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11. 发明申请

US20190195130A1 COMBUSTION CHAMBER WITH A HOT COMPRESSED AIR DEFLECTOR, IN PARTICULAR FOR A TURBINE INTENDED FOR PRODUCING ENERGY, IN PARTICULAR ELECTRICAL ENERGY 审中-公开
公开(公告)号：US20190195130A1
公开(公告)日：2019-06-27
申请号：US16328764
申请日：2017-07-11
申请人： IFP Energies nouvelles
发明人： Hubert BAYA TODA , Jean-Baptiste MICHEL , Thomas VALIN , Julien THIRIOT
IPC分类号： F02C7/10 , F23R3/02 , F02K3/00
CPC分类号： F02C7/10 , F02K3/00 , F23R3/02
摘要： The present invention relates to a combustion chamber (10) of a turbine, in particular a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, in particular electrical energy, comprising a casing (12) with an injection means (52) for injecting at least one fuel, and a hot compressed air intake (32), said casing housing a flame tube (22) with a perforated diffuser (26) for the passage of the hot compressed air and the fuel, and a flame stabiliser (54). According to the invention, the chamber comprises an air deflector (36) arranged facing the hot compressed air intake (32) in order to circulate this hot air in a single axial direction from this intake.

12. 发明申请

US20190107054A1 TURBULENCE GENERATING STRUCTURE FOR LINER COOLING ENHANCEMENT AND GAS TURBINE COMBUSTOR HAVING THE SAME 审中-公开
公开(公告)号：US20190107054A1
公开(公告)日：2019-04-11
申请号：US16112807
申请日：2018-08-27
申请人： DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
发明人： Sung Wan PARK , Jong Hwa LEE , In Chan CHOI , Moon Soo CHO
IPC分类号： F02C7/18 , F23R3/00 , F23R3/02
摘要： A turbulence generating structure for liner cooling enhancement is a liner cooling structure applied to a double-structured side portion formed by a liner and a flow sleeve and includes the liner and a first turbulence generator protruding from a surface space of the liner and including a plurality of ribs arranged in an axial direction, each of the ribs comprising blocks arranged at regular distances in the axial direction and interspaced by cooling holes. The ribs include a first set of adjacent ribs separated by a first passage distance, the first passage distance being repeated in a circumferential direction, and a second set of adjacent ribs separated by a second passage distance, the second passage distance being repeated in the circumferential direction, wherein the first and second sets of adjacent ribs have exactly one rib in common, and the first passage distance is greater than the second passage distance.

13. 发明授权

US10125992B2 Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages 有权
公开(公告)号：US10125992B2
公开(公告)日：2018-11-13
申请号：US14540123
申请日：2014-11-13
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： Yasuhiro Wada , Toshifumi Sasao , Takeo Saito
IPC分类号： F23R3/28 , F23D11/40 , F23D14/70 , F23R3/04 , F23R3/10 , F23R3/14 , F23R3/26 , F23R3/02 , F23R3/46
摘要： A gas turbine combustor includes a plurality of fuel nozzles, a premixing plate, and a plurality of annular flow sleeves. The plurality of annular flow sleeves includes an inner annular flow sleeve and an outer annular flow sleeve. The plurality of annular flow sleeves is formed to divide an airflow passage into a plurality of flow passages including an inner and an outer circumferential flow passages. The airflow passage is formed around the plurality of fuel nozzles. The airflow passage extends from an upstream side of the plurality of fuel nozzles to fuel injecting ports of the fuel nozzles. The plurality of annular flow sleeves rectifies a flow of air in each of the flow passages and guiding the flow of air to the fuel injecting ports of the fuel nozzles.

14. 发明授权

US10094573B2 Liner, flow sleeve and gas turbine combustor each having cooling sleeve 有权
公开(公告)号：US10094573B2
公开(公告)日：2018-10-09
申请号：US14590747
申请日：2015-01-06
申请人： DOOSAN HEAVY INDUSTRIES & CONSTRUCTION CO., LTD.
发明人： Young Bong Kim , Jinhoon Choe , Ujin Roh
IPC分类号： F23R3/54 , F02C7/18 , F23R3/00 , F23R3/02
摘要： A gas turbine combustor includes a liner and a transmission piece. Fuel injected in the liner from a fuel nozzle of a gas turbine mixes with compressed air. High temperature gas produced in the liner is transmitted through the transmission piece. The liner is disposed in a flow sleeve in which cooling holes are formed. The transition piece is disposed in a perforated sleeve. Compressed air supplied through holes formed in the perforated sleeve collides with the transition piece. The liner includes a cooling sleeve disposed thereon that divides the air supplied through the cooling holes of the flow sleeve and the compressed air flowing to a space portion between the liner and the flow sleeve.

