[...] with integrated Liquid evaporator.

Die vorliegende Erfindung stellt eine Brennstoffdüse (100) für eine Gasturbine bereit, die einen Primärbrennstoff und einen Sekundärbrennstoff verwendet. Die Brennstoffdüse (100) enthält eine Anzahl von Primärbrennstoffeinspritzanschlüssen (170) für den Primärbrennstoff, einen Wasserdurchgang (220), eine Anzahl von Sekundärbrennstoffeinspritzanschlüssen (280) und ein Sekundärbrennstoffverdampfungssystem zum Zerstäuben des Sekundärbrennstoffs.

Fuel nozzle.

Die vorliegende Erfindung stellt eine Brennstoffdüse (100) für eine Gasturbine bereit, die einen Primärbrennstoff und einen Sekundärbrennstoff verwendet. Die Brennstoffdüse (100) umfasst eine Anzahl von Primärbrennstoffeinspritzanschlüssen (170) für den Primärbrennstoff, einen Wasserdurchgang (220), eine Anzahl von Sekundärbrennstoffeinspritzöffnungen (280) und ein Sekundärbrennstoffverdampfungssystem zum Zerstäuben des Sekundärbrennstoffs.

TURBINE SYSTEM WITH EXHAUST GAS RECIRCULATION, SEPARATION AND EXTRACTION

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.

Systems and methods for high volumetric oxidant flow in gas turbine engine with exhaust gas recirculation

A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles.

Combustor with a Lean Pre-Nozzle Fuel Injection System

The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air. 1. A combustor for combusting a flow of fuel and a flow of air , comprising:a plurality of fuel nozzles;a lean pre-nozzle fuel injection system positioned upstream of the plurality of fuel nozzles; anda premixing annulus positioned between the plurality of fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.2. The combustor of claim 1 , wherein each of the plurality of fuel nozzles comprises a fuel injector and a swirler.3. The combustor of claim 1 , wherein each of the plurality of fuel nozzles comprises a plurality of outer fuel nozzles.4. The combustor of claim 1 , wherein the plurality of fuel nozzles comprises a bellmouth.5. The combustor of claim 1 , further comprising a cap baffle and a casing and wherein the cap baffle and the casing define the premixing annulus.6. The combustor of claim 5 , wherein the cap baffle and the casing comprise a flared shape that expands towards the plurality of fuel nozzles.7. The combustor of claim 1 , wherein the premixing annulus comprises a smooth turning portion adjacent to the plurality of fuel nozzles.8. The combustor of claim 1 , wherein the lean pre-nozzle fuel injection system comprises a plurality of fuel injectors.9. The combustor of claim 8 , wherein each of the plurality of fuel injectors comprises a streamlined wing-like shape.10. The combustor of claim 8 , wherein each of the plurality of fuel injectors comprises a plurality of injector holes.11. A method providing a number of flows of fuel and a flow of air in a combustor claim 8 , comprising:injecting a flow of a premix fuel into a ...

Turbine system with exhaust gas recirculation, separation and extraction

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber and a second volume configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.

AXIALLY STAGED PREMIXED COMBUSTION CHAMBER

A combustor for a gas turbine includes a plurality of radially outer nozzles arranged in an annular array, each of the radially outer nozzles having an outlet end located to supply fuel and/or air to a first combustion chamber. A center nozzle has an outlet end located axially upstream of the outlet ends of the radially outer nozzles, and is configured and arranged to supply fuel and air to a second combustion chamber axially upstream of the first combustion chamber. The second combustion chamber opens into the first combustion chamber and has a length sufficient to maintain a center nozzle flame confined to the second combustion chamber.

Combustor with a lean pre-nozzle fuel injection system

The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.

GAS TURBINE TRANSITION PIECE AIR BYPASS BAND ASSEMBLY

An air bypass band assembly includes a transition piece of a gas turbine, the transition piece having at least one opening therein to allow a flow of air to pass through the at least one opening. The air bypass band assembly also includes a band that is movable between at least two positions, a first one of the at least two positions being a closed position where the at least one opening is closed to prevent the flow of air from flowing through the at least one opening, a second one of the at least two positions being an open where the at least one opening is opened to allow the flow of air to flow through the at least one opening. The air bypass band assembly further includes a mechanism that moves the band between the at least two positions.

