CA2782196C - Burner for a turbine - Google Patents
Burner for a turbine Download PDFInfo
- Publication number
- CA2782196C CA2782196C CA2782196A CA2782196A CA2782196C CA 2782196 C CA2782196 C CA 2782196C CA 2782196 A CA2782196 A CA 2782196A CA 2782196 A CA2782196 A CA 2782196A CA 2782196 C CA2782196 C CA 2782196C
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- fuel
- burner
- fuel supply
- oxidizing agent
- supply tube
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Feeding And Controlling Fuel (AREA)
- Combustion Of Fluid Fuel (AREA)
Abstract
The invention relates to a burner for a turbine, comprising: a flame tube, in which a combustion chamber is formed, a jacket, which encloses the flame tube radially from the outside at a predetermined distance so that an oxidant collection chamber is formed between the flame tube and the jacket, a burner bottom, which bounds the oxidant collection chamber and the combustion chamber at an axial end of the burner, and a swirl generator, which is arranged axially between the flame tube and the burner bottom and axially adjacent to the burner bottom and radially adjacent to the oxidant collection chamber, for feeding a fuel-oxidant mixture into the combustion chamber, wherein the swirl generator has a plurality of guide blades arranged in a circumferential direction of the burner at a circumferential distance from each other so that the distances between the guide blades form a plurality of radial inlet passages to the combustion chamber that each have a tangential component in the course thereof, wherein a fuel supply tube is provided in the inlet flow area of at least some of the inlet passages, which fuel supply tube extends through the respective inlet passage in an axial direction of the burner and transversely to an oxidant flow direction, and wherein each fuel supply tube has at least one fuel outlet opening in the wall thereof, by means of which fuel outlet opening fuel can be mixed into the respective inlet passage with a directional component extending transversely to the oxidant flow direction.
Description
:A 02782196 2012 05 29 Burner for a Turbine The invention relates to a burner for a turbine, and more particularly to a burner that is provided with a device for premixing oxidizing agent and fuel for a turbine.
So as to achieve low emissions values, so-called "premix burners" are used in turbines, for example in gas turbines. By using the premix technology, the mixing process of fuel and oxidizing agent, such as air, is decoupled from the actual combustion process, which is to say it is provided upstream. As a result, the peak temperatures during combustion can be lowered. At the same time, the residence time of the fuel/oxidizing agent mixture (for example fuel/air mixture) in the reaction zone can be shortened. This reduces in particular the formation of NOx (especially thermal N0x). A
variety of "premix burners" are in use with atmospheric combustion and combustion under pressure. Various burners are also used in the field of gas turbines. In an optimal burner, the combustion process should be stable, controlled, low in harmful substances, and as complete as possible in a wide operating range. In this process, the quality of the mixture composed of fuel and oxidizing agent is always the focus of attention. The mixture plays a decisive role for the local combustion temperature, and hence for the reaction products, which is to say emissions. For this reason, the location and aerodynamics of fuel injection must be carefully selected.
DE 10 2008 019 117 Al describes a burner that is provided with a device for premixing air and fuel for a turbine. According to this document, the burner has a cylindrical combustion chamber for gaseous or liquid fuel and a main injector. The combustion chamber is delimited in an axial direction of the
So as to achieve low emissions values, so-called "premix burners" are used in turbines, for example in gas turbines. By using the premix technology, the mixing process of fuel and oxidizing agent, such as air, is decoupled from the actual combustion process, which is to say it is provided upstream. As a result, the peak temperatures during combustion can be lowered. At the same time, the residence time of the fuel/oxidizing agent mixture (for example fuel/air mixture) in the reaction zone can be shortened. This reduces in particular the formation of NOx (especially thermal N0x). A
variety of "premix burners" are in use with atmospheric combustion and combustion under pressure. Various burners are also used in the field of gas turbines. In an optimal burner, the combustion process should be stable, controlled, low in harmful substances, and as complete as possible in a wide operating range. In this process, the quality of the mixture composed of fuel and oxidizing agent is always the focus of attention. The mixture plays a decisive role for the local combustion temperature, and hence for the reaction products, which is to say emissions. For this reason, the location and aerodynamics of fuel injection must be carefully selected.
DE 10 2008 019 117 Al describes a burner that is provided with a device for premixing air and fuel for a turbine. According to this document, the burner has a cylindrical combustion chamber for gaseous or liquid fuel and a main injector. The combustion chamber is delimited in an axial direction of the
2 burner on one side by a burner bottom, and radially by a flame tube. The main injector is used to inject a premixed fuel/air mixture. Injection takes place radially to a longitudinal axis of the burner via main nozzles, which open into a radial swirler. The radial swirler is disposed between the burner bottom and the flame tube and causes a swirling momentum to act on the fuel/air mixture so that the same enters the combustion chamber in a swirled manner.
Other burners that are provided with a device for premixing oxidizing agent and fuel are described in DE 198 59 21 OA 1 and in DE 38 19 898 A 1.
It is the object of the invention to provide a burner for a turbine, in which extremely homogeneous premixing of a fuel/oxidizing agent mixture, such as a fuel/air mixture, to be introduced in a combustor of a burner, is achieved in a simple and cost-effective manner.
According to the invention, a burner for a turbine comprises: a flame tube, in which a combustor is formed; a jacket, which encloses the flame tube from radially outside at a predetermined distance therefrom, whereby an oxidizing agent collecting chamber is formed between the flame tube and jacket; a burner bottom, which delimits the oxidizing agent collecting chamber and the combustor at an axial end of the burner;
and a swirler, which axially adjoins the burner bottom and radially adjoins the oxidizing agent collecting chamber and is disposed axially between the flame tube and burner bottom, for supplying a fuel/oxidizing agent mixture to the combustor, wherein the swirler comprises a plurality of guide vanes disposed along a circumferential direction of the burner at a circumferential distance from each other, :A 02782196 2012 05 29
Other burners that are provided with a device for premixing oxidizing agent and fuel are described in DE 198 59 21 OA 1 and in DE 38 19 898 A 1.