15. 发明授权

US09840924B2 Gas turbine system with a transition duct having axially extending cooling channels 有权
公开(公告)号：US09840924B2
公开(公告)日：2017-12-12
申请号：US14460878
申请日：2014-08-15
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Matthias Hase , Paul A. Sanders , Vaidyanathan Krishnan
IPC分类号： F01D9/02 , F23R3/00 , F23R3/02 , F23R3/04 , F23R3/06 , F02C7/18 , F23R3/08 , F01D25/12
CPC分类号： F01D9/023 , F01D25/12 , F02C7/18 , F05D2260/202 , F05D2260/204 , F23R3/002 , F23R3/005 , F23R3/02 , F23R3/04 , F23R3/06 , F23R3/08 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045
摘要： A gas turbine system (1) including a burner arrangement having a tubular combustion chamber (5), a turbine (6) and a transition duct (7) connecting the combustion chamber (5) and the turbine (6), wherein the transition duct (7) is provided with an axially extending cooling air channel (11). The transition duct (7) includes a plurality of axially extending cooling air channels, and wherein each cooling air channel (11) is provided with one single inlet (12) opened to the outside of the transition duct (7) and with one single outlet (12) opened to the inside of the transition duct (7).

16. 发明授权

US09810430B2 Conjoined grommet assembly for a combustor 有权
公开(公告)号：US09810430B2
公开(公告)日：2017-11-07
申请号：US14581568
申请日：2014-12-23
申请人： United Technologies Corporation
发明人： Jonathan P. Sandoval , Randolph J. Smith
IPC分类号： F23R3/06 , F23R3/00 , F23R3/02
CPC分类号： F23R3/02 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/03041 , F23R2900/03044 , Y02T50/675
摘要： A conjoined grommet assembly for a combustor wall assembly of a gas turbine engine has a first grommet defining at least in-part a first dilution hole, and a second grommet defining at least in-part a second dilution hole. The first and second dilution holes are spaced closely together such that the first grommet is in contact with the second grommet.

17. 发明授权

US09625152B2 Combustor heat shield for a gas turbine engine 有权
公开(公告)号：US09625152B2
公开(公告)日：2017-04-18
申请号：US14294473
申请日：2014-06-03
申请人： Pratt & Whitney Canada Corp.
发明人： Michael Papple , Robert Sze
IPC分类号： F23R3/00 , F02C7/18 , F23R3/02 , F23R3/10
CPC分类号： F23R3/002 , F02C7/18 , F23R3/02 , F23R3/10 , F23R2900/03043 , F23R2900/03045
摘要： A heat shield for a combustor of a gas turbine engine has a heat shield adapted to be mounted to a combustor wall with a back face of the heat shield in spaced-apart facing relationship with an inner surface of the combustor wall to define an air gap. Rails extend from the back face of the heat shield across the air gap. Grooves are defined in at least one of the rails. The rail grooves are in fluid flow communication with the air gap when the heat shield is mounted to the combustor wall.