Annular ring-manifold quaternary fuel distributor

A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.

COMBUSTOR PORTION FOR A TURBOMACHINE AND METHOD OF OPERATING A TURBOMACHINE

A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones. 1. A turbomachine combustor portion comprising:a combustor body having a combustor outlet;a combustion liner arranged within the combustor body, the combustion liner defining a combustion chamber;a center injection nozzle arranged within the combustion chamber, the center injection nozzle having a center nozzle inlet and a center nozzle outlet;at least one outer premixed injection nozzle positioned radially outwardly of the center injection nozzle, the at least one outer premixed injection nozzle including an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet; andat least one late lean injector positioned downstream of the center injection nozzle and the at least one outer premixed injection nozzle;the combustor portion including a first combustion zone arranged downstream of the outer nozzle outlet and upstream of the center nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged downstream of the ...

Combustor portion for a turbomachine and method of operating a turbomachine

A turbomachine combustor portion includes a combustion chamber. A center injection nozzle is arranged within the combustion chamber and includes a center nozzle inlet and a center nozzle outlet. An outer premixed injection nozzle is positioned radially outward of the center injection nozzle and includes an outer nozzle inlet and an outer nozzle outlet that is arranged upstream of the center nozzle outlet. A late lean injector is positioned downstream of the center nozzle and the outer premixed nozzle. The combustor portion includes a first combustion zone arranged downstream of the outer nozzle outlet, a second combustion zone arranged downstream of the center nozzle outlet, and a third combustion zone arranged further downstream of the center nozzle outlet. The center injection nozzle, outer premixed injection nozzle, and late lean injector are selectively operated to establish a combustion flame front in the first, second, and third combustion zones.

COUNTER ROTATED GAS TURBINE FUEL NOZZLES

In certain embodiments, a system includes a gas turbine controller. The gas turbine controller includes a first operational mode enabling fuel flow only through a first plurality of fuel nozzles having a first swirl direction. The gas turbine controller also includes a second operational mode enabling fuel flow only through a second plurality of fuel nozzles having a second swirl direction opposite from the first swirl direction.

SEGMENTED ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR

A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

ANNULAR RING-MANIFOLD QUATERNARY FUEL DISTRIBUTOR

A combustor section is provided and includes one or more annular quaternary fuel manifolds mounted within an annular passage defined between a casing and a cap assembly of a combustor through which air and/or a fuel/air mixture flows upstream from a fuel nozzle support, the manifold including a body to accommodate quaternary fuel therein, the body defining injection holes through which the quaternary fuel is injected into a section of the passage at a location upstream from the fuel nozzle support.

Segmented annular ring-manifold quaternary fuel distributor

A combustor section is provided and includes a segmented annular manifold mounted upstream from a fuel nozzle support in a section of a passage through which an oxidizer flows, each segment of the manifold being substantially axially aligned and including a body to accommodate fuel internally that is formed to define injection holes through which the fuel is injected into the passage through which the oxidizer flows upstream of the fuel nozzle support.

SYSTEMS AND METHODS FOR HIGH VOLUMETRIC OXIDANT FLOW IN GAS TURBINE ENGINE WITH EXHAUST GAS RECIRCULATION

A system having a gas turbine engine is provided. The gas turbine engine includes a turbine and a combustor coupled to the turbine. The combustor includes a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly. The end cover assembly includes an oxidant inlet configured to receive an oxidant flow, a central oxidant passage, and at least one fuel supply passage. The central oxidant passage is in fluid communication with the oxidant inlet, and the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles. The at least one fuel supply passage is configured to receive a fuel flow and route the fuel flow into the one or more fuel nozzles. 1. A system , comprising: a turbine; and', 'a combustor coupled to the turbine, wherein the combustor comprises a combustion chamber, one or more fuel nozzles upstream from the combustion chamber, and a head end having an end cover assembly, wherein the end cover assembly comprises:', 'an oxidant inlet configured to receive an oxidant flow;', 'a central oxidant passage in fluid communication with the oxidant inlet, wherein the central oxidant passage is configured to route the oxidant flow to the one or more fuel nozzles; and', 'at least one fuel supply passage configured to receive a fuel flow, wherein the at least one fuel supply passage is configured to route the fuel flow into the one or more fuel nozzles., 'a gas turbine engine, comprising2. The system of claim 1 , wherein the end cover assembly comprises a baffle assembly in fluid communication with the central oxidant passage.3. The system of claim 2 , wherein the baffle assembly comprises a baffle channel defined by a baffle shell claim 2 , wherein the baffle channel is in fluid communication with the central oxidant passage.4. The system of claim 3 , wherein the baffle shell comprises a plurality of oxidant apertures disposed through a wall of the baffle shell claim 3 ...

