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Ansaldo Energia Switzerland Ag patents


Recent patent applications related to Ansaldo Energia Switzerland Ag. Ansaldo Energia Switzerland Ag is listed as an Agent/Assignee. Note: Ansaldo Energia Switzerland Ag may have other listings under different names/spellings. We're not affiliated with Ansaldo Energia Switzerland Ag, we're just tracking patents.

ARCHIVE: New 2018 2017 2016 2015 2014 2013 2012 2011 2010 2009 | Company Directory "A" | Ansaldo Energia Switzerland Ag-related inventors


Mixer

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. ... Ansaldo Energia Switzerland Ag

Burner assembly for a combustor of a gas turbine power plant and combustor comprising said burner assembly

A burner assembly for a combustor is provided with a pilot burner extending along a longitudinal axis and a premix burner surrounding the pilot burner; the pilot burner being integral with the premix burner.. . ... Ansaldo Energia Switzerland Ag

Method for manufacturing a burner assembly for a gas turbine combustor and burner assembly for a gas turbine combustor

A method for manufacturing a burner assembly for a gas turbine combustor, having a pilot burner extending along a longitudinal axis, and a premix burner surrounding the pilot burner, wherein the method includes manufacturing at least one portion of the pilot burner by an additive manufacturing technique which includes manufacturing at least one first thermal bridge connecting parts of the pilot burner having a temperature difference not greater than a threshold value.. . ... Ansaldo Energia Switzerland Ag

Heat exchanger for a gas turbine engine

A heat exchanger is disclosed which includes a pressure vessel with an inlet for air, an outlet for air, and a bundle of pipes housed within the pressure vessel for a thermo-vector fluid. A gas/solid separator is provided within the pressure vessel for separating particles drawn by the air.. ... Ansaldo Energia Switzerland Ag

Method for operating a supply assembly for supplying fuel gas and inert media to a gas turbine combustor, such supply assembly and a gas turbine comprising such supply assembly

A method for operating a supply assembly configured for supplying fuel gas and an inert purge media to a gas turbine combustor, the method including supplying fuel gas in a fuel gas circuit with an upper flow rate; reducing the fuel gas flow rate in the fuel gas circuit from the upper flow rate to a lower flow rate; stopping the supply of the fuel gas in the fuel gas circuit; and starting the supply of the inert purge media in the inert purge media circuit, wherein the starting is performed before the stopping to have a temporary parallel supply of fuel gas and of inert purge media to a fuel distribution system.. . ... Ansaldo Energia Switzerland Ag

Last turbine rotor disk for a gas turbine, rotor for a gas turbine comprising such last turbine rotor disk and gas turbine comprising such rotor

A gas turbine having a compressor section provided with a plurality of compressor blades and vanes for compressing air; a combustion section; a turbine section a rotor having an axis and extending from a compressor section to the turbine section for supporting the compressor and turbine blades, the rotor having a last rotor disk having a downstream portion for supporting a bearing cover and an upstream portion for supporting a last turbine blade; and a cooling duct system configured for supplying cooling air from a downstream end of the turbine section to the last turbine blade passing inside the last rotor disk, and having an axial bore in the downstream portion of the last rotor disk along the rotor axis; and a first plurality of inclined radial bores in the upstream portion of the last rotor disk off the axis.. . ... Ansaldo Energia Switzerland Ag

Sealing system for a rotating machine

The sealing system for a rotating machine comprises a fixed part and a movable part. The fixed part is connectable to a stator of a rotating machine and the movable part is connected to and movable to and fro the fixed part. ... Ansaldo Energia Switzerland Ag

Blade of a rotary flow machine with a radial strip seal

The invention refers to a blade of a rotary flow machine including an airfoil having a suction surface and a pressure surface joining each other along a trailing and a leading edge. A radially outward directed airfoil tip and a radially inward directed end joining an inner platform connect the airfoil to a shank at a radial end of the airfoil and providing, at least one shank pocket radially encircled by an axially extending portion of the platform. ... Ansaldo Energia Switzerland Ag

Vortex generating device

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. ... Ansaldo Energia Switzerland Ag

Vortex generating device

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. ... Ansaldo Energia Switzerland Ag

Nested article by additive manufacturing with non-removable internal supporting structure

. . 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.. . ... Ansaldo Energia Switzerland Ag

Method of operating a gas turbine power plant with exhaust gas recirculation and corresponding gas turbine power plant

An exemplary gas turbine power plant includes a gas turbine with a compressor having a compressor inlet. A combustion chamber follows the compressor and a turbine follows the combustion chamber. ... Ansaldo Energia Switzerland Ag

