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1. 发明授权

US06901756B2 Device for the injection of fuel into the flow wake of swirler vanes 失效
标题翻译：用于将燃料喷射到旋流器叶片的流动尾流中的装置
公开(公告)号：US06901756B2
公开(公告)日：2005-06-07
申请号：US10287718
申请日：2002-11-05
申请人： Miklos Gerendas , Thomas Doerr
发明人： Miklos Gerendas , Thomas Doerr
IPC分类号： F23R3/14 , F23R3/28
CPC分类号： F23R3/14 , F23R3/28
摘要： A device for the injection of fuel into the combustion chamber of a gas turbine includes at least one swirler (1) arranged in an air path with at least one swirler vane (2) and with at least one fuel injection nozzle (3), wherein the fuel injection nozzle (3) is arranged in a wake area of the swirler vane (2) and is separate from the swirler vane (2).
摘要翻译：用于将燃料喷射到燃气涡轮机的燃烧室中的装置包括至少一个与至少一个旋流器叶片（2）和至少一个燃料喷射喷嘴（3）在空气路径中布置的旋流器（1），其中燃料喷射喷嘴（3）布置在旋流器叶片（2）的尾流区域中并且与旋流器叶片（2）分离。

2. 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。

3. 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。

4. 发明授权

US08938970B2 Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall 有权
标题翻译：燃气轮机燃烧室具有用于冷却燃烧室壁的起动膜
公开(公告)号：US08938970B2
公开(公告)日：2015-01-27
申请号：US12815829
申请日：2010-06-15
申请人： Miklos Gerendas , Sermed Sadig
发明人： Miklos Gerendas , Sermed Sadig
IPC分类号： F02C1/00 , F23R3/06
CPC分类号： F23R3/06 , F23R3/10 , F23R2900/03042
摘要： A gas turbine combustion chamber has a starter film for cooling the combustion chamber wall, and a combustion chamber head, into which cooling air can be introduced and which is confined to the combustion chamber by a heat shield (5). A base plate (2) is arranged at a certain distance from the heat shield (5) and the base plate (2) is provided with several openings (6) in its rim area for passing the cooling air. Center axes (17) of the openings (6) are inclined at a shallow angle (α) relative to the combustion chamber wall (4).
摘要翻译：燃气轮机燃烧室具有用于冷却燃烧室壁的起动膜和燃烧室头部，其中可以通过隔热罩（5）将冷却空气引入其中并被限制在燃烧室中。基板（2）与隔热板（5）隔开一定距离，基板（2）在其边缘区域设有多个开口（6），用于通过冷却空气。开口（6）的中心轴（17）相对于燃烧室壁（4）以较小的角度（α）倾斜。

5. 发明授权

US08677757B2 Combustion chamber head of a gas turbine 失效
标题翻译：燃气轮机的燃烧室头部
公开(公告)号：US08677757B2
公开(公告)日：2014-03-25
申请号：US12774214
申请日：2010-05-05
申请人： Sermed Sadig , Miklos Gerendas
发明人： Sermed Sadig , Miklos Gerendas
IPC分类号： F02C1/00 , F02C7/24
CPC分类号： F23R3/04 , F23M20/005 , F23R3/283 , F23R2900/00014 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043
摘要： A combustion chamber head of a gas turbine has a confinement enclosing a dampening volume (207) and including a combustion chamber-opposite confinement (206) and a combustion chamber-side confinement (210). The combustion chamber-side confinement (210) is provided as perforated wall (210). In the edge area of the combustion chamber-side confinement (210), cooling air can be routed onto the combustion chamber-side confinement (210) via recesses (203) in the confinement (206). This cooling air, which flows along the combustion chamber-side confinement (210), crosses the cooling air flow through the perforated wall (210) in the combustion chamber (101) without mixing with the latter, as both are separated by walls.
摘要翻译：燃气轮机的燃烧室头部具有封闭阻尼体积（207）并包括燃烧室相对限制件（206）和燃烧室侧限制件（210）的限制。燃烧室侧限制（210）设置为穿孔壁（210）。在燃烧室侧限制（210）的边缘区域中，冷却空气可以通过限制（206）中的凹槽（203）被引导到燃烧室侧限制件（210）上。沿着燃烧室侧限制（210）流动的这种冷却空气与通过燃烧室（101）中的穿孔壁（210）的冷却空气流相交而不与后者混合，因为两者都被壁分开。

6. 发明授权

US07059133B2 Dilution air hole in a gas turbine combustion chamber with combustion chamber tiles 失效
标题翻译：具有燃烧室砖的燃气轮机燃烧室内的稀释气孔
公开(公告)号：US07059133B2
公开(公告)日：2006-06-13
申请号：US10400553
申请日：2003-03-28
申请人： Miklos Gerendas
发明人： Miklos Gerendas
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/06 , F23R3/002 , F23R2900/03041
摘要： A gas turbine combustion chamber includes combustion chamber tiles 3 attached to a supporting structure 6 of the gas turbine combustion chamber, with each tile possessing at least one dilution air hole 4 which is flush with a dilution air hole of the supporting structure 6, wherein a diameter of the dilution air hole of the supporting structure 6 is considerably larger than a diameter 14 of the dilution air hole 4 of the combustion chamber tile 3.
摘要翻译：燃气轮机燃烧室包括安装在燃气轮机燃烧室的支撑结构6上的燃烧室瓦3，每个瓦片具有与支撑结构6的稀释气孔齐平的至少一个稀释气孔4，其中支撑结构6的稀释气孔的直径比燃烧室瓦3的稀释气孔4的直径14大得多。

7. 发明授权

US06901757B2 Heat shield arrangement with sealing element 失效
标题翻译：带有密封元件的隔热罩
公开(公告)号：US06901757B2
公开(公告)日：2005-06-07
申请号：US10291425
申请日：2002-11-12
申请人： Miklos Gerendas
发明人： Miklos Gerendas
IPC分类号： F23M5/00 , F23M5/04 , F23R3/00 , F02C7/24
CPC分类号： F23M5/04 , F23M5/00 , F23M2900/05005 , F23R3/002 , F23R2900/00012
摘要： A heat shield arrangement includes several tiles 1 and several fasteners 6 for attaching the tiles at a spaced distance to a wall 2 to form an interspace 4 between the wall and the tiles which can be supplied with cooling air. At least one sealing element 3 is positioned between adjacent tiles 1 to provide a seal between rims 5 of the adjacent tiles 1. The rims 5 of the tiles 1 which are to be sealed are maintained at a spaced distance from the wall 2 by the fasteners 6 and the sealing element 3 is positioned remotely from the wall 2 and in abutment with the rims 5 of the tiles 1, with the sealing element 3 being allowed to float over the rims 5.
摘要翻译：隔热罩装置包括多个瓦片1和几个紧固件6，用于将瓦片以间隔距离连接到壁2，以在壁和瓦片之间形成间隙4，间隙4可以被供应冷却空气。至少一个密封元件3定位在相邻的瓦片1之间，以在相邻的瓦片1的边缘5之间提供密封。待密封的瓦1的边缘5通过紧固件6保持与壁2间隔开的距离，并且密封元件3远离壁2定位并且与瓦1的边缘5邻接。密封元件3被允许在边缘5上浮动。

8. 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。

9. 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。

10. 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。

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