Turbine system with exhaust gas recirculation, separation and extraction

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume.

FUEL NOZZLE WITH CENTRAL BODY COOLING SYSTEM

A fuel nozzle for turbine engine includes a cooling shroud located at the downstream end of the fuel nozzle to help cool the downstream end of the fuel nozzle. The cooling shroud surrounds the exterior circumference of the downstream end of the fuel nozzle. A flow of air is admitted into the cooling shroud and the flow of air travels in the downstream direction through a first passageway which covers the exterior of the fuel nozzle. The cooling air flow then turns 180° and travels in the upstream direction through a second passageway which is located concentrically outside the first passageway. The airflow then leaves the upstream end of the cooling shroud and enters the interior of the fuel nozzle.

TURBINE SYSTEM WITH EXHAUST GAS RECIRCULATION, SEPARATION AND EXTRACTION

A system includes a turbine combustor having a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber. The turbine combustor includes a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber. The turbine combustor also includes a third volume disposed axially downstream from the first volume and circumferentially about the second volume. The third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from the first volume and from the second volume. 1. A system , comprising: a first volume configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber;', 'a second volume configured to receive a first flow of an exhaust gas and to direct the first flow of the exhaust gas into the combustion chamber; and', 'a third volume disposed axially downstream from the first volume and circumferentially about at least a portion of the second volume, wherein the third volume is configured to receive a second flow of the exhaust gas and to direct the second flow of the exhaust gas out of the turbine combustor via an extraction outlet, and the third volume is isolated from each of the first volume and from the second volume., 'a turbine combustor, comprising2. The system of claim 1 , comprising:a housing;a flow sleeve disposed within the housing, wherein the third volume is defined between an aft portion of the flow sleeve and the housing; anda flange extending radially outward from the flow sleeve to the housing, wherein the flange isolates the third volume from the first volume.3. The system of claim 1 , wherein the extraction outlet is positioned between a transition piece and a head end of the combustor.4. The system of claim 1 , comprising:a ...

SYSTEM AND METHOD FOR A TURBINE COMBUSTOR

A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate. 1. A system , comprising: a head end portion having a head end chamber, wherein the head end portion comprises an exhaust gas path, a fuel path, and an oxidant path;', 'a combustion portion having a combustion chamber disposed downstream from the head end chamber;', 'a cap disposed between the head end chamber and the combustion chamber; and', 'an end plate having at least one port coupled to the exhaust gas path or the oxidant path, wherein the head end chamber is disposed axially between the cap and the end plate., 'a turbine combustor, comprising2. The system of claim 1 , wherein the at least one port is disposed along an axial face of the end plate.3. The system of claim 1 , wherein the at least one port comprises a first oxidant inlet of the oxidant path.4. The system of claim 3 , wherein the first oxidant inlet comprises an axial oxidant port.5. The system of claim 4 , wherein the axial oxidant port comprises a central oxidant port coupled to a central region of the end plate.6. The system of claim 4 , wherein the axial oxidant port comprises a peripheral oxidant port coupled to a peripheral region surrounding a central region of the end plate.7. The system of claim 3 , wherein the at least one port comprises a second oxidant inlet coupled to the end plate claim 3 , wherein the first oxidant inlet comprises a central oxidant port coupled to a central region of the end plate claim 3 , and the second oxidant ...

Premixing nozzle with integral liquid evaporator

The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel.

MULTI-ZONE COMBUSTOR

A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section. 1. A multi-zone combustor , comprising:a pre-mixer configured to output a first mixture to a primary zone of a combustor section; anda stepped center body disposable in an annulus defined within the pre-mixer and including:an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section, and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.2. The multi-zone combustor according to claim 1 , wherein the first mixture claim 1 , the second mixture and the third mixture are fueled separately.3. The multi-zone combustor according to claim 1 , wherein the second mixture and the third mixture are each output in a co-rotation condition.4. The multi-zone combustor according to claim 1 , wherein the second mixture and the third mixture are each output in a counter-rotation condition.5. The multi-zone combustor according to claim 1 , wherein the second mixture and the third mixture are each output with similar rotation angles.6. The multi-zone combustor according to claim 1 , wherein the stepped center body further includes an additional body disposable between the outer body and the inner body and configured to output at a third radial and axial step a fourth mixture to a fourth zone of the combustor section.7. A ...