Dual fuel concentric nozzle for a gas turbine

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.. . ... Ansaldo Energia Switzerland Ag

Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

A combustor device for a gas turbines engines includes first and a second tubular members telescopically fitted in axially sliding manner to one another with interposition of annular centering and sealing which include at least a centering annular shoulder and a sealing ring arranged coaxial to one another. The sealing ring is axially spaced apart from the centering annular shoulder so that an axial distance between the centering annular shoulder and the sealing ring is greater than a maximum axial movement allowed between the first and said second tubular members.. ... Ansaldo Energia Switzerland Ag

04/12/18 / #20180100439

Sealing device arrangement at the interface between a combustor and a turbine of a gas turbine and gas turbine with such a sealing arrangement

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. ... Ansaldo Energia Switzerland Ag

04/12/18 / #20180100409

Stator heat shield segment for a gas turbine power plant

A stator heat shield segment for a gas turbine includes an inner surface facing a hot gas main flow of the gas turbine; an outer surface opposite to the inner surface and at least partially exposed to cooling air; a first impingement cavity provided with a plurality of first impingement holes fluidly connected with the cooling air supplied outside the outer surface; a feeding cavity isolated from the cooling air supplied outside the outer surface and fluidly connected with first impingement cavity; and a second impingement cavity provided with a plurality of second impingement holes fluidly connected to the feeding cavity.. . ... Ansaldo Energia Switzerland Ag

03/22/18 / #20180080654

Sequential combustion with dilution gas mixer

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. ... Ansaldo Energia Switzerland Ag

03/22/18 / #20180080652

Annular helmholtz damper for a gas turbine can combustor

An annular helmholtz damper for a gas turbine can combustor, the annular helmholtz damper having an axis; an inner wall and an outer wall concentrically arranged with respect to the axis to define an annular damping volume arranged around a can combustor; a front and rear circumferential plates for closing the annular damping volume upstream and downstream; at least one intermediate circumferential plate arranged between the front and the rear plates for dividing the annular damping volume in a main and a secondary volume; and a plurality of intermediate drain holes passing the intermediate circumferential plate and configured for draining collected liquid from the main volume to the secondary volume.. . ... Ansaldo Energia Switzerland Ag

03/08/18 / #20180066848

Combustor device for a gas turbine engine and gas turbine engine incorporating said combustor device

Combustor device having a twin-shell tubular casing including: an inner tubular member which extends roughly coaxial a longitudinal axis of the combustor device, delimits the combustion chamber and surrounds the burner; and an outer tubular housing which extends roughly coaxial outside of the inner tubular member. An intermediate supporting structure includes an outer annular supporting member, an inner annular supporting member, and a series of three or more oblong connecting beams angularly staggered about the longitudinal axis of combustor device in cantilever manner to stably connect the inner and outer annular supporting members.. ... Ansaldo Energia Switzerland Ag

03/01/18 / #20180058951

Temperature probe

A temperature probe and method for determining a temperature in a gas flow are disclosed. The probe includes a probe body. ... Ansaldo Energia Switzerland Ag

02/22/18 / #20180051884

Injector device and method for manufacturing an injector device

An injector device is disclosed which includes an elongated body with a leading edge and a trailing edge, gas nozzles and oil nozzles, an oil supply duct housed within the elongated body and connected to the oil nozzles, and a gas supply duct housed within the elongated body and connected to the gas nozzles. The oil supply duct is connected to the gas supply duct only between one or more oil nozzles and one gas nozzles, and the gas supply duct is connected to the elongated body only via bridges.. ... Ansaldo Energia Switzerland Ag

02/22/18 / #20180051578

Gas turbine transition duct

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.. . ... Ansaldo Energia Switzerland Ag

02/08/18 / #20180038736

Temperature detecting device for a gas turbine power plant and gas turbine power plant comprising said temperature detecting device

A temperature detecting device for a gas turbine power plant is provided with at least one optical probe configured to detect a parameter indicative of a temperature and with at least one capsule configured to define a camera inside which the optical probe is housed.. . ... Ansaldo Energia Switzerland Ag

01/18/18 / #20180016923

Sealing arrangement on combustor to turbine interface in a gas turbine

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.. . ... Ansaldo Energia Switzerland Ag

12/14/17 / #20170356294

Airfoil cooling passageways for generating improved protective film

An airfoil for a gas turbine engine, the airfoil comprising a wall having a first surface, a second surface, and a passageway extending through the wall from a first opening in the first surface to a second opening in the second surface, the passageway having one or more sections between the first opening and the second opening, the one or more sections in fluid communication with each other, the plurality of sections comprising a first diffuser section providing a first change in cross-sectional area within the passageway, a second diffuser section providing a second change in cross-sectional area within the passageway, a flow conditioning section, and an edge section having two surfaces set opposite each other across the passageway, the two surfaces extending along the passageway substantially in parallel to one another, the edge section being located adjacent to the second opening.. . ... Ansaldo Energia Switzerland Ag

