The invention relates to a damper for reducing pulsations in a gas turbine, which includes an enclosure, a main neck extending from the enclosure, a spacer plate disposed in the enclosure to separate the enclosure into a first cavity and a second cavity and an inner neck with a first end and a second end, extending through the spacer plate to interconnect the first cavity and the second cavity. The first end of the inner neck remains in the first cavity and the second end remains in the second cavity. A flow deflecting member is disposed proximate the second end of the inner neck to deflect a flow passing through the inner neck. With the solution of the present invention, as a damper according to embodiments of the present invention operates, flow field hence damping characteristic in the second cavity constant regardless the adjustment of the spacer plate in the enclosure.
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
F23M 20/00 - Details of combustion chambers, not otherwise provided for
F01N 1/02 - Silencing apparatus characterised by method of silencing by using resonance
G10K 11/16 - Methods or devices for protecting against, or for damping, noise or other acoustic waves in general
H04R 1/28 - Transducer mountings or enclosures designed for specific frequency responseTransducer enclosures modified by provision of mechanical or acoustic impedances, e.g. resonator, damping means
2.
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. A cross section of the compressor inlet includes an inner sector and an outer sector in relation to the axis of rotation of the compressor. A plurality of feed ducts introduces oxygen-reduced gas into the inner sector of the compressor inlet. The plurality of feed ducts is arranged in the compressor inlet so as to be distributed in a circumferential direction on a circle concentrically with respect to the axis of the gas turbine.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
3.
Gas turbine part and method for manufacturing such gas turbine part
n, 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.
F01D 5/08 - Heating, heat-insulating, or cooling means
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
C04B 35/80 - Fibres, filaments, whiskers, platelets, or the like
C04B 35/56 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxides based on carbides
C04B 37/00 - Joining burned ceramic articles with other burned ceramic articles or other articles by heating
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
4.
FLOW CONTROL DEVICE FOR ROTATING FLOW SUPPLY SYSTEM
This disclosure describes a removable flow control device (102) which may be used in a rotating flow supply system in a gas turbine to optimize coolant flow by improving flow dynamics, reducing leakage of coolant, and reducing pressure loss in the flow supply system. The flow control device may be coupled to a blade (108) and rotor assembly (100) and may include a flow modifier (152) for directing flow through a junction at which cooling channels intersect and are in fluid communication. The device may direct, control, meter, channel, or otherwise modify the flow of coolant, and may be coupled to the blade and rotor assembly independently of other blade components so that coupling and decoupling the flow control device does not require modification or de-stacking of the rotor assembly.
Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary fuel cartridge assembly may comprise first and second fuel manifolds which are connected to respective fuel circuits which supply fuel, such as liquid fuel, through a plurality of fuel passages within the fuel cartridge assembly or to other locations within an associated combustor. The fuel cartridge assembly may further include a plurality of fuel injector tips located at a tip plate of the fuel cartridge assembly through which fuel may be supplied to an associated combustor.
F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23R 3/34 - Feeding into different combustion zones
Gas turbine combustion systems and fuel cartridge assemblies are provided. An exemplary combustion system may comprise a combustor including a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly. An exemplary combustor and/or fuel cartridge assembly may comprise first and second fuel circuits or manifolds. Methods and systems are also provided for staging and controlling a flow of fuel and/or water through different fuel circuits and pilot injectors, to allow purging and ignition using different fuel circuits, pilot injectors, and fuel sources.
F23R 3/14 - Air inlet arrangements for primary air inducing a vortex by using swirl vanes
F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
Systems and methods for dual-fuel operation of a gas turbine combustor are provided. An exemplary gas turbine combustor may comprise one or more components, such as a cylindrical combustion liner, a flow sleeve, a main mixer, a radial inflow swirler, a combustor dome, and a fuel cartridge assembly, one or more of which may be configured to supply either a gaseous or a liquid fuel to the combustion liner, depending on whether gaseous fuel operation or liquid fuel operation of the combustor is desired.