Fuel Nozzle Assembly Having a Premix Fuel Stabilizer

A fuel nozzle assembly includes a premix chamber, an air flow divider extending radially and axially within the premix chamber between an inner wall and an outer wall and a plurality of guide vanes disposed within the premix chamber. One or more of the guide vanes includes a fuel port in fluid communication with the flow divider. The fuel nozzle assembly further includes a premix plate that extends radially between the inner and outer walls and circumferentially between first and second side walls downstream from the fuel ports. The premix plate includes an upstream side axially spaced from a downstream side and a plurality of passages that provide for fluid flow from the premix chamber through the premix plate. 1. A fuel nozzle assembly comprising:a premix chamber defined between an arcuate inner wall, an arcuate outer wall, a first side wall and a circumferentially opposing second side wall;an air flow divider extending radially between the inner wall and the outer wall and extending axially within the premix chamber, wherein the air flow divider defines an internal fuel circuit;a plurality of guide vanes disposed within the premix chamber, wherein at least one guide vane extends circumferentially between the air flow divider and one of the first side wall or the second side wall, wherein one or more of the guide vanes includes a fuel port in fluid communication with the fuel circuit; anda premix plate that extends radially between the inner and outer walls and circumferentially between the first and second side walls downstream from the fuel ports, wherein the premix plate includes an upstream side axially spaced from a downstream side and a plurality of passages, wherein the passages provide for fluid flow from the premix chamber through the premix plate.2. The fuel nozzle assembly as in claim 1 , wherein the upstream side of the premix plate includes a plurality of concentrically aligned annular walls and a plurality of circumferentially spaced radial walls ...

COMBUSTOR AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR

A combustor () includes a cap (), a liner (), a transition piece (), and a combustion chamber () located downstream from the cap () and defined by the cap and liner. A secondary nozzle () circumferentially arranged around the liner () or transition piece () includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding the center body, and an annular passage between the center body and the shroud. A method for supplying fuel to a combustor () includes flowing fuel through a primary nozzle radially disposed in a breech end of the combustor and flowing fuel through a secondary nozzle () circumferentially arranged around and passing through at least one of a liner () or a transition piece. The secondary nozzle () includes a center body, a fluid passage through the center body, a shroud circumferentially surrounding at least a portion of the center body (), and an annular passage between the center body and the shroud. 1. A combustor , comprising:a. a cap;b. a liner extending downstream from the cap;c. a transition piece extending downstream from the liner;d. a combustion chamber downstream from the cap and at least partially defined by the cap and the liner; i. a center body that extends from a casing surrounding the combustor through at least one of the liner or the transition piece;', 'ii. a fluid passage through the center body;', 'iii. a shroud circumferentially surrounding at least a portion of the center body; and', 'iv. an annular passage between the center body and the shroud., 'e. a secondary nozzle circumferentially arranged around at least one of the liner or the transition piece, wherein the secondary nozzle comprises2. The combustor as in claim 1 , further comprising a plurality of primary nozzles radially disposed in the cap.3. The combustor as in claim 2 , wherein each primary nozzle is aligned approximately perpendicular to the secondary nozzle.4. The combustor as in claim 1 , further comprising a plurality of ...