It is the object of the invention to provide a burner for a turbine, in which extremely homogeneous premixing of a fuel/oxidizing agent mixture, such as a fuel/air mixture, to be introduced in a combustor of a burner, is achieved in a simple and cost-effective manner.
According to the invention, a burner for a turbine comprises: a flame tube, in which a combustor is formed; a jacket, which encloses the flame tube from radially outside at a predetermined distance therefrom, whereby an oxidizing agent collecting chamber is formed between the flame tube and jacket; a burner bottom, which delimits the oxidizing agent collecting chamber and the combustor at an axial end of the burner;
and a swirler, which axially adjoins the burner bottom and radially adjoins the oxidizing agent collecting chamber and is disposed axially between the flame tube and burner bottom, for supplying a fuel/oxidizing agent mixture to the combustor, wherein the swirler comprises a plurality of guide vanes disposed along a circumferential direction of the burner at a circumferential distance from each other, :A 02782196 2012 05 29
3 whereby the respective distances between the guide vanes form a plurality of radial inlet passages to the combustor which each have a tangential component, wherein a fuel supply tube, which extends, relative to the length thereof, in an axial direction of the burner and transversely to an oxidizing agent flow direction through the respective inlet passage, is provided in a respective inlet flow region of each of at least some of the plurality of inlet passages, and wherein the wall of each fuel supply tube has at least one fuel dispensing opening which is radial relative to the fuel supply tube and via which fuel can be admixed into the respective inlet passage with a directional component that is transverse to the oxidizing agent flow direction.
Air is the preferred oxidizing agent and is fed at atmospheric or elevated pressure to the oxidizing agent collecting chamber.
Because in the burner according to the invention fuel injection takes place within the inlet passages or air ducts of the swirler through individual fuel supply tubes with a directional component that is transverse to the oxidizing agent flow direction, extremely homogeneous premixing of the fuel/oxidizing agent mixture, such as a fuel/air mixture, to be introduced in the combustor of the burner, is achieved in a simple and cost-effective manner.
Because the fuel dispensing opening(s) can be freely designed, and preferably is or are configured as a borehole, and because the positioning of the fuel supply tubes and the fuel dispensing opening(s) within the respective inlet flow regions or at the respective fuel supply tubes can be freely selected, optimal premixing of fuel (for example fuel gas) and oxidizing agent (for example air) can be achieved. If the fuel composition changes, the sizes and shapes of the fuel dispensing openings can be adjusted.
:A 02782196 2012 05 29
Air is the preferred oxidizing agent and is fed at atmospheric or elevated pressure to the oxidizing agent collecting chamber.
Because in the burner according to the invention fuel injection takes place within the inlet passages or air ducts of the swirler through individual fuel supply tubes with a directional component that is transverse to the oxidizing agent flow direction, extremely homogeneous premixing of the fuel/oxidizing agent mixture, such as a fuel/air mixture, to be introduced in the combustor of the burner, is achieved in a simple and cost-effective manner.
Because the fuel dispensing opening(s) can be freely designed, and preferably is or are configured as a borehole, and because the positioning of the fuel supply tubes and the fuel dispensing opening(s) within the respective inlet flow regions or at the respective fuel supply tubes can be freely selected, optimal premixing of fuel (for example fuel gas) and oxidizing agent (for example air) can be achieved. If the fuel composition changes, the sizes and shapes of the fuel dispensing openings can be adjusted.
:A 02782196 2012 05 29
4 According to one embodiment of the invention, each of the inlet passages is provided with a fuel supply tube.
This advantageously promotes particularly homogeneous mixing of fuel and oxidizing agent before introduction in the combustor.
According to a further embodiment of the invention, at least one of the fuel supply tubes is disposed in the respective inlet passage.
This embodiment of the invention represents an advantageous variant for arranging one, or more, or all fuel supply tubes, wherein the respective position in the inlet passage can be freely selected and thus the mixing length of fuel and oxidizing agent can be varied freely.
According to yet another embodiment of the invention, at least one of the fuel supply tubes is disposed in the oxidizing agent flow direction directly in front of the respective inlet passages, which is to say at the beginning of the inlet flow region.
This embodiment of the invention represents a further advantageous variant for arranging one, or more, or all fuel supply tubes, wherein the mixing length or mixing distance of fuel and oxidizing agent is maximized.
:A 02782196 2012 05 29 According to still another embodiment of the invention, at least one of the fuel supply tubes is disposed eccentrically in the respective inlet passage relative to a longitudinal central axis of the respective inlet passage.
This embodiment of the invention represents another advantageous variant for arranging one, or more, or all fuel supply tubes, wherein the respective eccentric position in the inlet passage transversely to the longitudinal central axis thereof can be freely selected and thus the swirling intensity of the fuel can be varied freely. According to one embodiment of the invention, at least one of the fuel supply tubes is, or several or all fuel supply tubes are, disposed centrally in the respective inlet passage relative to the longitudinal central axis of the respective inlet passage.
According to a further embodiment of the invention, at least one of the fuel supply tubes comprises a plurality of fuel dispensing openings, which are disposed along the length of the fuel supply tube at a distance from each other.
This embodiment of the invention allows the homogeneous mixing of fuel and oxidizing agent to be improved even further. Several or all fuel supply tubes are thus preferably in each case provided with a plurality of fuel dispensing openings disposed at a distance from each other along the length of the fuel supply tubes.
According to yet another embodiment of the invention, at least one of the fuel supply tubes comprises two fuel dispensing openings, which are disposed in the same position relative to the length of the fuel supply tube, whereby fuel can be dispensed from the fuel supply tube with two opposing directional components via these two fuel dispensing openings.