18. 发明申请

US20170045228A1 SEQUENTIAL COMBUSTION ARRANGEMENT WITH COOLING GAS FOR DILUTION 审中-公开
标题翻译：连续燃烧装置与冷却气体进行稀释
公开(公告)号：US20170045228A1
公开(公告)日：2017-02-16
申请号：US15234605
申请日：2016-08-11
申请人： ANSALDO ENERGIA SWITZERLAND AG
发明人： Wilhelm REITER , Jürgen Gerhard HOFFMANN
IPC分类号： F23R3/00 , F01D9/04 , F01D25/12 , F01D5/18 , F23R3/36 , F23R3/02
摘要： A gas turbine with a sequential combustor arrangement as disclosed includes a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, a second burner for admixing a second fuel and a second combustion chamber. To assure a temperature profile after the dilution gas admixer and to increase the gas turbine's power and efficiency a vane and/or blade of the turbine has a closed loop cooling. The outlet of the closed loop cooling is connected to the dilution gas admixer for admixing the heated cooling gas leaving the vane and/or blade into the first combustor combustion products.
摘要翻译：具有所公开的顺序燃烧器装置的燃气轮机包括具有第一燃烧器的第一燃烧器，其具有用于在操作期间将第一燃料引入燃烧器入口气体的第一燃烧器和用于燃烧第一燃料的第一燃烧室，用于混合稀释气体的稀释气体混合器涉及离开第一燃烧室的第一燃烧器燃烧产物，用于混合第二燃料和第二燃烧室的第二燃烧器。为了确保在稀释气体混合器之后的温度曲线，并且为了提高燃气轮机的功率和效率，涡轮机的叶片和/或叶片具有闭环冷却。闭环冷却的出口连接到稀释气体混合器，用于将离开叶片和/或叶片的加热的冷却气体混合到第一燃烧器燃烧产物中。

19. 发明申请

US20160356223A1 IGNITER ASSEMBLY FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的IGNITER组件
公开(公告)号：US20160356223A1
公开(公告)日：2016-12-08
申请号：US14731524
申请日：2015-06-05
申请人： GENERAL ELECTRIC COMPANY
发明人： Fei Huang , Christophe J. Day
IPC分类号： F02C7/266 , F23R3/02
CPC分类号： F02C7/266 , F02C7/28 , F05D2220/32 , F05D2230/642 , F05D2240/55 , F05D2260/36 , F05D2260/941 , F05D2260/99 , F23R3/002 , F23R3/02 , F23R3/60 , F23R2900/00012 , Y02T50/672
摘要： In one aspect the present subject matter is directed to an igniter assembly for a gas turbine engine. The igniter assembly includes an outer housing and an igniter tube that extends radially through the outer housing. The igniter tube includes an ignition tip, a nut coupled to the igniter tube and disposed at least partially within the outer housing and a biasing member that extends between an inner surface of a top portion of the outer housing and the nut. A flexible seal extends radially inwardly from a bottom side of the nut and a retention collar is coupled to the igniter tube proximate to the ignition tip. The retention collar is configured to couple to a mounting ring connected to an outer liner of a combustor for the gas turbine engine.
摘要翻译：在一个方面，本主题涉及一种用于燃气涡轮发动机的点火器组件。点火器组件包括外壳体和径向延伸穿过外壳体的点火管。点火管包括点火头，联接到点火管并且至少部分地设置在外壳内的螺母和在外壳的顶部的内表面和螺母之间延伸的偏置构件。柔性密封件从螺母的底侧径向向内延伸，并且保持套环与靠近点火头的点火器管连接。保持套环构造成联接到连接到用于燃气涡轮发动机的燃烧器的外衬套的安装环。

20. 发明授权

US09447973B2 Combustion chamber of a gas turbine 有权
标题翻译：燃气轮机的燃烧室
公开(公告)号：US09447973B2
公开(公告)日：2016-09-20
申请号：US14641797
申请日：2015-03-09
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Carsten Clemen
IPC分类号： F02C1/00 , F23R3/02 , F23R3/00 , F23R3/60
CPC分类号： F23R3/02 , F23R3/002 , F23R3/60 , F23R2900/00017
摘要： A combustion chamber of a gas turbine includes an external combustion chamber wall and at least one shingle that is mounted at the same, as well as a base plate and a combustion chamber head, characterized in that the shingle extends over the entire length of the combustion chamber and is held at its frontal end area, as it appears with respect to the flow direction of the combustion chamber, inside a groove of the base plate, and at its back end area inside a groove of the external combustion chamber wall.
摘要翻译：燃气轮机的燃烧室包括外部燃烧室壁和安装在其上的至少一个瓦块，以及基板和燃烧室头部，其特征在于，所述瓦板在燃烧的整个长度上延伸并且相对于燃烧室的流动方向，在基板的凹槽内部以及在外部燃烧室壁的槽内的后端区域处，保持在其前端区域。

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