公开(公告)号：US09810152B2

公开(公告)日：2017-11-07

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: F23R3/34 ,  F02C7/22 ,  F23C6/04 ,  F23R3/28 ,  F23R3/46 ,  F02C3/14 ,  F02C6/00 ,  F23M20/00

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.

公开(公告)号：US20150000282A1

公开(公告)日：2015-01-01

申请号：US14488652

申请日：2014-09-17

Applicant: ALSTOM Technology Ltd

Inventor： Franklin Marie GENIN ,  Naresh Aluri ,  Mirko Ruben Bothien

IPC: F23R3/00

CPC classification number: F23R3/002 ,  F23M20/005 ,  F23R2900/00014 ,  Y10T29/49

Abstract: The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

Abstract translation: 阻尼器装置包括两个同心的中空形状，每个具有壁，其中壁之间形成环形体积。 阻尼器装置还包括用于在对应的一个或多个接触点处连接到燃烧室的一个或多个颈部。 一个或多个颈部连接到环形容积。

公开(公告)号：US09618206B2

公开(公告)日：2017-04-11

申请号：US14488652

申请日：2014-09-17

Applicant: ALSTOM Technology Ltd

Inventor： Franklin Marie Genin ,  Naresh Aluri ,  Mirko Ruben Bothien

IPC: F23R3/00 ,  F23M20/00

CPC classification number: F23R3/002 ,  F23M20/005 ,  F23R2900/00014 ,  Y10T29/49

Abstract: The damper arrangement include two concentric hollow shapes, each having a wall, wherein the walls form an annular volume therebetween. The damper arrangement further includes one or more necks for connecting to a combustion chamber at corresponding one or more contact points. The one or more necks are connected to the annular volume.

公开(公告)号：US10422535B2

公开(公告)日：2019-09-24

申请号：US14260617

申请日：2014-04-24

Applicant: ALSTOM Technology Ltd

Inventor： Klaus Knapp ,  Naresh Aluri ,  Nicolas Tran ,  Ulrich Rathmann ,  Franklin Marie Genin

IPC: F23R3/28 ,  F23R3/14 ,  F23R3/34 ,  F23R3/46

Abstract: The invention relates to a can-combustor for a can-annular combustor arrangement in a gas turbine. The can combustor includes an essentially cylindrical casing with an axially upstream front panel and an axially downstream outlet end. The can combustor further includes a number of premixed burners, extending in an upstream direction from said front panel and having a burner exit, supported by this front panel, for supplying a fuel/air mixture into a combustion zone inside the casing. Up to four premixed burners are attached to the front panel in a substantially annular array. Each burner has a conical swirl generator and a mixing tube to induce a swirl flow of said fuel/air mixture.

公开(公告)号：US09518740B2

公开(公告)日：2016-12-13

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 ,  F23R3/28 ,  F23C7/00

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。