FUEL NOZZLE CARTRIDGE AND METHOD FOR ASSEMBLY

A gas turbine system is provided. The gas turbine system includes a combustor assembly. At least one liquid fuel cartridge in the combustor assembly includes at least one flexible tube section coupled within a housing. An elongated inner tube section is coupled in fluid communication with the at least one flexible tube section and oriented within an elongated outer tube extending from the housing. At least one support member oriented within and coupled to an inner surface of the elongated outer tube substantially precludes transverse movement of the elongated inner tube section within the elongated outer tube. 1. A method for assembling a liquid fuel cartridge for use in a gas turbine engine , said method comprising:orienting at least one flexible tube section within a housing;coupling the at least one flexible tube section to an elongated inner tube section oriented within an elongated outer tube extending from the housing; andsupporting the elongated inner tube section by at least one support member oriented within and coupled to an inner surface of the elongated outer tube, such that the at least one support member substantially precludes transverse movement of the elongated inner tube section within the elongated outer tube, and such that the elongated inner tube section is axially movable relative to the at least one support member.2. The method in accordance with claim 1 , wherein said method further comprises coupling the at least one flexible tube section in fluid communication with at least one fitting oriented on the housing.3. The method in accordance with claim 1 , wherein said method further comprises coupling the at least one flexible tube section in fluid communication with at least one aperture defined on a tip oriented on the elongated outer tube.4. The method in accordance with claim 1 , wherein said method further comprises defining the at least one flexible tube section as a coil substantially encircling an axis oriented transversely to a ...

Air bypass belt arrangement for a gas turbine transition piece

Eine Luftbypassbandanordnung (16) enthält ein Übergangsstück (14) einer Gasturbine (10), wobei das Übergangsstück (14) wenigstens eine darin ausgebildete Öffnung (26) aufweist, um einer Luftströmung (28) zu ermöglichen, durch die wenigstens eine Öffnung (26) hindurchzutreten. Die Luftbypassbandanordnung (16) enthält ferner ein Band (20), das zwischen wenigstens zwei Stellungen überführbar ist, wobei eine erste der wenigstens zwei Stellungen eine Schließstellung ist, in der wenigstens eine Öffnung (26) verschlossen ist, um die Luftströmung (28) daran zu hindern, durch die wenigstens eine Öffnung (26) zu strömen, wobei eine zweite der wenigstens zwei Stellungen eine Offenstellung ist, in der wenigstens eine Öffnung (26) geöffnet ist, um der Luftströmung (28) zu ermöglichen, durch die wenigstens eine Öffnung (26) zu strömen. Die Luftbypassbandanordnung (16) enthält ferner einen Mechanismus (22), der das Band (20) zwischen den wenigstens zwei Stellungen überführt. An air bypass belt assembly (16) includes a transition piece (14) of a gas turbine (10), the transition piece (14) having at least one opening (26) formed therein to allow an air flow (28) through which at least one opening (26) to step through. The air bypass belt arrangement (16) also contains a belt (20) which can be transferred between at least two positions, a first of the at least two positions being a closed position in which at least one opening (26) is closed to allow the air flow (28) thereon to prevent flowing through the at least one opening (26), wherein a second of the at least two positions is an open position in which at least one opening (26) is opened to allow air flow (28) through the at least one opening (26) to flow. The air bypass belt assembly (16) further includes a mechanism (22) that transfers the belt (20) between the at least two positions.

System and method for a turbine combustor

A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.

System and method for a turbine combustor

A system includes a turbine combustor, which includes a head end portion having a head end chamber. The head end portion includes an exhaust gas path, a fuel path, and an oxidant path. The turbine combustor also includes a combustion portion having a combustion chamber disposed downstream from the head end chamber, a cap disposed between the head end chamber and the combustion chamber, and an end plate having at least one port coupled to the exhaust gas path or the oxidant path. The head end chamber is disposed axially between the cap and the end plate.

COMBUSTION DEVICE HAVING A POOR FUEL INJECTION SYSTEM UPSIDE NOZZLES

Dispositif de combustion (100) pour brûler un flux de combustible et un flux d'air. Le dispositif de combustion (100) peut comprendre un certain nombre de buses (120) de combustible, un système d'injection (270) de combustible pauvre en amont des buses, placé en amont des buses (120) de combustible, et un volume annulaire de prémélange (250) placé entre les buses (120) de combustible et le système d'injection (270) de combustible pauvre en amont des buses, pour prémélanger le flux de combustible et le flux d'air. Combustion device (100) for burning a fuel flow and an air flow. The combustion device (100) may include a number of fuel nozzles (120), a lean fuel injection system (270) upstream of the nozzles, located upstream of the fuel nozzles (120), and a volume premix annulus (250) positioned between the fuel nozzles (120) and the lean fuel injection system (270) upstream of the nozzles for premixing the fuel flow and the air flow.