:A 02782196 2012 05 29 According to this embodiment of the invention, the dispensing of fuel in opposing directions into the inlet passage utilizes the oxidizing agent flow on both sides of the fuel supply tube so as to generate turbulence in the fuel, whereby homogeneous mixing of fuel and oxidizing agent is further improved.
Preferably each of several or all of the fuel supply tubes comprises two fuel dispensing openings, which are disposed in the same position relative to the length of the fuel supply tube, whereby fuel can be dispensed from the fuel supply tube with two opposing directional components via these two fuel dispensing openings.
It is still even more preferred for each fuel dispensing opening of a respective fuel supply tube to have a fuel dispensing opening which is disposed in the same position relative to the length of the fuel supply tube and dispenses the fuel thereof with opposing directional components In addition to optimal "standard positions", it is of course also possible to perform individual optimizations with respect to emissions and backfiring behavior, depending on the fuel.
According to further embodiments of the invention, the two fuel dispensing openings, as seen looking in the cross-section of the respective fuel dispensing tube, are located diametrically opposed, or respective longitudinal central axes of the two fuel dispensing openings form an obtuse angle with each other.
This embodiment of the invention also allows the intensity of turbulence and entrainment of the fuel in the oxidizing agent to be influenced in a simple and :A 02782196 2012 05 29 efficient manner, and thus to be optimized for the respective application.
According to further embodiments of the invention, each fuel supply tube has a cylindrical cross-section or a hydrofoil-shaped cross-section, or other cross-sections that are suitable for optimal swirling. According to the invention, all fuel supply tubes can have the same cross-sectional shape.
Embodiments in which groups of fuel supply tubes are formed, wherein all fuel supply tubes within a group have the same cross-sectional shape, yet the groups have differing cross-sectional shapes, are likewise conceivable.
For example, the hydrofoil shape may prove to be advantageous so as to reduce direct mixing in the tube tail, which may be necessary notably with reactive fuels (such as hydrogen).
According to yet another embodiment of the invention, each of the fuel supply tubes is detachably mounted, whereby each fuel supply tube designed according to a predetermined fuel mixing configuration can be individually replaced, if necessary, with a fuel supply tube according to another predetermined fuel mixing configuration.
Given the easy replacement of the fuel supply tubes, the burner can be easily and quickly adapted to a fuel change. The burner according to the invention is typically suitable when using fuel gas as the fuel. The burner according to the invention, however, can also be operated with liquid fuel, wherein optionally special nozzles should be inserted in the fuel dispensing openings.
:A 02782196 2012 05 29 By using the central fuel supply tubes in the inlet passages of the swirler, optimal mixtures of fuel (such as fuel gas) and oxidizing agent (such as air) are possible. Lower emission values can thus be achieved. By individually designing the fuel dispensing openings and/or positioning the fuel supply tubes, it is also possible to react to locally varying oxidizing agent distributions, for example locally varying air distributions. Because of the central, replaceable fuel supply tubes, the solution according to the invention is very cost-effective.
The invention will be described in more detail hereafter based on preferred embodiments and with reference to the accompanying drawings.
FIG. 1 shows a schematic longitudinal sectional view of the construction of a burner of a gas turbine according to one embodiment of the invention;
FIG. 2 shows a schematic cross-sectional view of a part of the burner of FIG. 1, as seen looking along a line A-A in FIG. 1;
FIG. 3 shows enlarged partial views of three possible configuration variants of a fuel supply tube of an inlet passage of the burner of FIG. 2; and FIG. 4 shows two possible configuration variants of a fuel supply tube in an inlet passage of the burner according to the invention, as seen looking along a line B-B- in FIG. 2.
FIG. 1 shows the construction of a burner 1 of a gas turbine (not shown in its entirety) according to one embodiment of the invention.
The burner 1 comprises a flame tube 10, in which a combustor 11 is formed, and a tubular jacket 20, which encloses the flame tube 10 from radially :A 02782196 2012 05 29 outside at a predetermined distance therefrom, whereby an oxidizing agent collecting chamber 21 is formed between the flame tube 10 and jacket 20.
Fuel gas is provided as the fuel for the burner 1, and atmospheric air is provided as the oxidizing agent for the fuel gas, the air being compressed by means of a compressor (not shown) and then supplied to the oxidizing agent collecting chamber 21.
The burner 1 moreover comprises a burner bottom 30, which delimits the oxidizing agent collecting chamber 21 and the combustor 11 at an axial end of the burner1, and a swirler 40, which axially adjoins the burner bottom 30 and radially adjoins the oxidizing agent collecting chamber 21 and is disposed axially between the flame tube 10 and burner bottom 30, for supplying a fuel/oxidizing agent mixture BOG to the combustion chamber 11.
With additional reference to FIG. 2, which shows a sectional view of a part of the burner of FIG. 1 as seen looking along a line A-A in FIG. 1, the swirler comprises a plurality of (here eight) guide vanes 41 which are disposed at a circumferential distance from each other along a circumferential direction UR
of the burner 1.
The guide vanes 41 are shaped and disposed such that the respective distances between the guide vanes 41 form a plurality of (here eight) radial inlet passages 42 to the combustor 11 which each have a tangential component.
A fuel supply tube 43a, 43b, 43c, 43d, which extends, relative to the length thereof, in an axial direction AR (see FIG. 1) of the burner 1 and transversely to the oxidizing agent flow direction OR through the respective inlet passage 42, is provided in each inlet flow region of at least some of the plurality of :A 02782196 2012 05 29 inlet passages 42.
While FIG. 2 shows only a fuel supply tube 43a, 43b, 43c, 43d in each of four of the eight inlet passages 42, according to embodiments of the invention which are not shown it is also possible to provide fuel supply tubes 43a, 43b, 43c, 43d in each of more, or fewer or all, inlet passages 42.
