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公开(公告)号：US09328926B2
公开(公告)日：2016-05-03
申请号：US13426070
申请日：2012-03-21
Applicant: Stefan Penz , Miklos Gerendas , Sermed Sadig
Inventor： Stefan Penz , Miklos Gerendas , Sermed Sadig
CPC classification number: F23R3/60 , F23R3/002 , F23R3/10 , F23R3/283 , F23R2900/00012 , F23R2900/00014
Abstract: 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.
Abstract translation: 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 。
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2.发明授权Gas-turbine combustion chamber with starter film for cooling the combustion chamber wall 有权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
Applicant: Miklos Gerendas , Sermed Sadig
Inventor： Miklos Gerendas , Sermed Sadig
CPC classification number: F23R3/06 , F23R3/10 , F23R2900/03042
Abstract: 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).
Abstract translation: 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。
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公开(公告)号：US08677757B2
公开(公告)日：2014-03-25
申请号：US12774214
申请日：2010-05-05
Applicant: Sermed Sadig , Miklos Gerendas
Inventor： Sermed Sadig , Miklos Gerendas
CPC classification number: F23R3/04 , F23M20/005 , F23R3/283 , F23R2900/00014 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043
Abstract: 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.
Abstract translation: 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。
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Patent Agency Ranking
公开(公告)号：US08074453B2
公开(公告)日：2011-12-13
申请号：US12318259
申请日：2008-12-23
Applicant: Miklos Gerendas , Sermed Sadig
Inventor： Miklos Gerendas , Sermed Sadig
IPC: F02C1/00
CPC classification number: F23R3/002 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US08281598B2
公开(公告)日：2012-10-09
申请号：US12379380
申请日：2009-02-19
Applicant: Miklos Gerendas , Sermed Sadig
Inventor： Miklos Gerendas , Sermed Sadig
CPC classification number: F23R3/007 , F23D2212/10 , F23M5/04 , F23R3/002 , F23R3/50
Abstract: A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.
Abstract translation: 燃气轮机燃烧室包括基本上为圆柱形的火焰管2，其由陶瓷材料制成，并周向地分成若干周向元件10,11,12。
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公开(公告)号：US20110005233A1
公开(公告)日：2011-01-13
申请号：US12774214
申请日：2010-05-05
Applicant: Sermed Sadig , Miklos Gerendas
Inventor： Sermed Sadig , Miklos Gerendas
IPC: F02C3/14
CPC classification number: F23R3/04 , F23M20/005 , F23R3/283 , F23R2900/00014 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043
Abstract: 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.
Abstract translation: 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。
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公开(公告)号：US20090235667A1
公开(公告)日：2009-09-24
申请号：US12379380
申请日：2009-02-19
Applicant: Miklos Gerendas , Sermed Sadig
Inventor： Miklos Gerendas , Sermed Sadig
IPC: F23R3/42
CPC classification number: F23R3/007 , F23D2212/10 , F23M5/04 , F23R3/002 , F23R3/50
Abstract: A gas turbine combustion chamber includes an essentially cylindrical flame tube 2, which is made of a ceramic material and circumferentially divided into several circumferential elements 10, 11, 12.
Abstract translation: 燃气轮机燃烧室包括基本上为圆柱形的火焰管2，其由陶瓷材料制成，并周向地分成若干周向元件10,11,12。
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公开(公告)号：US20090193810A1
公开(公告)日：2009-08-06
申请号：US12318259
申请日：2008-12-23
Applicant: Miklos Gerendas , Sermed Sadig
Inventor： Miklos Gerendas , Sermed Sadig
IPC: F02C1/00
CPC classification number: F23R3/002 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03042 , F23R2900/03044
Abstract: 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.
Abstract translation: 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。
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