Premixing nozzle with integral liquid evaporator

The present application provides a fuel nozzle for a gas turbine engine using a primary fuel and a secondary fuel. The fuel nozzle may include a number of primary fuel injection ports for the primary fuel, a water passage, a number of secondary fuel injection ports, and a secondary fuel evaporator system for atomizing the secondary fuel.

Fuel nozzle assembly having a premix flame stabilizer

A fuel nozzle assembly (100) includes a premix chamber (114), an air flow divider (116) extending radially and axially within the premix chamber (114) between an inner wall (102) and an outer wall (104) and a plurality of guide vanes (122) disposed within the premix chamber (114). One or more of the guide vanes (122) includes a fuel port (130) in fluid communication with the flow divider (116). The fuel nozzle assembly (100) further includes a premix plate (110) that extends radially between the inner and outer walls (102), (104) and circumferentially between first and second side walls (106), (108) downstream from the fuel ports (130). The premix plate (110) includes an upstream side (142) axially spaced from a downstream side (144) and a plurality of passages (146) that provide for fluid flow from the premix chamber (114) through the premix plate (110).

Turbine system with exhaust gas recirculation, separation and extraction

A system includes a turbine combustor having a first volume (76) configured to receive a combustion fluid and to direct the combustion fluid into a combustion chamber (60) and a second volume (92) configured to receive a first flow of an exhaust gas. The second volume is configured to direct a first portion of the first flow of the exhaust gas into the combustion chamber and to direct a second portion of the first flow of the exhaust gas into a third volume isolated from the first volume. The third volume is in fluid communication with an extraction conduit (46) that is configured to direct the second portion of the first flow of the exhaust gas out of the turbine combustor.

Segmented annular ring-manifold quaternary fuel distributor

Brenner und Verfahren zur Brennstoffzufuhr zu einem Brenner

Ein Brenner (10) enthält eine Kappe (16), eine Buchse (20) ein Übergangsstück (24) und eine Brennkammer (22), die stromabwärts der Kappe (16) angeordnet ist und durch die Kappe und die Buchse gebildet ist. Eine Sekundärdüse (40), die im Umfang um die Buchse (20) oder das Übergangsstück (24) angeordnet ist, enthält einen zentralen Körper, einen Fluiddurchlass durch den zentralen Körper, einen den zentralen Körper in Umfangsrichtung umschließenden Kragen und einen Ringdurchlass zwischen dem zentralen Körper und dem Kragen. Ein Verfahren zur Brennstoffzufuhr zu einem Brenner (10) enthält das Einströmen von Brennstoff durch eine Primärdüse, die radial in einem geschlossenen Ende des Brenners angeordnet ist und das Einströmen von Brennstoff durch eine Sekundärdüse (40) die im Umfang um und durchgehend durch die Buchse (20) und/oder das Übergangstück angeordnet ist. Die Sekundärdüse (40) enthält einen zentralen Körper, einen Fluiddurchlass durch den zentralen Körper, einen zumindest einen Abschnitt des zentralen Körpers (44) in Umfangsrichtung umschließenden Kragen und einen Ringdurchlass zwischen dem zentralen Körper und dem Kragen.

Fuel nozzle assembly having a premix flame stabilizer

A fuel nozzle assembly for use in a gas turbine includes a center body, an outer tube that at least partially surrounds the center body, a premix flow passage that is defined radially between the center body and the outer tube, and a plurality of fuel ports that is disposed between the center body and the outer tube within the premix flow passage. The fuel nozzle assembly also includes a baffle plate that extends radially outwardly from the center body to the outer tube across a downstream end portion of the fuel nozzle assembly. The baffle plate includes an upstream side that is axially spaced from a downstream side and a plurality of passages. The passages provide for fluid flow from the premix flow passage through the baffle plate.

Fuel nozzle assembly having a premix fuel stabilizer

A fuel nozzle assembly includes a premix chamber, an air flow divider extending radially and axially within the premix chamber between an inner wall and an outer wall and a plurality of guide vanes disposed within the premix chamber. One or more of the guide vanes includes a fuel port in fluid communication with the flow divider. The fuel nozzle assembly further includes a premix plate that extends radially between the inner and outer walls and circumferentially between first and second side walls downstream from the fuel ports. The premix plate includes an upstream side axially spaced from a downstream side and a plurality of passages that provide for fluid flow from the premix chamber through the premix plate.

Multi-zone combustor

A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section.