公开(公告)号：US20160091208A1

公开(公告)日：2016-03-31

申请号：US14868782

申请日：2015-09-29

Applicant: ALSTOM Technology Ltd

Inventor： Ulrich RATHMANN ,  Naresh ALURI

IPC: F23R3/60 ,  F23R3/00

CPC classification number: F23R3/60 ,  F05D2230/642 ,  F05D2240/14 ,  F05D2240/35 ,  F05D2260/30 ,  F05D2260/941 ,  F05D2300/50212 ,  F23R3/002 ,  F23R3/007 ,  F23R3/28 ,  F23R3/283 ,  F23R3/42 ,  F23R3/425 ,  F23R3/44 ,  F23R3/46 ,  F23R3/50 ,  F23R3/52 ,  F23R3/54 ,  F23R3/58 ,  F23R2900/00005 ,  F23R2900/00012 ,  F23R2900/00017 ,  F23R2900/03342

Abstract: A combustor arrangement with a front panel, a combustor liner, and a carrier structure element is provided for carrying the front panel and the combustor liner, wherein the combustor arrangement further includes a fastening system for connecting the front panel, the combustor liner, and the carrier structure element to one another. The fastening system includes at least one elastic connection element, the latter being fixedly connected to the carrier structure element and extending therefrom to the combustor liner and to the front panel. The elastic connection element is further fixedly connected to the combustor liner and/or the front panel such as to clamp the front panel, the combustor liner, and the carrier structure element to one another in a substantially fluid tight manner.

Abstract translation: 提供具有前面板，燃烧器衬套和载体结构元件的燃烧器装置，用于承载前面板和燃烧器衬套，其中燃烧器装置还包括紧固系统，用于连接前面板，燃烧器衬套和 载体结构元件彼此。 紧固系统包括至少一个弹性连接元件，弹性连接元件固定地连接到承载结构元件并从其延伸到燃烧器衬套和前面板。 弹性连接元件进一步固定地连接到燃烧器衬套和/或前面板，以便以基本上流体密封的方式将前面板，燃烧器衬套和载体结构元件彼此夹紧。

公开(公告)号：US20140013764A1

公开(公告)日：2014-01-16

申请号：US13937482

申请日：2013-07-09

Applicant: ALSTOM Technology Ltd

Inventor： Fernando BIAGIOLI ,  Naresh ALURI ,  Madhavan Narasimhan POYYAPAKKAM ,  Jan CERNY

IPC: F23R3/14

CPC classification number: F23R3/14 ,  F23C7/004 ,  F23R3/286

Abstract: An axial swirler for a gas turbine burner includes a vane ring with a plurality of swirler vanes circumferentially distributed around a swirler axis. Each of the swirler vanes includes a trailing edge. In order to achieve a controlled distribution of the exit flow velocity profile and/or the fuel equivalence ratio in the radial direction. The trailing edge is discontinuous with the trailing edge having a discontinuity at a predetermined radius.

Abstract translation: 用于燃气涡轮燃烧器的轴向旋流器包括具有围绕旋流器轴线周向分布的多个旋流器叶片的叶片环。 每个旋流器叶片包括后缘。 为了实现径向方向上的出口流速分布和/或燃料当量比的受控分布。 后缘是不连续的，后缘具有预定半径的不连续性。

公开(公告)号：US20160091206A1

公开(公告)日：2016-03-31

申请号：US14868842

申请日：2015-09-29

Applicant: ALSTOM Technology Ltd

Inventor： Ulrich RATHMANN ,  Naresh ALURI ,  Kaspar LOEFFEL ,  Michael HUBER

IPC: F23R3/00 ,  F23R3/06

CPC classification number: F23R3/002 ,  F23R3/005 ,  F23R3/007 ,  F23R3/06 ,  F23R3/10 ,  F23R3/283 ,  F23R3/42 ,  F23R3/44 ,  F23R3/46 ,  F23R3/50 ,  F23R3/54 ,  F23R3/60 ,  F23R2900/00017 ,  F23R2900/00018 ,  F23R2900/03041 ,  F23R2900/03342

Abstract: A front panel for a combustor has a hot side and a cold side and at least one reception adapted for receiving a combustor part. The front panel has a double-wall design with a hot-side wall and a cold-side wall. The hot-side wall defines a hot-side downstream surface of the front panel. The cold-side wall defines a cold-side upstream surface of the front panel. The hot-side wall and the cold-side wall are axially spaced from one another, extend parallel to one another, and are connected to one another by an outer side wall.

Abstract translation: 用于燃烧器的前面板具有热侧和冷侧以及至少一个适于容纳燃烧器部分的接收器。 前面板具有双壁设计，具有热侧壁和冷侧壁。 热侧壁限定前面板的热侧下游表面。 冷侧壁限定前面板的冷侧上游表面。 热侧壁和冷侧壁彼此轴向间隔开，彼此平行延伸，并且通过外侧壁彼此连接。

公开(公告)号：US20140007578A1

公开(公告)日：2014-01-09

申请号：US13936310

申请日：2013-07-08

Applicant: ALSTOM Technology Ltd

Inventor： Franklin Marie GENIN ,  Naresh ALURI ,  Jan CERNY ,  Adnan EROGLU ,  Ennio PASQUALOTTO

IPC: F02C7/22

CPC classification number: F02C7/22 ,  F02C3/14 ,  F02C6/003 ,  F23C6/047 ,  F23C2201/301 ,  F23C2201/40 ,  F23C2900/07002 ,  F23M20/005 ,  F23R3/286 ,  F23R3/346 ,  F23R3/46 ,  F23R2900/00014 ,  F23R2900/03341

Abstract: The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

Abstract translation: 本发明涉及一种包括燃气轮机的燃气轮机燃烧系统。 燃气轮机包括至少一个压缩机，至少一个用于产生工作气体的燃烧室，其中燃烧室被连接以从压缩机接收压缩空气，至少一个涡轮连接以接收来自燃烧室的工作气体。 燃烧室由单独的罐式燃烧器组成或包括布置在环形罐结构中的多个罐式燃烧器，其中罐式燃烧器具有至少一个预混燃烧器。 混合物的点火开始于预混燃烧器出口，并且火焰通过回流区在预混燃烧器出口的区域中稳定。 罐式燃烧器包括多个预混合燃烧器，其均匀地排列或在罐内燃烧器内至少分成两组。