3/286 , F05D2240/35 , F23C5/00 , F23C5/08 , F23C5/10 , F23C5/24 , F23C5/32 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/10 , F23R3/12 , F23R3/34 , F23R3/346 , F23R3/42 , F23R3/58 , F23R2900/00015 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： A gas turbine engine and combustor assembly including a combustor liner defining therein a combustion chamber for the downstream flow of a main fluid. At least two axially spaced apart annular trapped vortex cavities are located on the combustor liner and staged axially and radially spaced apart. A cavity opening is located at a radially inner end of each of the at least two annular trapped vortex cavities. A plurality of injectors are configured tangentially relative to circular radially outer wall extending between an aft wall and a forward wall of each cavity to provide for an injection of air and fuel to form an annular rotating trapped vortex of a fuel and air mixture within a respective annular trapped vortex cavity. The annular rotating trapped vortex of the fuel and air mixture at the cavity openings is substantially perpendicular to the downstream flow of the main fluid.

7. 发明申请

US20160327271A1 COOLED GROMMET FOR A COMBUSTOR WALL ASSEMBLY 审中-公开
标题翻译：冷凝水龙头组合
公开(公告)号：US20160327271A1
公开(公告)日：2016-11-10
申请号：US15108148
申请日：2014-12-24
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Jonathan P. Sandoval
IPC分类号： F23R3/04 , F02C3/14 , F23R3/50 , F23R3/00
CPC分类号： F23R3/045 , F02C3/14 , F05D2220/32 , F23R3/002 , F23R3/005 , F23R3/06 , F23R3/50 , F23R2900/03041 , F23R2900/03043 , Y02T50/675
摘要： A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.
摘要翻译：燃烧器壁组件具有隔热罩和支撑壳体，其间限定有冷却腔。索环通常包括限定与冷却腔隔离的稀释孔的壁，以及从壁径向向外突出并进入冷却腔的凸缘。凸缘是与隔热罩的空间，并且在壁和隔热罩之间限定了冷却通道，该隔热件与空腔连通，用于冷却靠近燃烧室的壁。

8. 发明申请

US20160230995A1 Gas Turbine Combustor and Steam Injected Gas Turbine 审中-公开
标题翻译：燃气轮机燃烧器和蒸汽注入燃气轮机
公开(公告)号：US20160230995A1
公开(公告)日：2016-08-11
申请号：US15015843
申请日：2016-02-04
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Tomomi KOGANEZAWA
IPC分类号： F23R3/00 , F02C3/30 , F23R3/04
CPC分类号： F23R3/002 , F02C3/30 , F02C3/305 , F23L7/005 , F23L2900/07009 , F23R3/04 , F23R3/045 , F23R3/06
摘要： A gas turbine combustor includes a tubular combustion liner that has a plurality of dilution holes disposed circumferentially at a section downstream in a direction of flow of combustion gas, a combustor casing that encloses the combustion liner, a liner flow sleeve disposed between the combustion liner and the combustor casing, to define with the combustion liner an air flow path through which compressed air flows, the liner flow sleeve having a plurality of steam injection holes, and a steam distribution mechanism disposed on an outer peripheral side of the liner flow sleeve. The steam distribution mechanism distributes received injection steam to the steam injection holes. At least some of the steam injection holes are disposed so to face at least some of the dilution holes. The steam injection holes facing the respective dilution holes are each formed so as to spurt the injection steam toward the corresponding dilution hole.
摘要翻译：燃气轮机燃烧器包括管状燃烧衬套，其具有沿燃烧气体流动方向下游的部分周向设置的多个稀释孔，封闭燃烧衬套的燃烧器壳体，设置在燃烧衬套和燃烧衬套之间的衬套流动套筒燃烧器壳体与燃烧衬套一起限定压缩空气流动的空气流动通道，衬套流动套管具有多个蒸汽喷射孔，以及设置在衬套流动套管的外周侧上的蒸汽分配机构。蒸汽分配机构将接收到的注入蒸汽分配到蒸汽注入孔。至少一些蒸汽喷射孔被设置为面对至少一些稀释孔。面对各个稀释孔的蒸汽注入孔各自形成为将喷射蒸汽喷射到相应的稀释孔。

9. 发明申请

US20160054003A1 COMBUSTOR CAP ASSEMBLY 有权
公开(公告)号：US20160054003A1
公开(公告)日：2016-02-25
申请号：US14462639
申请日：2014-08-19
申请人： General Electric Company
发明人： William Francis Carnell, JR. , Carolyn Ashley Antoniono , Jonathan Hale Kegley , Yon Han Chong
IPC分类号： F23R3/28 , F02C7/18
CPC分类号： F23R3/283 , F02C7/18 , F05B2260/201 , F05B2260/205 , F05D2240/126 , F05D2260/201 , F05D2260/205 , F23R3/002 , F23R3/04 , F23R3/045 , F23R3/10 , F23R3/16 , F23R3/26 , F23R3/286 , F23R3/54 , F23R3/60 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , Y02T50/675
摘要： A combustor cap assembly includes an impingement plate coupled to an annular shroud and a cap plate which is coupled to the impingement plate and forms an impingement air plenum therebetween. The cap assembly further includes a flow conditioning plate which is coupled to a forward end portion of the shroud. The flow conditioning plate includes an inner band portion, an outer band portion and an annular portion which extends radially therebetween. The annular portion includes upstream side, a downstream side and a plurality of flow conditioning passages which provide for fluid communication through the upstream and downstream sides. The inner band portion of the flow conditioning plate at least partially defines an exhaust channel. The exhaust channel is in fluid communication with the impingement air plenum and an exhaust outlet. The exhaust outlet is positioned to route cooling air from the impingement air plenum into an annular flow passage defined within a combustor.
摘要翻译：燃烧器盖组件包括联接到环形护罩的冲击板和联接到冲击板的盖板，并在其间形成冲击空气增压室。盖组件还包括流动调节板，其联接到护罩的前端部分。流量调节板包括内带部分，外带部分和径向地延伸的环形部分。环形部分包括上游侧，下游侧和多个流动调节通道，其提供通过上游侧和下游侧的流体连通。流量调节板的内带部分至少部分地限定排气通道。排气通道与冲击空气通风室和排气出口流体连通。排气出口被定位成将冷却空气从冲击空气压力通道引导到限定在燃烧器内的环形流动通道中。

10. 发明申请

US20150362190A1 COMBUSTOR ASSEMBLY WITH CHUTES 有权
标题翻译： COMBUSTOR大会与CHUTES
公开(公告)号：US20150362190A1
公开(公告)日：2015-12-17
申请号：US14734814
申请日：2015-06-09
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Todd S. Taylor , Jack D. Petty , Kenneth W. Froemming
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F23R3/02 , F23R3/04 , F23R3/045 , F23R3/06 , F23R3/16 , F23R3/50 , F23R2900/00017 , F23R2900/03041 , Y02T50/675 , Y10T29/49236
摘要： A combustor for use in a gas turbine engine includes a chute and a combustion liner defining a combustion chamber and a chute-receiving aperture that extends through the combustion liner. The chute extends through the chute-receiving aperture of the combustion liner and defines a passageway sized to convey air from an environment outside the combustion chamber through the combustion liner into the combustion chamber.
摘要翻译：用于燃气涡轮发动机的燃烧器包括限定燃烧室的滑槽和燃烧衬套以及延伸穿过燃烧衬套的滑槽接收孔。滑槽延伸穿过燃烧衬套的滑槽接收孔，并且限定了通道，该通道的尺寸设置成将空气从燃烧室外的环境传送通过燃烧衬套进入燃烧室。

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