10/12/17 / #20170292708

Method for combusting a fuel, and combustion appliance

A method for combusting a fuel includes, providing an oxidizer mass flow, providing a first oxidizer partial mass flow, combusting a fuel in the first oxidizer partial mass flow thus providing a mass flow of combustion products, providing the mass flow of combustion products to a duct, and ducting the mass flow of combustion products through the duct in a flow direction. A flow of a first supplementary fluid which is essentially aligned with the flow of combustion products is selectively provided as one of an oxidizer and a premixed fuel/oxidizer mixture. ... Ansaldo Energia Switzerland Ag

10/12/17 / #20170292695

Method for combusting a fuel, and combustion device

A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.. ... Ansaldo Energia Switzerland Ag

10/12/17 / #20170292408

Assembly, in particular of engine components

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. ... Ansaldo Energia Switzerland Ag

10/12/17 / #20170292401

Method for determination of fatigue lifetime consumption of an engine component

A method for determining fatigue lifetime consumption of an engine component, by defining a reference thermal load cycle, the reference thermal load cycle being characterized by a reference load cycle amplitude and a reference load cycle time, and determining a reference load cycle lifetime consumption. The method includes measuring a temperature of the engine component, determining a thermal load cycle based upon the temperature measurement, determining a load cycle amplitude, determining a load cycle time, relating the load cycle time to the reference load cycle time, thereby determining a load cycle time factor, relating the load cycle amplitude to the reference load cycle amplitude, thereby determining a load cycle amplitude factor, combining the load cycle time factor and the load cycle amplitude factor into a combined load cycle factor for determining a load cycle lifetime consumption.. ... Ansaldo Energia Switzerland Ag

10/12/17 / #20170292392

Turboengine, and vane carrier unit for turboengine

A turboengine as disclosed includes an outer wall structure and an inner wall structure, wherein the inner wall structure is provided at a radially inner position with respect to the outer wall structure, and each of the wall structures has a surface, the surfaces being arranged facing each other in the radial direction. At least one guide vane member includes at least one airfoil, a radially inner end and a radially outer end. ... Ansaldo Energia Switzerland Ag

10/12/17 / #20170292383

Blade

A blade includes an airfoil and a root having diverging walls. The diverging walls are made of a ceramic matrix composite material. ... Ansaldo Energia Switzerland Ag

10/05/17 / #20170284207

Airfoil

An airfoil for a working fluid path of a turboengine extends along a spanwidth direction from a base to a tip. An aerodynamic body thereof includes a suction side surface, a pressure side surface, a leading edge, a trailing edge and a tip, the tip of the aerodynamic body having a tip cross section and a cross-sectional contour circumscribing the tip cross section. ... Ansaldo Energia Switzerland Ag

08/10/17 / #20170226862

Fluid cooled rotor for a gas turbine

The present disclosure relates to a rotor for a gas turbine having a plurality of rotor disks arranged one behind the other in a rotor axis and connected to one another, where the geometrical form of the disks leads to the formation of cavities between adjacent disks. The rotor extends from a compressor part to a turbine part and has a central part between the compressor part and the turbine part, wherein the first turbine disk, the last compressor disk and the central part enclose a central cavity. ... Ansaldo Energia Switzerland Ag

07/27/17 / #20170211418

Cooled wall of a turbine component and a method for cooling this wall

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.. . ... Ansaldo Energia Switzerland Ag

07/27/17 / #20170211405

Stator heat shield for a gas turbine, gas turbine with such a stator heat shield and method of cooling a stator heat shield

A stator heat shield for a gas turbine having a hot gas flow path, is disclosed. The stator heat shield includes a first surface configured to face the hot gas flow path of the gas turbine; a second surface opposite to the first surface; cooling channels for directing cooling fluid from the second surface towards the first surface; and cavities arranged at the first surface for receiving the cooling fluid from at least a part of the cooling channels; wherein at least a part of the cavities each have at least two corresponding cooling channels open thereto, the at least two corresponding cooling channels being inclined towards each other. ... Ansaldo Energia Switzerland Ag

06/22/17 / #20170176737

Boroscope sheath

A boroscope sheath is disclosed for providing a boroscope with temperature protection during a boroscope inspection of a machine such as a gas turbine or a steam turbine. The boroscope sheath includes an elongate tube having a wall extending from a front end to a back end and around a central bore configured and arranged to allow removable insertion of a boroscope cooling channels extend in the wall. ... Ansaldo Energia Switzerland Ag

