公开(公告)号：US10323574B2

公开(公告)日：2019-06-18

申请号：US14974622

申请日：2015-12-18

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Devis Tonon ,  Mirko Ruben Bothien ,  Luis Tay Wo Chong Hilares

IPC: F02C3/20 ,  F23C9/08 ,  F02C7/18 ,  F23R3/04 ,  F23R3/06 ,  F23M20/00

Abstract: The invention refers to a combustor arrangement of a gas turbine engine or power plant, having at least one combustion chamber, at least one mixer for admixing a dilution medium or air to the hot gas flow leaving the combustion chamber. The mixer is configured to guide combustion gases in a hot gas flow path extending downstream of the combustion chamber, wherein the mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution medium or air to cool the hot gas flow leaving combustion chamber. The mixer includes at least one dilution air plenum having at least one pressure-controlled compartment which is directly or indirectly connected to at least one injection pipe.

公开(公告)号：US10451283B2

公开(公告)日：2019-10-22

申请号：US15007981

申请日：2016-01-27

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Mirko Ruben Bothien ,  Devis Tonon ,  Bruno Schuermans

IPC: F02C3/20 ,  F02C3/30 ,  F23R3/06 ,  F23R3/16 ,  F23R3/34 ,  F23M20/00

Abstract: A sequential combustor arrangement and method are disclosed which can include a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer can include at least one injection opening in the mixer wall for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber. Further, the mixer can include a damper with a damper volume and a neck connecting the damper volume to the mixer, for modulating and damping pressure pulsations inside the mixer.

公开(公告)号：US10267525B2

公开(公告)日：2019-04-23

申请号：US14925527

申请日：2015-10-28

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Douglas Anthony Pennell ,  Urs Benz ,  Adnan Eroglu ,  Ewald Freitag ,  Mirko Ruben Bothien ,  Andrea Ciani

IPC: F23R3/06 ,  F23R3/34 ,  F23R3/36 ,  F23C6/04 ,  F23R3/28

Abstract: A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner.

公开(公告)号：US11454398B2

公开(公告)日：2022-09-27

申请号：US17174939

申请日：2021-02-12

Applicant: Ansaldo Energia Switzerland AG

Inventor： Mirko Ruben Bothien ,  Alessandro Scarpato

IPC: F23R3/34 ,  F23R3/06 ,  F23R3/04 ,  F23R3/28 ,  F23R3/00

Abstract: A mixer having a housing, a duct within the housing, a first and a second injector arranged to inject a fluid at a centre zone of the duct, a third and a fourth injector arranged to inject the fluid at a wall zone of the duct. The first/third injectors are at a distance D1=v/2f1 or odd integer multiples of it from the second/fourth injectors in the absence of an acoustic node between them, or at a distance D1=λconv=v/f1 or full wave length integer multiples of it in the presence of an acoustic node between them. Advantageously f1 is greater than f2.

公开(公告)号：US20210172606A1

公开(公告)日：2021-06-10

申请号：US17174939

申请日：2021-02-12

Applicant: Ansaldo Energia Switzerland AG

Inventor： Mirko Ruben Bothien ,  Alessandro Scarpato

IPC: F23R3/34 ,  F23R3/28 ,  F23R3/00

Abstract: A mixer having a housing, a duct within the housing, a first and a second injector arranged to inject a fluid at a centre zone of the duct, a third and a fourth injector arranged to inject the fluid at a wall zone of the duct. The first/third injectors are at a distance D1=v/2f1 or odd integer multiples of it from the second/fourth injectors in the absence of an acoustic node between them, or at a distance D1=λconv=v/f1 or full wave length integer multiples of it in the presence of an acoustic node between them. Advantageously f1 is greater than f2.