F23R 3/16 - Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23R 3/34 - Feeding into different combustion zones
The invention refers to a sandwich arrangement comprising at least two peripheral disposed ceramic panels (101a, 101b) and a ceramic felt (110) which is inserted be- tween a first and second ceramic panel, The material of the first ceramic panel being equal or different to the material of the second panel, wherein the ceramic felt is formed by a textile structure with a regularly or quasi-regularly structured woven fi- bres. The fibres are made of at least one material and/or composition, wherein at least one adhesive mean is provided between the underside of the panels and adja- cent fibres.
B32B 5/02 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine. Additionally, a method of automated extended turndown of a GT engine to find a minimum load is provided.
The present invention discloses a novel apparatus and way for reducing the recirculation zone at the inlet end of a combustor. The recirculation zone is reduced by altering the geometry of the inlet end through a tapering of the liner wall thickness and a tapering of the thermal barrier coating to reduce the bluff body effect at the combustion liner inlet end.
F23R 3/42 - Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
F23R 3/00 - Continuous combustion chambers using liquid or gaseous fuel
The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.
The present invention includes systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.
Methods and systems of cooling airfoils are provided. The present invention provides systems and methods for providing cooling channels located within walls of a turbine airfoil. These cooling channels include micro-circuits that taper in various directions along the length and width of the airfoil. In addition, these cooling channels have a variety of shapes and areas to facilitate convective heat transfer between the surrounding air and the airfoil.
A turbo machine, such as a gas turbine, includes a rotor, which rotates about a horizontal machine axis, and which is enclosed by a coaxial enclosure. The turbo machine includes a metal casing, whereby an electrical heating system is provided on the lower half of the metal casing. A safe operation is achieved by having the heating system configured as a redundant system.
The invention relates to a method for operating a gas turbine which includes a compressor with annular inlet area, at least two burners, a combustion chamber and a turbine. According to the method, at least one first partial intake flow, consisting of oxygen-reduced gas which has an oxygen concentration which is lower than the average oxygen concentration of the compressor intake flow, and at least one second partial intake flow, consisting of fresh air, are fed to the compressor in an alternating manner in the circumferential direction of the inlet area. In addition, the invention relates to a gas turbine power plant with a gas turbine, the compressor inlet of which includes at least one first segment and at least one second segment which are arranged in an alternating manner around a compressor inlet in the circumferential direction, wherein a feed for an oxygen-reduced gas is connected to the first segment and a fresh air feed is connected to the second segment of the compressor inlet.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 7/08 - Heating air supply before combustion, e.g. by exhaust gases
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
F23C 9/00 - Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
F02C 3/13 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
A method for operating a gas turbine power plant, and a gas turbine power plant in which fresh air is delivered to a compressor inlet and is accelerated in the compressor inlet and a recirculated first exhaust gas substream is delivered into a region of the compressor inlet in which the fresh air is accelerated to an extent such that the difference between total pressure and static pressure in the fresh air is greater than or equal to a pressure difference which is required in order to suck a target mass flow of the recirculated first exhaust gas substream into the compressor inlet.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
F02C 7/042 - Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
F01K 13/02 - Controlling, e.g. stopping or starting
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
17.
Method of operating a gas turbine power plant with exhaust gas recirculation and corresponding gas turbine power plant
The invention relates to a method for operating a gas turbine, in which an oxygen-reduced gas and fresh air are delivered to a compressor of the gas turbine in a radially staged manner, the fresh air being delivered via an outer sector of the inlet cross section in relation to the axis of rotation of the compressor, and the oxygen-reduced gas being delivered via an inner sector of the inlet cross section in relation to the axis of rotation of the compressor.
The invention relates, further, to a gas turbine power plant with a gas turbine having a compressor inlet which is followed by the flow duct of the compressor and which is divided into an inner sector and an outer sector, a feed for an oxygen-reduced gas being connected to the inner sector of the compressor inlet, and a fresh air feed being connected to the outer sector of the compressor inlet.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
F02C 6/08 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F02C 3/06 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
18.
Mixing element for gas turbine units with flue gas recirculation
The invention pertains to fluegas recirculation in gas turbines, and specifically to an intake section upstream of the inlet of a compressor of a gas turbine unit with fluegas recirculation. The intake section includes at least one section with a flow path defined by sidewalls in which the fresh airflow of the intake air is flowing along a principal airflow direction, including at least one mixing duct extending into the flow path from at least one sidewall. The mixing duct includes an intake at the at least one sidewall for receiving recirculated fluegas, as well as including at least one outlet opening distanced from said sidewall for blowing recirculated fluegas out of the mixing duct into the airflow.