06/22/17 / #20170175558

Hula seal

A hula seal as disclosed extends in a circumferential direction, a radial direction and an axial direction relative to a central axis. The hula seal includes a first leaf extending from the first edge region to the second edge region and a second leaf extending from the first edge region to the second edge region. ... Ansaldo Energia Switzerland Ag

06/15/17 / #20170167008

Solution heat treatment method for manufacturing metallic components of a turbo machine

A solution heat treatment method is disclosed for manufacturing metallic components of a turbo machine, which components provide a hot gas flow channel when assembled in the turbo machine after manufacturing, wherein the components are subjected to a time-temperature-cycle in a furnace. The method includes positioning the components in the furnace in a same principle as the component assembly in the turbo machine, but leaving flow areas and gaps between neighbouring components; then starting the time-temperature-cycle; and applying an inert gas during the solution heat treatment process so that the inert gas flows through flow areas and gaps for achieving a uniform temperature.. ... Ansaldo Energia Switzerland Ag

05/18/17 / #20170138273

Method for controlling the operation of a gas turbine with an averaged turbine outlet temperature

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. ... Ansaldo Energia Switzerland Ag

05/18/17 / #20170138265

Heat exchangers and cooling methods for gas turbines

A gas turbine is disclosed which includes a compressor, a combustor downstream of the compressor, a turbine downstream of the combustor, a heat exchanger, a first cooling fluid system and a second cooling fluid system. The first and the second cooling fluid systems are each configured and arranged to extract a cooling fluid from the compressor and to cool a part of the gas turbine using the cooling fluid. ... Ansaldo Energia Switzerland Ag

05/18/17 / #20170138199

Gas turbine part and method for manufacturing such gas turbine part

The present disclosure relates to a gas turbine part, which can be exposed to high temperatures and centrifugal forces within a gas turbine. The gas turbine part can include plural sliced parts, wherein at least one of said sliced parts is made from a ternary ceramic called max phase, having the formula mn+1axn, where n=1, 2, or 3, m is an early transition metal such as ti, v, cr, zr, nb, mo, hf, sc, ta, and a is an a-group element such as al, si, p, s, ga, ge, as, cd, in, sn, tl, pb, and x is c and/or n.. ... Ansaldo Energia Switzerland Ag

05/18/17 / #20170138198

Gas turbine part and method for manufacturing such gas

The present disclosure relates to building very large gas turbines without changing rotor materials. The gas turbine part can include a structure composed of a metal and a ternary ceramic called max phase, having a formula mn+1axn, where n=1, 2, or 3, m is an early transition metal such as ti, v, cr, zr, nb, mo, hf, sc, ta, and a is an a-group element such as al, si, p, s, ga, ge, as, cd, in, sn, tl, pb, and x is c and/or n.. ... Ansaldo Energia Switzerland Ag

05/18/17 / #20170137949

Power plant component and method for manufacturing such component

A power plant component is disclosed having a substrate, the surface of which is coated with a functionally graded coating of a predetermined thickness, with anti-erosion, anti-corrosion and anti-fouling properties. Improved operation properties are achieved by the functionally graded coating having a corrosion resistant portion, and an erosion resistant and hydrophobic portion, whereby the functionally graded coating is a composite coating consisting of a single layer.. ... Ansaldo Energia Switzerland Ag

04/06/17 / #20170096919

Damper assembly for a combustion chamber

The present disclosure relates to gas turbines and to a damper assembly for a combustion chamber of a gas turbine. A damper assembly as disclosed herein may be adjusted to different frequencies during operation and/or deactivated for different operation regimes.. ... Ansaldo Energia Switzerland Ag

03/30/17 / #20170089584

Vortex generator, and fuel injection system of a gas turbine with such vortex generator

A vortex generator, such as for a fuel injection system of a gas turbine, includes a base area and a vortex generator body extending in a tapering fashion from the base area with a predetermined height. A rapid fuel-air mixing at allowable pressure drops for higher firing temperature gas turbines and within short burner-mixing length or time scales is achieved by the vortex generator body forming at least two partial vortex generators, whereby each of the at least two partial vortex generators has its own trailing edge.. ... Ansaldo Energia Switzerland Ag

03/23/17 / #20170081969

Gas turbine vane

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.. ... Ansaldo Energia Switzerland Ag

