Patents Assigned to Ansaldo Energia Switzerland AG
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Patent number: 10865987Abstract: The present invention generally relates to a sequential combustor for a gas turbine having second and/or subsequent stages of a re-heat, sequential or axially-staged combustion system. A variation in Mach number along the flow path can be used to control static temperature variation, which in turn influences the progress of auto-ignition reactions that eventually lead to the onset of combustion.Type: GrantFiled: July 8, 2016Date of Patent: December 15, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Khawar Syed, Madhavan Narasimhan Poyyapakkam, Franklin Marie Genin
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Patent number: 10865990Abstract: An additive manufactured article for a gas turbine having a body with two lateral surfaces elongated in a first direction; at least a nested duct housed within the lateral surfaces and elongated in the first direction; a structure so that the nested duct is structurally connected to an attachment within the lateral surfaces, wherein at least the body, the duct and the structure are manufactured by an additive manufacturing process and the structure includes an array of ribs attached to the duct in order to compensate differential elongation along the first direction of the duct with respect to the attachment of the ribs by flexural deformation.Type: GrantFiled: November 17, 2017Date of Patent: December 15, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Alexey Stytsenko, Sergey Mylnikov, Igor Baibuzenko, Michael Maurer
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Patent number: 10865986Abstract: A vortex generating device is provided as a generally airfoil-shaped lobed body. The flow deflection varies along a spanwise extent, such that the body exhibits a corrugated geometry in a trailing edge region, and the trailing edge exhibits an undulating shape. The undulating shape includes at least one corner. The trailing edge may include or may consist of straight trailing edge sections. The trailing edge may exhibit a polygonial waveform shape, in particular a trapezoidal or rectangular waveform shape. The vortex generating device may be provided as a fuel discharge device which is suited to discharge a fuel into a vortex flow generated by the vortex generating device. To this extent, a fuel supply plenum may be provided inside the body and at least one fuel discharge opening which is in fluid communication with the fuel supply plenum may be provided on the trailing edge.Type: GrantFiled: November 29, 2017Date of Patent: December 15, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Andre Theuer, Urs Benz, Yang Yang, Michael Düsing
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Publication number: 20200386120Abstract: Disclosed is a cooled airfoil having a hub end and tip, an airfoil height being defined between the hub end and the tip. The airfoil has a leading edge, trailing edge, suction side and pressure side. The airfoil has a first airfoil height section adjacent the hub end and extending towards the tip, wherein, in a meridional view, the leading edge and trailing edge are straight along the first airfoil height section. The airfoil has a second airfoil height section adjacent the tip and extending towards the hub end, wherein, in a meridional view, the airfoil is concavely shaped at the leading edge and is convexly shaped at the trailing edge along the second airfoil height section. At least one cooling channel has a length principally extending along the airfoil height, extends straight in a first cooling channel length section, and is bent in a second cooling channel length section.Type: ApplicationFiled: April 24, 2020Publication date: December 10, 2020Applicant: Ansaldo Energia Switzerland AGInventors: Frank GERSBACH, Brian Kenneth WARDLE, Iannis BUFFART
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Patent number: 10851659Abstract: Disclosed is a vortex generating device having a body, extending between a leading edge and a trailing edge. The body, in profile cross sections taken across the spanwise direction, exhibits an airfoil-shaped geometry. Each airfoil-shaped profile cross section has a camber line extending from the leading edge to the trailing edge, at least two of the camber lines exhibiting different camber angles, such that the body exhibits at least two different flow deflection angles along the spanwise extent. An imaginary trailing edge diagonal extends straight from a first spanwise end of the trailing edge to a second spanwise end of the trailing edge. When seen from the downstream viewpoint, the trailing edge crosses the imaginary trailing edge diagonal exactly once at one diagonal crossing point.Type: GrantFiled: November 29, 2017Date of Patent: December 1, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Yang Yang, Andre Theuer
