专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

11. 发明申请

US20130042627A1 COMBUSTION CHAMBER HEAD OF A GAS TURBINE WITH COOLING AND DAMPING FUNCTIONS 审中-公开
标题翻译：具有冷却和阻尼功能的燃气轮机的燃烧室头部
公开(公告)号：US20130042627A1
公开(公告)日：2013-02-21
申请号：US13587663
申请日：2012-08-16
申请人： Miklos GERENDAS , Sermed SADIG , Jochen BECKER , Jonathan F. CARROTTE , Jochen RUPP
发明人： Miklos GERENDAS , Sermed SADIG , Jochen BECKER , Jonathan F. CARROTTE , Jochen RUPP
IPC分类号： F02C7/18 , F02C7/24
CPC分类号： F23R3/10 , F23M20/005 , F23R2900/00014 , F23R2900/00017 , F23R2900/03042 , F23R2900/03043 , F23R2900/03045
摘要： A combustion chamber head of a gas turbine has a substantially annular combustion chamber outer wall 18 as well as a substantially annular combustion chamber inner wall 42 and several burners 6 distributed around the circumference. The combustion chamber head 5 has an inflow-side wall 13 which together with a wall 14 facing the combustion chamber 7 forms a combustion chamber head volume 15. The inflow-side wall 13 is provided with at least one inflow opening 32, the wall 14 facing the combustion chamber 7 is provided with at least one outflow opening 17 for connecting the combustion chamber head volume 15 to the combustion chamber 7, and at least one cooling air duct 29 is provided in the wall 14 facing the combustion chamber 7. A method for cooling and damping of the combustion chamber head is also disclosed.
摘要翻译：燃气轮机的燃烧室头部具有大致环形的燃烧室外壁18以及围绕圆周分布的大致环形的燃烧室内壁42和多个燃烧器6。燃烧室头部5具有流入侧壁13，其与面向燃烧室7的壁14一起形成燃烧室头部容积15.流入侧壁13设置有至少一个流入开口32，壁14 面对燃烧室7设置有至少一个用于将燃烧室头部体积15连接到燃烧室7的流出开口17，并且至少一个冷却空气管道29设置在面向燃烧室7的壁14中。还公开了用于燃烧室头部的冷却和阻尼的装置。

12. 发明授权

US08099961B2 Gas-turbine combustion chamber wall 有权
标题翻译：燃气轮机燃烧室壁
公开(公告)号：US08099961B2
公开(公告)日：2012-01-24
申请号：US12081573
申请日：2008-04-17
申请人： Miklos Gerendas
发明人： Miklos Gerendas
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/002 , F23R3/007 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A gas-turbine combustion chamber wall for a gas-turbine has a combustion chamber wall 9, on the inner side of which several tiles 10 are arranged, with an interspace 14 being formed between the tiles 10 and the combustion chamber wall 9, into which cooling air is introduced via impingement-cooling holes 8 provided in the combustion chamber wall 9 and from which the cooling air flows into the combustion chamber via effusion-cooling holes 11, 23 provided in the tile 10. The tile 10 includes a surface structure 19, 22 on the side facing the combustion chamber wall 9. The area of the impingement-cooling holes 8 and the area of the effusion-cooling holes 11 do not coincide.
摘要翻译：用于燃气轮机的燃气轮机燃烧室壁具有燃烧室壁9，燃烧室壁9在其内侧布置有多个瓦片10，在瓦片10和燃烧室壁9之间形成有间隙14，燃烧室壁9 冷却空气通过设置在燃烧室壁9中的冲击冷却孔8引入，并且冷却空气通过设置在瓦10中的渗出冷却孔11,23流入燃烧室。瓦10包括表面结构19 22在面向燃烧室壁9的一侧。冲击冷却孔8的面积和积层冷却孔11的面积不重合。