As is shown in FIGS. 3 and 4, the wall of each fuel supply tube 43a, 43b, 43c, 43d has at least one fuel dispensing opening 44, 45 which is radial relative to the fuel supply tube 43a, 43b, 43c, 43d and via which fuel BS can be admixed into the respective inlet passage 42 with a directional component that is transverse to the oxidizing agent flow direction OS.
Preferably each fuel dispensing opening 44, 45 is designed as a borehole or as a nozzle insert.
As is apparent from FIG. 2, one, more or all fuel supply tubes 43a, 43b, 43d can be disposed directly in the respective inlet passages 42. As is also apparent from FIG. 2, the fuel supply tubes 43a, 43b, 43d can be disposed within the respective inlet passages 42 in differing positions along the length of the respective inlet passages 42.
On the other hand, one, more or all fuel supply tubes 43c can be disposed in the oxidizing agent flow direction OS directly in front of the respective inlet passages 42 (which is to say, at the entrance of the respective inlet passages 42, partially or entirely in the oxidizing agent collecting chamber 21).
:A 02782196 2012 05 29 As is likewise apparent from FIG. 2, one, more or all fuel supply tubes 43a, 43b, 43c can be disposed centrally in the respective inlet passages 42 relative to the central longitudinal axes L of the respective inlet passages 42.
On the other hand, one, more or all fuel supply tubes 43d can be disposed eccentrically in the respective inlet passages 42 relative to the center longitudinal axes L of the same.
As is apparent from FIG. 4, one, more or all fuel supply tubes 43a, 43b, 43c, 43d may comprise a plurality of fuel dispensing openings 44, 45, which are disposed along the respective length of the fuel supply tubes 43a, 43h, 43c, 43d at a distance from each other [variant a) in FIG. 4). On the other hand, one, more or all fuel supply tubes 43a, 43b, 43c, 43d can comprise merely a single fuel dispensing opening 44, 45 relative to the respective length of the fuel supply tubes 43a, 43b, 43c, 43d [variant b) in FIG. 4].
As is apparent from FIG. 3, one, more or all central fuel supply tubes 43a, 43b, 43c (denoted by 43a-c in FIG. 3), and one, more or all eccentric fuel supply tubes 43d (not shown in FIG. 3), can have two fuel dispensing openings 44, 45, which are disposed in the same position relative to the length of the fuel supply tube, whereby fuel BS can be dispensed from the respective fuel supply tube 43a, 43b, 43c with two mutually opposing directional components (as indicated by the exit arrows for the fuel BS
directed oppositely from each other) via these two fuel dispensing openings 44, 45.
As is also apparent from FIG. 3, the two fuel dispensing openings 44, 45 can, as seen looking in the cross-section of the respective fuel supply tube 43a, 43b, 43c, 43d, be located diametrically opposed [variant a) in FIG. 3], or respective longitudinal central axes Ll, L2 of the two fuel dispensing :A 02782196 2012 05 29 openings 44, 45 can form an obtuse angle a (45'<a<180 ) with each other [variants b) and c) in FIG. 3].
Within the scope of the invention it would, of course, also be possible to alternate the fuel dispensing openings 44, 45 which are diametrically opposed, or opposed at the obtuse angle a, along the length of the fuel supply tube 43a, 43b, 43c, 43d, whereby only a single fuel dispensing opening 44, 45 is disposed at each longitudinal position of the fuel supply tube 43a, 43h, 43c, 43d.
As is apparent from FIGS. 2 to 4, the fuel supply tubes 43a, 43b, 43c, 43d each have a cylindrical cross-section. However, according to embodiments of the invention which are not shown, the fuel supply tubes 43a, 43b, 43c, 43d can also have a hydrofoil-shaped cross-section, or other cross-sections suitable for homogeneously mixing oxidizing agent and fuel. A hydrofoil shape is shown, for example, in DE 38 19 898 Al in FIG. 2 with respect to the guide vanes.
While FIGS. 1 to 4 do not show this in detail, each of the fuel supply tubes 43a, 43b, 43c, 43d is detachably mounted in the burner 1, whereby each fuel supply tube 43a, 43b, 43c, 43d designed according to a predetermined fuel mixing configuration (position of the fuel supply tube in the inlet passage, number and arrangement of fuel dispensing openings, cross-sectional shape of the fuel supply tube), if needed, can be individually replaced with a fuel supply tube 43a, 43b, 43c, 43d according to another predetermined fuel mixing configuration.
For this purpose, the fuel supply tubes 43a, 43b, 43c, 43d (denoted by 43a-d in FIG. 4), as shown in FIG. 4, are detachably inserted in corresponding openings in the burner bottom 30, wherein a longitudinal end of each fuel :A 02782196 2012 05 29 supply tube 43a, 43b, 43c, 43d has a flange section or head section 46, 47 which is seated against the burner bottom 30 on the side thereof facing away from the swirler 40 and is bolted to the burner bottom 30, for example by means of bolts (not shown).
Finally, it should be noted that each fuel supply tube 43a, 43b, 43c, 43d is, of course, fluidically connected via corresponding lines and control valves (neither is shown) to a fuel source (not shown), such as a fuel gas tank.
:A 02782196 2012 05 29 List of reference numerals 1 Burner Flame tube 11 Cornbustor Jacket 21 Oxidizing agent collecting chamber 21 Burner bottom Swirler 41 Guide vane 42 Inlet passage 43a Fuel supply tube 43b Fuel supply tube 43c Fuel supply tube 43d Fuel supply tube 44 Fuel dispensing opening Fuel dispensing opening 46 Head section 47 Head section L Longitudinal central axis L1 Longitudinal central axis L2 Longitudinal central axis a Obtuse angle UR Circumferential direction AR Axial direction OR Oxidizing agent flow direction BS Fuel BOG Fuel/oxidizing agent mixture
This advantageously promotes particularly homogeneous mixing of fuel and oxidizing agent before introduction in the combustor.