F02C 7/04 - Air intakes for gas-turbine plants or jet-propulsion plants
B01F 3/02 - Mixing, e.g. dispersing, emulsifying, according to the phases to be mixed gases with gases or vapours
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
A method and system are disclosed for operating a gas turbine power plant with flue gas recirculation, in which variable compressor inlet guide vanes are controlled as a function of flue gas recirculation ratio and/or as a function of a process parameter which is indicative for the flue gas recirculation. A controller setpoint position of the variable compressor inlet guide vanes can be controlled as a function of a position of a control element for controlling flue gas recirculation flow.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes
F23C 9/00 - Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
F01K 17/04 - Use of steam or condensate extracted or exhausted from steam engine plant for specific purposes other than heating
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
F02C 9/50 - Control of fuel supply conjointly with another control of the plant with control of working fluid flow
21.
Transitional region for a combustion chamber of a gas turbine
A gas turbine including a combustion chamber and a first row of guide vanes, arranged essentially directly downstream thereof, of a turbine. The outer and/or inner limitation of the combustion chamber defined by at least one outer and/or inner heat shield, mounted on at least one combustion chamber structure arranged radially outside and/or inside. The hot gases flow path in the region of the guide vane row being restricted radially on the outside and/or inside by an outer and/or inner vane platform, mounted at least indirectly on at least one turbine carrier. A minimal gap size directly upstream of the first row of guide vanes is achieved by mounting at least indirectly on the turbine carrier at least one mini heat shield, arranged upstream of the first row of guide vanes and essentially adjacent the vane platform and in the flow direction between the heat shield and the vane platform.
An exemplary method for the operation of a CCPP with flue gas recirculation to reduce NOx emissions and/or to increase the CO2 concentration in the flue gases to facilitate CO2 capture from the flue gases as well as a plant designed to operate is disclosed. To allow a high flue gas recirculation ration (rFRG) an imposed combustion inhomogeneity ratio (ri) is used for flame stabilization. The imposed combustion inhomogeneity ratio (ri) is controlled as function of the flue gas recirculation rate (rFRG) and/or combustion pressure. Oxygen or oxygen enriched air to the gas turbine inlet gases or to the combustor is admixed to enhance operatability.
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F01K 17/04 - Use of steam or condensate extracted or exhausted from steam engine plant for specific purposes other than heating
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
F02C 3/28 - Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products the fuel or oxidant being solid or pulverulent, e.g. in slurry or suspension using a separate gas producer for gasifying the fuel before combustion
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
F02C 9/24 - Control of the pressure level in closed cycles
23.
Sequential combustor gas turbine including a plurality of gaseous fuel injection nozzles and method for operating the same
A gas turbine (1) includes a compressor (2) that feeds an oxidizer to one or more combustion devices (3, 5) in which fuel is injected and is combusted to generate hot gases that are expanded in a turbine (4, 6). The flue gases discharged from the turbine (4, 6) are partially recirculated into the compressor (2). The fuel is a gaseous fuel that is injected into the combustion devices (3, 5) via two or more stages (20, 22, 23). One of the stages is a pilot stage (20) in which the fuel is injected along a longitudinal axis (21) of the combustion device (3, 5) or an axis parallel thereto.
F23R 3/34 - Feeding into different combustion zones
F02C 3/34 - Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
F01K 23/10 - Plants characterised by more than one engine delivering power external to the plant, the engines being driven by different fluids the engine cycles being thermally coupled combustion heat from one cycle heating the fluid in another cycle with exhaust fluid of one cycle heating the fluid in another cycle
F02C 9/34 - Joint control of separate flows to main and auxiliary burners
F22B 1/18 - Methods of steam generation characterised by form of heating method by exploitation of the heat content of hot heat carriers the heat carrier being a hot gas, e.g. waste gas such as exhaust gas of internal-combustion engines
F23C 9/00 - Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
F23R 3/28 - Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
C22F 1/10 - Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
patents
