-
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
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：US10920670B2
公开(公告)日：2021-02-16
申请号：US15727328
申请日：2017-10-06
Applicant: ANSALDO ENERGIA SWITZERLAND AG
Inventor： Marcos Escudero Olano , Stephan Strueken , Thomas Zierer , Frank Graf , Adnan Eroglu , Joshua R. McNally , Stephen W. Jorgensen , Afzal Pasha Mohammed
Abstract: A sealing arrangement at an interface between a combustor and a turbine of a gas turbine. The turbine can include deflecting vanes at its inlet, which deflecting vanes are each mounted within the turbine so as to define an inner or outer diameter platform and are in sealing engagement via an inner or outer diameter vane tooth with a seal arranged at the corresponding inner or outer diameter part of the outlet of the combustor. The seal is movable and is pressed on the inner or outer diameter vane tooth by a differential pressure such that the pressure of the mainstream hot gas flow is a lower pressure.
-
公开(公告)号：US20180080654A1
公开(公告)日：2018-03-22
申请号：US15823939
申请日：2017-11-28
Applicant: Ansaldo Energia Switzerland AG
Inventor： Ewald Freitag , Adnan Eroglu , Michael Maurer , Peter Stuttaford
CPC classification number: F23R3/34 , F02C7/22 , F02C7/228 , F23R3/06 , F23R3/20 , F23R3/346 , F23R3/42 , F23R2900/00014 , F23R2900/03042 , F23R2900/03341
Abstract: The invention refers to a sequential combustor arrangement comprising a first burner, a first combustion chamber, a mixer for admixing a dilution gas via a dilution gas inlet 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 sequential combustor arrangement further includes four cooling zones with a cooling channel. During operation a cooling gas flows through the cooling channels. The disclosure further refers to a method for operating a gas turbine with such a sequential 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
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.
-
Patent Agency Ranking
公开(公告)号：US10544940B2
公开(公告)日：2020-01-28
申请号：US15084012
申请日：2016-03-29
Applicant: ANSALDO ENERGIA SWITZERLAND AG
Inventor： Kaspar Loeffel , Yang Yang , Adnan Eroglu , Michael Thomas Maurer , Nico Biagioli , Alexey Stytsenko , Sergey Mylnikov , Igor Baibuzenko
Abstract: A fuel injector device includes a body having a leading edge and a trailing edge and defining a streamwise direction from the leading edge to the trailing edge. The fuel injector device body includes a first surface and a second surface opposite the first surface, each surface extending between and including the leading edge and the trailing edge, and the surfaces conjoining each other at the leading edge and the trailing edge. The trailing edge, when seen in the streamwise direction, undulates along a trailing edge mean line and, along its extent, deviates in opposite directions from the mean line and includes at least one inflection point along its extent.
-
公开(公告)号：US10352568B2
公开(公告)日：2019-07-16
申请号：US14925435
申请日：2015-10-28
Applicant: Ansaldo Energia Switzerland AG
Inventor： Adnan Eroglu , Andrea Ciani , Douglas Anthony Pennell
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 arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements.
-
公开(公告)号：US10774740B2
公开(公告)日：2020-09-15
申请号：US14048878
申请日：2013-10-08
Applicant: Ansaldo Energia Switzerland AG
Inventor： Robert Marmilic , Jaan Hellat , Ewald Freitag , Adnan Eroglu
Abstract: The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.
-
公开(公告)号：US10753615B2
公开(公告)日：2020-08-25
申请号：US15725770
申请日：2017-10-05
Applicant: ANSALDO ENERGIA SWITZERLAND AG
Inventor： John Philip Wood , Andrea Ciani , Adnan Eroglu
Abstract: A dual fuel concentric nozzle such as for a dual fuel injector of a sequential burner of a sequential gas turbine, the dual fuel concentric nozzle having a nozzle downstream end, a liquid fuel duct, a gas fuel duct concentrically surrounding the liquid fuel duct and defining a gas fuel passage between the outer surface of the liquid fuel duct and the inner surface of the gas fuel duct, and a lateral surface concentrically surrounding the gas fuel duct and defining a carrier air passage, a downstream end edge of the gas fuel duct being recessed inside the nozzle downstream end with respect to a downstream end edge of the liquid fuel duct.
-
公开(公告)号：US10443847B2
公开(公告)日：2019-10-15
申请号：US14837039
申请日：2015-08-27
Applicant: Ansaldo Energia Switzerland AG
Inventor： Andrea Ciani , Adnan Eroglu
Abstract: A sequential combustor arrangement including a first burner, a first combustion chamber, a mixer for admixing dilution air to hot gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow direction. The mixer guides combustion gases in a hot gas flow path extending from the first combustion chamber. The second burner including a duct having an inlet for connection to the first combustion chamber and an outlet for connection to the second burner. The mixer includes injection pipes pointing inwards from the side walls for admixing the dilution air to cool the hot gases leaving the first combustion chamber. The injection pipes are distributed circumferentially along the side wall of the mixer. The injection pipes have a conical or quasi-conical shape addressed to the center of the mixer.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.012 seconds)