According to a further embodiment of the invention, at least one of the fuel supply tubes is disposed in the respective inlet passage.
This embodiment of the invention represents an advantageous variant for arranging one, or more, or all fuel supply tubes, wherein the respective position in the inlet passage can be freely selected and thus the mixing length of fuel and oxidizing agent can be varied freely.
According to yet another embodiment of the invention, at least one of the fuel supply tubes is disposed in the oxidizing agent flow direction directly in front of the respective inlet passages, which is to say at the beginning of the inlet flow region.
This embodiment of the invention represents a further advantageous variant for arranging one, or more, or all fuel supply tubes, wherein the mixing length or mixing distance of fuel and oxidizing agent is maximized.
:A 02782196 2012 05 29 According to still another embodiment of the invention, at least one of the fuel supply tubes is disposed eccentrically in the respective inlet passage relative to a longitudinal central axis of the respective inlet passage.
This embodiment of the invention represents another advantageous variant for arranging one, or more, or all fuel supply tubes, wherein the respective eccentric position in the inlet passage transversely to the longitudinal central axis thereof can be freely selected and thus the swirling intensity of the fuel can be varied freely. According to one embodiment of the invention, at least one of the fuel supply tubes is, or several or all fuel supply tubes are, disposed centrally in the respective inlet passage relative to the longitudinal central axis of the respective inlet passage.
According to a further embodiment of the invention, at least one of the fuel supply tubes comprises a plurality of fuel dispensing openings, which are disposed along the length of the fuel supply tube at a distance from each other.
This embodiment of the invention allows the homogeneous mixing of fuel and oxidizing agent to be improved even further. Several or all fuel supply tubes are thus preferably in each case provided with a plurality of fuel dispensing openings disposed at a distance from each other along the length of the fuel supply tubes.
According to yet another embodiment of the invention, at least one of the fuel supply tubes comprises two fuel dispensing openings, which are disposed in the same position relative to the length of the fuel supply tube, whereby fuel can be dispensed from the fuel supply tube with two opposing directional components via these two fuel dispensing openings.
:A 02782196 2012 05 29 According to this embodiment of the invention, the dispensing of fuel in opposing directions into the inlet passage utilizes the oxidizing agent flow on both sides of the fuel supply tube so as to generate turbulence in the fuel, whereby homogeneous mixing of fuel and oxidizing agent is further improved.
Preferably each of several or all of the fuel supply tubes comprises two fuel dispensing openings, which are disposed in the same position relative to the length of the fuel supply tube, whereby fuel can be dispensed from the fuel supply tube with two opposing directional components via these two fuel dispensing openings.
It is still even more preferred for each fuel dispensing opening of a respective fuel supply tube to have a fuel dispensing opening which is disposed in the same position relative to the length of the fuel supply tube and dispenses the fuel thereof with opposing directional components In addition to optimal "standard positions", it is of course also possible to perform individual optimizations with respect to emissions and backfiring behavior, depending on the fuel.
According to further embodiments of the invention, the two fuel dispensing openings, as seen looking in the cross-section of the respective fuel dispensing tube, are located diametrically opposed, or respective longitudinal central axes of the two fuel dispensing openings form an obtuse angle with each other.
This embodiment of the invention also allows the intensity of turbulence and entrainment of the fuel in the oxidizing agent to be influenced in a simple and :A 02782196 2012 05 29 efficient manner, and thus to be optimized for the respective application.
According to further embodiments of the invention, each fuel supply tube has a cylindrical cross-section or a hydrofoil-shaped cross-section, or other cross-sections that are suitable for optimal swirling. According to the invention, all fuel supply tubes can have the same cross-sectional shape.
Embodiments in which groups of fuel supply tubes are formed, wherein all fuel supply tubes within a group have the same cross-sectional shape, yet the groups have differing cross-sectional shapes, are likewise conceivable.
For example, the hydrofoil shape may prove to be advantageous so as to reduce direct mixing in the tube tail, which may be necessary notably with reactive fuels (such as hydrogen).
According to yet another embodiment of the invention, each of the fuel supply tubes is detachably mounted, whereby each fuel supply tube designed according to a predetermined fuel mixing configuration can be individually replaced, if necessary, with a fuel supply tube according to another predetermined fuel mixing configuration.
Given the easy replacement of the fuel supply tubes, the burner can be easily and quickly adapted to a fuel change. The burner according to the invention is typically suitable when using fuel gas as the fuel. The burner according to the invention, however, can also be operated with liquid fuel, wherein optionally special nozzles should be inserted in the fuel dispensing openings.
:A 02782196 2012 05 29 By using the central fuel supply tubes in the inlet passages of the swirler, optimal mixtures of fuel (such as fuel gas) and oxidizing agent (such as air) are possible. Lower emission values can thus be achieved. By individually designing the fuel dispensing openings and/or positioning the fuel supply tubes, it is also possible to react to locally varying oxidizing agent distributions, for example locally varying air distributions. Because of the central, replaceable fuel supply tubes, the solution according to the invention is very cost-effective.
The invention will be described in more detail hereafter based on preferred embodiments and with reference to the accompanying drawings.
FIG. 1 shows a schematic longitudinal sectional view of the construction of a burner of a gas turbine according to one embodiment of the invention;
FIG. 2 shows a schematic cross-sectional view of a part of the burner of FIG. 1, as seen looking along a line A-A in FIG. 1;
FIG. 3 shows enlarged partial views of three possible configuration variants of a fuel supply tube of an inlet passage of the burner of FIG. 2; and FIG. 4 shows two possible configuration variants of a fuel supply tube in an inlet passage of the burner according to the invention, as seen looking along a line B-B- in FIG. 2.
FIG. 1 shows the construction of a burner 1 of a gas turbine (not shown in its entirety) according to one embodiment of the invention.