03/09/17 / #20170067362

Gas turbine rotor cover

A gas turbine rotor cover includes a body, the body having an inner side facing towards a central axis and an outer side facing away from the central axis, wherein the gas turbine rotor cover is configured and arranged to extend in an axial direction and a circumferential direction relative to the central axis. An inner layer of insulation is attached to the inner side of the body and extends along at least part of the length of the body in the axial direction and/or an outer layer of insulation is attached to the outer side of the body, and extends along at least part of the length of the body in the axial direction. ... Ansaldo Energia Switzerland Ag

02/16/17 / #20170045228

Sequential combustion arrangement with cooling gas for dilution

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. ... Ansaldo Energia Switzerland Ag

02/16/17 / #20170044916

Gas turbine membrane seal

A gas turbine membrane seal is disclosed. The gas turbine membrane seal includes a membrane, the membrane configured and arranged to extend from a first gas turbine component to a second gas turbine component and to separate two volumes, and an anti-fretting part configured and arranged to be attached to the first gas turbine component. ... Ansaldo Energia Switzerland Ag

02/16/17 / #20170044909

Gas turbine cooling systems and methods

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. ... Ansaldo Energia Switzerland Ag

02/02/17 / #20170030219

First stage turbine vane arrangement

A first stage vane arrangement having an array of first stage vanes and an array of frame segments and method for cooling frame segments of the first vane arrangement of a gas turbine are disclosed. The frame segments are designed for axially receiving aft ends of a combustor transition pieces. ... Ansaldo Energia Switzerland Ag

01/26/17 / #20170023050

Locking pin

Subject matter of the disclosure is a locking pin arrangement with a basic element for receiving an insert and a fall-proof locking pin for fixing the insert in the basic element. The locking pin is at least partially inserted into a borehole of the basic element and is pushed towards an opening of the borehole by a spring. ... Ansaldo Energia Switzerland Ag

01/19/17 / #20170016123

High temperature protective coating

The invention relates to a high temperature protective coating based on mcraly coating, with m at least one element out of the group of ni, co and fe, for a component of a turbo machine, especially a gas turbine, the coating containing at least at least 1.75 vol.-% chromium borides and the coating consisting of the following chemical composition (in wt.-%): 10-27 cr; 3-12 al; 1-4 si; 0.1-3 ta; 0.01-3 y; 0.1-3 b; 0-7 m, with m being a different element out of said group compared to the remainder, and the remainder being m and inevitable impurities. A preferred embodiment is a coating with the following chemical composition: 10-27 cr; 3-12 al; 1-4 si; 0.1-3 ta; 0.01-3 y; 0.1-3 b; 0-7 co and the remainder being ni and inevitable impurities.. ... Ansaldo Energia Switzerland Ag

01/12/17 / #20170009990

Gas turbine

The present invention relates to a gas turbine implemented for example at the interface between the combustor and the vane platform. An efficiency of a cooling film associated to the vane platform can be increased, hence reducing the quantity of the air needed.. ... Ansaldo Energia Switzerland Ag

01/12/17 / #20170009651

Sequential combustor and method for operating the same

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.. ... Ansaldo Energia Switzerland Ag

01/12/17 / #20170009601

Mechanical component for thermal turbo machinery

A mechanical component for thermal turbo machinery, such as a steam or gas turbine, includes a base part and at least one additional device being mechanically coupled to the base part in order to influence the vibration characteristic of the base part during operation of the turbo machine. High-cycle fatigue at part-load can be reduced by enabling the mechanical coupling between the base part and the at least one additional device to change with the temperature of the at least one additional device.. ... Ansaldo Energia Switzerland Ag

01/05/17 / #20170002740

Gas turbine cool-down phase operation methods

The application describes a method of operating a gas turbine during a cool-down phase. The gas turbine provides a compressor, a combustor downstream of the compressor, and a turbine downstream of the combustor, with the turbine providing a turbine vane carrier. ... Ansaldo Energia Switzerland Ag

01/05/17 / #20170002665

Gas turbine blade

A gas turbine blade includes a blade root and a blade aerofoil, a cooling fluid plenum extending inside the gas turbine blade through the blade root, the blade aerofoil and the blade tip, a blade root impingement plate in the cooling fluid plenum inside the blade root and a blade tip impingement plate in the cooling fluid plenum inside the blade tip, the blade tip impingement plate having at least one cooling fluid hole configured and arranged to enable a cooling fluid to flow from the blade tip into the blade aerofoil via the cooling fluid hole or holes, and a pipe extending in the cooling fluid plenum from the blade root impingement plate to the blade tip impingement plate. The blade root impingement plate can direct the cooling fluid from the blade root to the pipe.. ... Ansaldo Energia Switzerland Ag








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