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Patent number: 10851668Abstract: A cooled wall of a turbine component includes a first layer of channels for a coolant arranged along a side of the wall facing to a flow of hot gas, the first layer of channels having a serpentine shape, each channel of the first layer having an inlet and an outlet; a second layer of channels for the coolant disposed further from the flow of hot gas than the first layer, each channel of the second layer having an inlet and an outlet, the outlet of each of the channels of the first layer being in fluid communication with corresponding inlet of associated channel of the second layer creating a bend for changing a direction of the coolant leaving the channel of the first layer when entering the channel of the second layer.Type: GrantFiled: January 25, 2017Date of Patent: December 1, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Andrey Sedlov, Maxim Plodistyy, Oleg Naryzhny
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Patent number: 10801352Abstract: The invention concerns a turbine for a gas turbine comprising a blade, a vane and an abradable lip attached to the blade or to the vane, wherein the blade and the vane are separated by a gap and the abradable lip extends part of the distance across the gap. Embodiments include the addition of an abrasive layer attached on the other side of the gap from the abradable lip. A method of manufacturing is also described.Type: GrantFiled: April 21, 2016Date of Patent: October 13, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Guillaume Wagner, Herbert Brandl, Emanuele Facchinetti, Matthias Hoebel, Carlos Simon-Delgado
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Patent number: 10787918Abstract: A gas turbine transition duct includes: an inner tubular body, defining a transition channel and having a first upstream end and a first downstream end for coupling to a can combustor and to a turbine section of a gas turbine assembly, respectively; an outer tubular body, arranged around the inner tubular body and having a second upstream end at the first upstream end of the inner tubular body and a second downstream end at the first downstream end of the inner tubular body; wherein a convective cooling channel is defined between the inner tubular body and the outer tubular body, the convective cooling channel having an inlet between the first downstream end and the second downstream end; and wherein the outer tubular body is continuous between the second upstream end and the second downstream end.Type: GrantFiled: August 18, 2017Date of Patent: September 29, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Paul Marlow, Michael Maurer, Dalibor Vrbetic
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Patent number: 10774740Abstract: 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.Type: GrantFiled: October 8, 2013Date of Patent: September 15, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Robert Marmilic, Jaan Hellat, Ewald Freitag, Adnan Eroglu
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Patent number: 10767569Abstract: A method is disclosed for operating a gas turbine having a compressor, a combustor, a turbine downstream of the combustor, and a total number of turbine outlet temperature measurements. The method includes locally measuring the turbine outlet temperature of the turbine with the turbine outlet temperature measurements of the respective turbine, and averaging measured temperatures of the selected turbine outlet temperature measurements to obtain an average turbine outlet temperature. The gas turbine operation is controlled depending on the determined average turbine outlet temperature.Type: GrantFiled: November 14, 2016Date of Patent: September 8, 2020Assignee: Ansaldo Energia Switzerland AGInventors: Martin Gassner, Andreas Jan Schesny, Sebastian Lipari, Stefano Bernero, Manuel Ramirez-Espana-Mejia, Mengbin Zhang
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Patent number: 10753615Abstract: 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.Type: GrantFiled: October 5, 2017Date of Patent: August 25, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: John Philip Wood, Andrea Ciani, Adnan Eroglu
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Patent number: 10753214Abstract: A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.Type: GrantFiled: July 14, 2017Date of Patent: August 25, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Jost Imfeld, Hans-Christian Mathews, Urs Benz
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Patent number: 10746055Abstract: An assembly of at least two members. One of the members supports the other member, the assembly defining an axial direction, a radial direction, and a circumferential direction, an inner member of the at least two members being received radially inside an outer member of the at least two members, wherein the inner member and the outer member am attached to each other by a support arrangement, the support arrangement including at least one floating support assembly as a displaceable coupling between an inner member support point provided at the inner member and an outer member support point provided at the outer member. A displacement of support points in a radial direction results in an interrelated relative displacement of the support points in an axial direction end vice versa.Type: GrantFiled: April 7, 2017Date of Patent: August 18, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Meisam Sistaninia, Diego Ugel, Giovanni Cataldi, Martin Schaefer