The burner 1 comprises a flame tube 10, in which a combustor 11 is formed, and a tubular jacket 20, which encloses the flame tube 10 from radially :A 02782196 2012 05 29 outside at a predetermined distance therefrom, whereby an oxidizing agent collecting chamber 21 is formed between the flame tube 10 and jacket 20.
Fuel gas is provided as the fuel for the burner 1, and atmospheric air is provided as the oxidizing agent for the fuel gas, the air being compressed by means of a compressor (not shown) and then supplied to the oxidizing agent collecting chamber 21.
The burner 1 moreover comprises a burner bottom 30, which delimits the oxidizing agent collecting chamber 21 and the combustor 11 at an axial end of the burner1, and a swirler 40, which axially adjoins the burner bottom 30 and radially adjoins the oxidizing agent collecting chamber 21 and is disposed axially between the flame tube 10 and burner bottom 30, for supplying a fuel/oxidizing agent mixture BOG to the combustion chamber 11.
With additional reference to FIG. 2, which shows a sectional view of a part of the burner of FIG. 1 as seen looking along a line A-A in FIG. 1, the swirler comprises a plurality of (here eight) guide vanes 41 which are disposed at a circumferential distance from each other along a circumferential direction UR
of the burner 1.
The guide vanes 41 are shaped and disposed such that the respective distances between the guide vanes 41 form a plurality of (here eight) radial inlet passages 42 to the combustor 11 which each have a tangential component.
A fuel supply tube 43a, 43b, 43c, 43d, which extends, relative to the length thereof, in an axial direction AR (see FIG. 1) of the burner 1 and transversely to the oxidizing agent flow direction OR through the respective inlet passage 42, is provided in each inlet flow region of at least some of the plurality of :A 02782196 2012 05 29 inlet passages 42.
While FIG. 2 shows only a fuel supply tube 43a, 43b, 43c, 43d in each of four of the eight inlet passages 42, according to embodiments of the invention which are not shown it is also possible to provide fuel supply tubes 43a, 43b, 43c, 43d in each of more, or fewer or all, inlet passages 42.
As is shown in FIGS. 3 and 4, the wall of each fuel supply tube 43a, 43b, 43c, 43d has at least one fuel dispensing opening 44, 45 which is radial relative to the fuel supply tube 43a, 43b, 43c, 43d and via which fuel BS can be admixed into the respective inlet passage 42 with a directional component that is transverse to the oxidizing agent flow direction OS.
Preferably each fuel dispensing opening 44, 45 is designed as a borehole or as a nozzle insert.
As is apparent from FIG. 2, one, more or all fuel supply tubes 43a, 43b, 43d can be disposed directly in the respective inlet passages 42. As is also apparent from FIG. 2, the fuel supply tubes 43a, 43b, 43d can be disposed within the respective inlet passages 42 in differing positions along the length of the respective inlet passages 42.
On the other hand, one, more or all fuel supply tubes 43c can be disposed in the oxidizing agent flow direction OS directly in front of the respective inlet passages 42 (which is to say, at the entrance of the respective inlet passages 42, partially or entirely in the oxidizing agent collecting chamber 21).
:A 02782196 2012 05 29 As is likewise apparent from FIG. 2, one, more or all fuel supply tubes 43a, 43b, 43c can be disposed centrally in the respective inlet passages 42 relative to the central longitudinal axes L of the respective inlet passages 42.
On the other hand, one, more or all fuel supply tubes 43d can be disposed eccentrically in the respective inlet passages 42 relative to the center longitudinal axes L of the same.
As is apparent from FIG. 4, one, more or all fuel supply tubes 43a, 43b, 43c, 43d may comprise a plurality of fuel dispensing openings 44, 45, which are disposed along the respective length of the fuel supply tubes 43a, 43h, 43c, 43d at a distance from each other [variant a) in FIG. 4). On the other hand, one, more or all fuel supply tubes 43a, 43b, 43c, 43d can comprise merely a single fuel dispensing opening 44, 45 relative to the respective length of the fuel supply tubes 43a, 43b, 43c, 43d [variant b) in FIG. 4].
As is apparent from FIG. 3, one, more or all central fuel supply tubes 43a, 43b, 43c (denoted by 43a-c in FIG. 3), and one, more or all eccentric fuel supply tubes 43d (not shown in FIG. 3), can have two fuel dispensing openings 44, 45, which are disposed in the same position relative to the length of the fuel supply tube, whereby fuel BS can be dispensed from the respective fuel supply tube 43a, 43b, 43c with two mutually opposing directional components (as indicated by the exit arrows for the fuel BS
directed oppositely from each other) via these two fuel dispensing openings 44, 45.
As is also apparent from FIG. 3, the two fuel dispensing openings 44, 45 can, as seen looking in the cross-section of the respective fuel supply tube 43a, 43b, 43c, 43d, be located diametrically opposed [variant a) in FIG. 3], or respective longitudinal central axes Ll, L2 of the two fuel dispensing :A 02782196 2012 05 29 openings 44, 45 can form an obtuse angle a (45'<a<180 ) with each other [variants b) and c) in FIG. 3].
Within the scope of the invention it would, of course, also be possible to alternate the fuel dispensing openings 44, 45 which are diametrically opposed, or opposed at the obtuse angle a, along the length of the fuel supply tube 43a, 43b, 43c, 43d, whereby only a single fuel dispensing opening 44, 45 is disposed at each longitudinal position of the fuel supply tube 43a, 43h, 43c, 43d.
As is apparent from FIGS. 2 to 4, the fuel supply tubes 43a, 43b, 43c, 43d each have a cylindrical cross-section. However, according to embodiments of the invention which are not shown, the fuel supply tubes 43a, 43b, 43c, 43d can also have a hydrofoil-shaped cross-section, or other cross-sections suitable for homogeneously mixing oxidizing agent and fuel. A hydrofoil shape is shown, for example, in DE 38 19 898 Al in FIG. 2 with respect to the guide vanes.