13. 发明申请

US20100192588A1 METHOD FOR THE PROVISION OF A COOLING-AIR OPENING IN A WALL OF A GAS-TURBINE COMBUSTION CHAMBER AS WELL AS A COMBUSTION-CHAMBER WALL PRODUCED IN ACCORDANCE WITH THIS METHOD 审中-公开
标题翻译：用于在气体涡轮机燃烧室中提供冷却空气开放的方法，作为根据本方法生产的燃烧室壁
公开(公告)号：US20100192588A1
公开(公告)日：2010-08-05
申请号：US12697838
申请日：2010-02-01
申请人： Miklos GERENDAS
发明人： Miklos GERENDAS
IPC分类号： F02C3/14
CPC分类号： F01D5/186 , B23K26/389 , B23K2101/001 , F23R2900/00018
摘要： A cooling-air opening in produced in a wall (6) of a gas-turbine combustion chamber using a laser beam. In a first operation, a recess (10c) with a first, larger cross-section is produced from the hot gas side in a partial area of the wall (6) at a shallow angle to the surface. In at least one subsequent operation, a recess (10b, 10a) with a second, smaller cross-section is produced through the entire material of the wall (6) at a shallow angle to the surface while deepening a partial area of the previous recess (10c). A step (12), which is produced between the two recesses in the two operations, is larger than a median coating thickness of a subsequently applied ceramic thermal barrier coating (14).
摘要翻译：在使用激光束的燃气轮机燃烧室的壁（6）中产生的冷却空气开口。在第一操作中，从壁面（6）的部分区域的热气体侧以与表面成浅的角度产生具有第一较大横截面的凹部（10c）。在至少一个随后的操作中，具有第二较小横截面的凹部（10b，10a）通过壁（6）的整个材料以与表面成浅的角度产生，同时使之前的凹部的部分区域变深（10c）。在两个操作中在两个凹部之间产生的台阶（12）大于随后施加的陶瓷热障涂层（14）的中间涂层厚度。

14. 发明申请

US20080264065A1 Gas-turbine combustion chamber wall 有权
标题翻译：燃气轮机燃烧室壁
公开(公告)号：US20080264065A1
公开(公告)日：2008-10-30
申请号：US12081573
申请日：2008-04-17
申请人： Miklos Gerendas
发明人： Miklos Gerendas
IPC分类号： F02C1/00
CPC分类号： F23R3/002 , F23R3/007 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A gas-turbine combustion chamber wall for a gas-turbine has a combustion chamber wall 9, on the inner side of which several tiles 10 are arranged, with an interspace 14 being formed between the tiles 10 and the combustion chamber wall 9, into which cooling air is introduced via impingement-cooling holes 8 provided in the combustion chamber wall 9 and from which the cooling air flows into the combustion chamber via effusion-cooling holes 11, 23 provided in the tile 10. The tile 10 includes a surface structure 19, 22 on the side facing the combustion chamber wall 9. The area of the impingement-cooling holes 8 and the area of the effusion-cooling holes 11 do not coincide.
摘要翻译：用于燃气轮机的燃气轮机燃烧室壁具有燃烧室壁9，燃烧室壁9在其内侧布置有多个瓦片10，在瓦片10和燃烧室壁9之间形成有间隙14，燃烧室壁9 冷却空气通过设置在燃烧室壁9中的冲击冷却孔8引入，并且冷却空气通过设置在瓦10中的溢流冷却孔11,23流入燃烧室。瓦10包括在面向燃烧室壁9的一侧上的表面结构19,22。冲击冷却孔8的面积和积存冷却孔11的面积不一致。

15. 发明授权

US09328926B2 Segmented combustion chamber head 有权
标题翻译：分段燃烧室头
公开(公告)号：US09328926B2
公开(公告)日：2016-05-03
申请号：US13426070
申请日：2012-03-21
申请人： Stefan Penz , Miklos Gerendas , Sermed Sadig
发明人： Stefan Penz , Miklos Gerendas , Sermed Sadig
IPC分类号： F23R3/60 , F23R3/00 , F23R3/10 , F23R3/28
CPC分类号： F23R3/60 , F23R3/002 , F23R3/10 , F23R3/283 , F23R2900/00012 , F23R2900/00014
摘要： A combustion chamber head for a gas turbine, with the gas turbine having a substantially annular outer combustion chamber wall, at least one substantially annular inner combustion chamber wall, and several burners 106 distributed around a circumference of the gas turbine. Several segment-like head segments are arranged over the circumference in equal number to the number of burners and extend in the radial direction between the inner combustion chamber wall and the outer combustion chamber wall and in the circumferential direction between radial planes formed by the burner axes.
摘要翻译：一种用于燃气轮机的燃烧室头部，其中燃气轮机具有基本上环形的外部燃烧室壁，至少一个基本上环形的内部燃烧室壁和分布在燃气轮机周围的多个燃烧器106。在圆周上布置几个段状的头部段，其数量与燃烧器的数量相等，并且在径向方向上在内燃机室壁和外部燃烧室壁之间以及在由燃烧器轴形成的径向平面之间的圆周方向上延伸。