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Patent number: 10731490Abstract: The present disclosure generally relates to a guide vane for a gas turbine, and provides for example an innovative guide vane with improved flexibility leading to a reduction of stresses at the interface between the vane platform and the vane carrier. Exemplary embodiments provide only circumferential line contact or point contact between the guide vane and the guide vane carrier.Type: GrantFiled: September 21, 2016Date of Patent: August 4, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Marc Widmer, Herbert Brandl
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Patent number: 10724382Abstract: A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part.Type: GrantFiled: August 12, 2016Date of Patent: July 28, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Sergei Riazantsev, Stefan Rofka, Robert Marmilic, Hanspeter Knopfel, Sergey Shchukin
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Patent number: 10718520Abstract: The invention concerns a damper arrangement for reducing combustion-chamber pulsation arising inside a gas turbine, wherein the gas turbine includes at least one compressor, a primary combustor which is connected downstream to the compressor, and the hot gases of the primary combustor are admitted at least to an intermediate turbine or directly or indirectly to a secondary combustor. The hot gases of the secondary combustor are admitted to a further turbine or directly or indirectly to an energy recovery, wherein at least one combustor is arranged in a can-architecture. At least one combustor liner includes air passages, wherein at least one of the air passages is formed as a damper neck. The damper neck being actively connected to a damper volume, and the damper volume is part of a connecting duct extending between a compressor air plenum and the combustor.Type: GrantFiled: October 24, 2013Date of Patent: July 21, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Mirko Ruben Bothien, Jaan Hellat, Bruno Schuermans
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Patent number: 10677453Abstract: A gas turbine with a sequential combustor arrangement as disclosed includes a first combustor with a first burner for admitting a first fuel into a combustor inlet gas during operation and a first combustion chamber for burning the first fuel, a dilution gas admixer for admixing a dilution gas to the first combustor combustion products leaving the first combustion chamber, a second burner for admixing a second fuel and a second combustion chamber. To assure a temperature profile after the dilution gas admixer and to increase the gas turbine's power and efficiency a vane and/or blade of the turbine has a closed loop cooling. The outlet of the closed loop cooling is connected to the dilution gas admixer for admixing the heated cooling gas leaving the vane and/or blade into the first combustor combustion products.Type: GrantFiled: August 11, 2016Date of Patent: June 9, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Wilhelm Reiter, Jürgen Gerhard Hoffmann
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Patent number: 10648667Abstract: A combustion chamber includes a duct wall for guiding a hot gas flow in a hot gas flow path during operation. The duct wall is a double-walled construction including an inner face, an outer face, and a wall cavity. A sleeve at least partly encloses the duct wall for guiding a cooling gas in a cooling channel between the sleeve and the duct wall along the outer surface of the duct wall to an exit end, and the cavity opens to the cooling channel. A gas turbine is disclosing as having such a combustion chamber.Type: GrantFiled: March 11, 2016Date of Patent: May 12, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Michael Thomas Maurer, Felix Baumgartner
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Patent number: 10634357Abstract: 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.Type: GrantFiled: November 28, 2017Date of Patent: April 28, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Ewald Freitag, Adnan Eroglu, Michael Maurer, Peter Stuttaford
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Patent number: 10590790Abstract: The invention concerns a conical hula seal wherein an inner part of the conical hula seal is closer to a conical hula seal longitudinal axis than an outer part of the conical hula seal, and wherein the conical hula seal extends in a circumferential direction relative to the conical hula seal longitudinal axis. A gas turbine which includes the conical hula seal is also disclosed, along with a method of operating a gas turbine which includes a conical hula seal that seals a gap between a first vane and a picture frame, the method including purging the gap with a cooling fluid.Type: GrantFiled: March 25, 2016Date of Patent: March 17, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Hans-Christian Mathews, Urs Benz, Frank Graf