While FIGS. 1 to 4 do not show this in detail, each of the fuel supply tubes 43a, 43b, 43c, 43d is detachably mounted in the burner 1, whereby each fuel supply tube 43a, 43b, 43c, 43d designed according to a predetermined fuel mixing configuration (position of the fuel supply tube in the inlet passage, number and arrangement of fuel dispensing openings, cross-sectional shape of the fuel supply tube), if needed, can be individually replaced with a fuel supply tube 43a, 43b, 43c, 43d according to another predetermined fuel mixing configuration.
For this purpose, the fuel supply tubes 43a, 43b, 43c, 43d (denoted by 43a-d in FIG. 4), as shown in FIG. 4, are detachably inserted in corresponding openings in the burner bottom 30, wherein a longitudinal end of each fuel :A 02782196 2012 05 29 supply tube 43a, 43b, 43c, 43d has a flange section or head section 46, 47 which is seated against the burner bottom 30 on the side thereof facing away from the swirler 40 and is bolted to the burner bottom 30, for example by means of bolts (not shown).
Finally, it should be noted that each fuel supply tube 43a, 43b, 43c, 43d is, of course, fluidically connected via corresponding lines and control valves (neither is shown) to a fuel source (not shown), such as a fuel gas tank.
:A 02782196 2012 05 29 List of reference numerals 1 Burner Flame tube 11 Cornbustor Jacket 21 Oxidizing agent collecting chamber 21 Burner bottom Swirler 41 Guide vane 42 Inlet passage 43a Fuel supply tube 43b Fuel supply tube 43c Fuel supply tube 43d Fuel supply tube 44 Fuel dispensing opening Fuel dispensing opening 46 Head section 47 Head section L Longitudinal central axis L1 Longitudinal central axis L2 Longitudinal central axis a Obtuse angle UR Circumferential direction AR Axial direction OR Oxidizing agent flow direction BS Fuel BOG Fuel/oxidizing agent mixture
Claims (9)
1. A burner (1) for a turbine, comprising:
a flame tube (10), in which a combustor (11) is formed, a jacket (20), which encloses the flame tube (10) from radially outside at a predetermined distance therefrom, whereby an oxidizing agent collecting chamber (21) is formed between the flame tube (10) and jacket (20);
a burner bottom (30), which delimits the oxidizing agent collecting chamber (21) and the combustor (11) at an axial end of the burner (1); and a swirler (40), which axially adjoins the burner bottom (30) and radially adjoins the oxidizing agent collecting chamber (21) and is disposed axially between the flame tube (10) and burner bottom (30), for supplying a fuel/oxidizing agent mixture (BOG) to the combustor (11), wherein the swirler (40) comprises a plurality of guide vanes (41) which are disposed along a circumferential direction (UR) of the burner (1) at a circumferential distance from each other, whereby the respective distances between the guide vanes (41) form a plurality of radial inlet passages (42) to the combustor (11) which each have a tangential component, wherein a fuel supply tube (43a, 43b, 43c, 43d), which extends, relative to the length thereof, in an axial direction (AR) of the burner (1) and transversely to the oxidizing agent flow direction (OR) through the respective inlet passage (42), is provided in each inlet flow region of at least some of the plurality of inlet passages (42), and wherein the wall of each supply tube (43a, 43b, 43c, 43d) has at least one fuel dispensing opening (44, 45) which is radial relative to the fuel supply tube (43a, 43b, 43c, 43d) and via which fuel (BS) can be admixed into the respective inlet passage (42) with a directional component that is transverse to the oxidizing agent flow direction (OR), characterized in that the fuel supply tubes (43a, 43b, 43c) may be disposed in a wide variety of positions along the length of each of the inlet passages (42) such that the swirling intensity of the fuel/oxidizing agent mixture is freely variable by a different extension of the the mixing section.
a flame tube (10), in which a combustor (11) is formed, a jacket (20), which encloses the flame tube (10) from radially outside at a predetermined distance therefrom, whereby an oxidizing agent collecting chamber (21) is formed between the flame tube (10) and jacket (20);
a burner bottom (30), which delimits the oxidizing agent collecting chamber (21) and the combustor (11) at an axial end of the burner (1); and a swirler (40), which axially adjoins the burner bottom (30) and radially adjoins the oxidizing agent collecting chamber (21) and is disposed axially between the flame tube (10) and burner bottom (30), for supplying a fuel/oxidizing agent mixture (BOG) to the combustor (11), wherein the swirler (40) comprises a plurality of guide vanes (41) which are disposed along a circumferential direction (UR) of the burner (1) at a circumferential distance from each other, whereby the respective distances between the guide vanes (41) form a plurality of radial inlet passages (42) to the combustor (11) which each have a tangential component, wherein a fuel supply tube (43a, 43b, 43c, 43d), which extends, relative to the length thereof, in an axial direction (AR) of the burner (1) and transversely to the oxidizing agent flow direction (OR) through the respective inlet passage (42), is provided in each inlet flow region of at least some of the plurality of inlet passages (42), and wherein the wall of each supply tube (43a, 43b, 43c, 43d) has at least one fuel dispensing opening (44, 45) which is radial relative to the fuel supply tube (43a, 43b, 43c, 43d) and via which fuel (BS) can be admixed into the respective inlet passage (42) with a directional component that is transverse to the oxidizing agent flow direction (OR), characterized in that the fuel supply tubes (43a, 43b, 43c) may be disposed in a wide variety of positions along the length of each of the inlet passages (42) such that the swirling intensity of the fuel/oxidizing agent mixture is freely variable by a different extension of the the mixing section.
2. The burner (1) according to claim 1, wherein at least one of the fuel supply tubes (43c) is disposed in the oxidizing agent flow direction (OR) directly in front of the respective inlet passage (42).
3. A burner (1) according to any one of claims 1 to 2, wherein at least one of the fuel supply tubes (43a, 43b, 43c) is disposed centrally in the respective inlet passage (42) relative to the longitudinal central axis (L) of the respective inlet passage (42).