16. 发明授权

US09016067B2 Gas-turbine combustion chamber with a cooling-air supply device 有权
标题翻译：带有冷气供气装置的燃气轮机燃烧室
公开(公告)号：US09016067B2
公开(公告)日：2015-04-28
申请号：US13275805
申请日：2011-10-18
申请人： Miklos Gerendas
发明人： Miklos Gerendas
IPC分类号： F02C1/00 , F23R3/06
CPC分类号： F23R3/06 , F23R2900/03041 , F23R2900/03042 , Y02T50/675
摘要： A gas-turbine combustion chamber has a cooling-air supply device delivering cooling air to a combustion chamber wall 6 to be cooled. The cooling-air supply device includes at least one air-supply duct 8 which, in respect of its flow axis, is arranged vertically to the combustion chamber wall 6, with the air-supply duct 8 being flow-connected to at least one cooling duct 9. The air-supply duct 8 forms a throttle and has a smaller diameter than the cooling duct 9. The cooling duct 9 issues at a shallow angle, relative to its flow axis, to the surface of the combustion chamber wall 6 in a recess 10 of the combustion chamber wall 6, with the cooling duct 9 being designed to impart a swirl to the air flowing through it.
摘要翻译：燃气轮机燃烧室具有向要冷却的燃烧室壁6输送冷却空气的冷却空气供给装置。冷却空气供应装置包括至少一个空气供应管道8，空气供应管道8在其流动轴线上垂直于燃烧室壁6布置，供气管道8与至少一个冷却供气管道8形成节气门并且具有比冷却管道9更小的直径。冷却管道9相对于其流动轴线以相对于燃烧室壁6的表面的浅角度发出燃烧室壁6的凹部10，其中冷却管道9被设计成使流过其的空气产生漩涡。

17. 发明授权

US08646279B2 Segment component in high-temperature casting material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for the manufacture of an annular combustion chamber 有权
标题翻译：用于环形燃烧室的高温铸造材料中的段部件，用于飞机发动机的环形燃烧室，用于制造环形燃烧室的飞机发动机和方法
公开(公告)号：US08646279B2
公开(公告)日：2014-02-11
申请号：US13480696
申请日：2012-05-25
申请人： Karl Schreiber , Miklos Gerendas
发明人： Karl Schreiber , Miklos Gerendas
IPC分类号： F02C3/06 , F02C1/00 , F02G3/00
CPC分类号： F23R3/50 , F23R2900/00018
摘要： The present invention relates to a segment component in high-temperature casting material for an annular combustion chamber of an aircraft engine, characterized by a combustion-chamber wall which in operation shields a fuel flame extending along a burner axis from the environment, with the combustion-chamber wall having a bulge which points in a direction facing away from the burner axis. The invention furthermore relates to an annular combustion chamber, an aircraft engine with an annular combustion chamber as well as a method for the manufacture of an annular combustion chamber.
摘要翻译：本发明涉及一种用于飞机发动机的环形燃烧室的高温铸造材料中的段组件，其特征在于燃烧室壁，其在操作中屏蔽沿燃烧器轴线从环境延伸的燃料火焰与燃烧 - 具有在朝向远离燃烧器轴线的方向上指向的凸起的室壁。本发明还涉及环形燃烧室，具有环形燃烧室的飞机发动机以及制造环形燃烧室的方法。