公开(公告)号：US10323575B2

公开(公告)日：2019-06-18

申请号：US14975241

申请日：2015-12-18

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Anders Martin Axel Wickström ,  Devis Tonon ,  Mirko Ruben Bothien

IPC: F02C7/22 ,  F23D14/46 ,  F23D11/36 ,  F23M20/00 ,  F23R3/28

Abstract: The invention concerns a gas turbine fuel pipe, having a fuel line, the fuel line having a fuel line volume, a fuel line outer wall and an opening in the fuel line outer wall, a damper having a damper volume and a damper outer wall and attached in fluid communication with the fuel line, wherein the damper covers the opening in the fuel line outer wall, and a perforated lining extending across at least part of the opening in the fuel line outer wall.

公开(公告)号：US11242806B2

公开(公告)日：2022-02-08

申请号：US15817861

申请日：2017-11-20

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Mirko Ruben Bothien ,  Douglas Pennell ,  Peter Stuttaford

IPC: F02C9/26 ,  F23R3/16 ,  F23R3/34 ,  F23R3/12 ,  F02C7/228 ,  F23R3/28 ,  F23R3/36

Abstract: A method is disclosed for controlling fuel injection in a reheat combustor of a gas turbine combustor assembly including a combustor casing defining a gas flow channel and a plurality of injection nozzles distributed in or around the gas flow channel; the method includes the step of distributing fuel among the injection nozzles according to a non-uniform distribution pattern.

公开(公告)号：US10125987B2

公开(公告)日：2018-11-13

申请号：US14958386

申请日：2015-12-03

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Devis Tonon ,  Mirko Ruben Bothien

IPC: F23M3/00 ,  F23M20/00 ,  F23R3/00

Abstract: A damper for a gas turbine combustion chamber as shown in FIG. 1 includes a damper volume wall and a main neck. The damper volume wall defines a damper volume inside the damper volume wall. The main neck includes a main neck wall defining a main neck volume inside the main neck wall. The main neck is associated with the damper volume for fluid communication between the damper volume and the gas turbine combustion chamber. In addition, the damper includes a gap between the main neck wall and the damper volume wall. The main neck defines a main neck axis. For example, the gap is a second neck, and in further embodiments, multiple damper volumes are provided.

公开(公告)号：US10330319B2

公开(公告)日：2019-06-25

申请号：US14693045

申请日：2015-04-22

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Michael Duesing ,  Luis Tay Wo Chong Hilares ,  Mirko Ruben Bothien ,  Jaan Hellat ,  Bruno Schuermans

IPC: F23R3/34 ,  F23C6/04 ,  F23R3/06 ,  F02C6/02 ,  F23R3/00 ,  F23M20/00

Abstract: The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. The mixer includes a plurality of injection pipes pointing inwards from the side walls of the mixer for admixing the dilution gas to cool the hot flue gases leaving the first combustion chamber with a low pressure drop. The disclosure further refers to a method for operating a gas turbine with such a combustor arrangement.

公开(公告)号：US10247420B2

公开(公告)日：2019-04-02

申请号：US14970857

申请日：2015-12-16

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Mirko Ruben Bothien ,  Luis Tay Wo Chong Hilares ,  Adnan Eroglu ,  Bruno Schuermans ,  Michael Düsing

IPC: F02C7/18 ,  F23R3/34 ,  F23R3/00 ,  F23R3/06 ,  F23R3/12 ,  F23C6/04 ,  F23C9/08

Abstract: A method is disclosed for operating an axially staged mixer arrangement with dilution air or dilution gas injection in connection with a combustion arrangement of a gas turbine engine or turbo machinery, having at least one combustion chamber, at least one mixer arrangement for admixing air or gas portions to the hot gas flow leaving the combustion chamber. The mixer arrangement includes a plurality of injectors for admixing air portions to cool at least the hot gas flow leaving combustion chamber. The spacing between the last injection location of acting injectors and at least one subsequently arranged dilution air injection, inside of the mixer arrangement in the hot gas flow, where there is no node between the injection locations, corresponds to a distance equal or approximating to half of convective wave length.