18. 发明申请

US20120304658A1 Segment component in high-temperature casting material for an annular combustion chamber, annular combustion chamber for an aircraft engine, aircraft engine and method for the manufacture of an annular combustion chamber 有权
标题翻译：用于环形燃烧室的高温铸造材料中的段部件，用于飞机发动机的环形燃烧室，用于制造环形燃烧室的飞机发动机和方法
公开(公告)号：US20120304658A1
公开(公告)日：2012-12-06
申请号：US13480696
申请日：2012-05-25
申请人： Karl SCHREIBER , Miklos GERENDAS
发明人： Karl SCHREIBER , Miklos GERENDAS
IPC分类号： F02G3/00 , B23P11/00
CPC分类号： F23R3/50 , F23R2900/00018
摘要： The present invention relates to a segment component in high-temperature casting material for an annular combustion chamber of an aircraft engine, characterized by a combustion-chamber wall which in operation shields a fuel flame extending along a burner axis from the environment, with the combustion-chamber wall having a bulge which points in a direction facing away from the burner axis. The invention furthermore relates to an annular combustion chamber, an aircraft engine with an annular combustion chamber as well as a method for the manufacture of an annular combustion chamber.
摘要翻译：本发明涉及一种用于飞机发动机的环形燃烧室的高温铸造材料中的段组件，其特征在于燃烧室壁，其在操作中屏蔽沿燃烧器轴线从环境延伸的燃料火焰与燃烧 - 具有在朝向远离燃烧器轴线的方向上指向的凸起的室壁。本发明还涉及环形燃烧室，具有环形燃烧室的飞机发动机以及制造环形燃烧室的方法。

19. 发明授权

US08074453B2 Combustion chamber lining 有权
标题翻译：燃烧室内衬
公开(公告)号：US08074453B2
公开(公告)日：2011-12-13
申请号：US12318259
申请日：2008-12-23
申请人： Miklos Gerendas , Sermed Sadig
发明人： Miklos Gerendas , Sermed Sadig
IPC分类号： F02C1/00
CPC分类号： F23R3/002 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
摘要： A combustion chamber for a gas turbine has a metallic supporting structure 6 and several circumferentially distributed ceramic bodies 2 attached to the supporting structure 6. The ceramic bodies 2 each have a straight hollow tubular profile and are arranged as individual segments At least one hollow metallic body 1 having air-passage holes 5 for the passage of cooling air is provided in each ceramic body 2.
摘要翻译：用于燃气轮机的燃烧室具有金属支撑结构6和附接到支撑结构6的几个周向分布的陶瓷体2.陶瓷体2各自具有直的中空管状轮廓并且被布置为单独的段至少一个中空金属体在每个陶瓷体2中设置有用于冷却空气通过的通气孔5。

20. 发明授权

US09222675B2 Combustion chamber head with holding means for seals on burners in gas turbines 有权
标题翻译：燃烧室头部，带有燃气轮机燃烧器密封件的固定装置
公开(公告)号：US09222675B2
公开(公告)日：2015-12-29
申请号：US13428633
申请日：2012-03-23
申请人： Miklos Gerendas
发明人： Miklos Gerendas
IPC分类号： F23R3/28 , F23R3/00
CPC分类号： F23R3/283 , F23R3/002 , F23R2900/00012
摘要： A combustion chamber head of a gas turbine has a base plate 113 provided with a centric recess 121 in which at least one burner 106 is arranged, with the base plate 113 being connected to walls of the combustion chamber 108 and to a burner seal 116 sealing the burner 106 towards the rim of the recess 121. The burner seal 116 is arranged upstream of the base plate 113 and can be brought into contact with a collar 118 provided on the base plate 113 and forming the rim of the centric recess 121. A holding element 117 of the burner seal 116 is formed as a ring and arranged upstream of the burner seal 116 and engages with at least one projection 114 of the base plate 113 in a tension-free state.
摘要翻译：燃气轮机的燃烧室头具有设置有中心凹部121的基板113，其中布置有至少一个燃烧器106，其中底板113连接到燃烧室108的壁和燃烧器密封件116的密封燃烧器106朝向凹部121的边缘。燃烧器密封件116布置在基板113的上游，并且可以与设置在基板113上的轴环118接触并形成中心凹部121的边缘。燃烧器密封件116的保持元件117形成为环并且布置在燃烧器密封件116的上游，并且以无张力状态与基板113的至少一个突起114接合。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式