4. A burner (1) according to any one of claims 1 to 3, wherein at least one of the fuel supply tubes (43d) is disposed eccentrically in the respective inlet passage (42) relative to the longitudinal central axis (L) of the respective inlet passage (42).
5. A burner (1) according to any one of claims 1 to 4, wherein at least one of the fuel supply tubes (43a, 43b, 43c, 43d) comprises a plurality of fuel dispensing openings (44, 45), which are disposed along the length of the fuel supply tube (43a, 43b, 43c, 43d) at a distance from each other.
6. A burner (1) according to any one of claims 1 to 5, wherein at least one of the fuel supply tubes (43a, 43b, 43c, 43d) comprises two fuel dispensing openings (44, 45), which are disposed in the same position relative to the length of the fuel supply tube (43a, 43b, 43c, 43d), whereby fuel (BS) can be dispensed from the fuel supply tube (43a, 43b, 43c, 43d) with two mutually opposing directional components via these two fuel dispensing openings (44, 45).
7. The burner (1) according to claim 6, wherein the two fuel dispensing openings (44, 45) are, as seen looking in the cross-section of the respective fuel supply tube (43a, 43b, 43c, 43d), located diametrically opposed from each other, or respective longitudinal central axes (L1, L2) of the two fuel dispensing openings (44, 45) can form an obtuse angle (a) with each other.
8. A burner (1) according to any one of claims 1 to 7, wherein each of the fuel supply tubes (43a, 43b, 43c, 43d) has a cylindrical cross-section or a hydrofoil-shaped cross-section.
9. A burner (1) according to any one of claims 1 to 8, wherein each of the fuel supply tubes (43a, 43b, 43c, 43d) is detachably mounted, whereby each fuel supply tube (43a, 43b, 43c, 43d) designed according to a predetermined fuel mixing configuration, if needed, can be individually replaced with a fuel supply tube (43a, 43b, 43c, 43d) according to another predetermined fuel mixing configuration.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102009054669.3 | 2009-12-15 | ||
| DE102009054669A DE102009054669A1 (en) | 2009-12-15 | 2009-12-15 | Burner for a turbine |
| PCT/DE2010/050074 WO2011072665A1 (en) | 2009-12-15 | 2010-09-28 | Burner for a turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2782196A1 CA2782196A1 (en) | 2011-06-23 |
| CA2782196C true CA2782196C (en) | 2014-07-29 |
Family
ID=43568285
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2782196A Active CA2782196C (en) | 2009-12-15 | 2010-09-28 | Burner for a turbine |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20120227407A1 (en) |
| EP (1) | EP2513562B1 (en) |
| JP (1) | JP2013517440A (en) |
| CA (1) | CA2782196C (en) |
| DE (1) | DE102009054669A1 (en) |
| WO (1) | WO2011072665A1 (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9581333B2 (en) * | 2012-05-01 | 2017-02-28 | Aerco International, Inc. | Igniter assembly and method for operating |
| US9677766B2 (en) * | 2012-11-28 | 2017-06-13 | General Electric Company | Fuel nozzle for use in a turbine engine and method of assembly |
| KR102184778B1 (en) * | 2013-12-19 | 2020-11-30 | 한화에어로스페이스 주식회사 | Swirler for gas turbine |
| JP6602004B2 (en) * | 2014-09-29 | 2019-11-06 | 川崎重工業株式会社 | Fuel injector and gas turbine |
| EP3098514A1 (en) * | 2015-05-29 | 2016-11-30 | Siemens Aktiengesellschaft | Combustor arrangement |
| US10215415B2 (en) * | 2015-09-23 | 2019-02-26 | General Electric Company | Premix fuel nozzle assembly cartridge |
| EP3236157A1 (en) | 2016-04-22 | 2017-10-25 | Siemens Aktiengesellschaft | Swirler for mixing fuel with air in a combustion engine |
| JP6995696B2 (en) * | 2018-05-28 | 2022-01-17 | 三菱重工業株式会社 | Fuel injection system and gas turbine |
| CN113310071B (en) * | 2021-06-16 | 2022-11-15 | 哈尔滨工程大学 | Coaxial staged combustor for low-pollution combustion chamber of gas fuel gas turbine |
| CN113834094B (en) * | 2021-09-15 | 2022-11-01 | 中国船舶重工集团公司第七0三研究所 | Nozzle with tangential rotational flow structure |
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| EP0169431B1 (en) * | 1984-07-10 | 1990-04-11 | Hitachi, Ltd. | Gas turbine combustor |
| DE3819898A1 (en) | 1988-06-11 | 1989-12-14 | Daimler Benz Ag | Combustion chamber for a thermal turbo-engine |
| US5117637A (en) * | 1990-08-02 | 1992-06-02 | General Electric Company | Combustor dome assembly |
| US5450724A (en) * | 1993-08-27 | 1995-09-19 | Northern Research & Engineering Corporation | Gas turbine apparatus including fuel and air mixer |
| US5394688A (en) * | 1993-10-27 | 1995-03-07 | Westinghouse Electric Corporation | Gas turbine combustor swirl vane arrangement |
| JPH09119641A (en) * | 1995-06-05 | 1997-05-06 | Allison Engine Co Inc | Low nitrogen-oxide dilution premixing module for gas-turbineengine |
| DE19532264C2 (en) * | 1995-09-01 | 2001-09-06 | Mtu Aero Engines Gmbh | Device for the preparation of a mixture of fuel and air in combustion chambers for gas turbine engines |
| US5647215A (en) * | 1995-11-07 | 1997-07-15 | Westinghouse Electric Corporation | Gas turbine combustor with turbulence enhanced mixing fuel injectors |
| GB2332509B (en) | 1997-12-19 | 2002-06-19 | Europ Gas Turbines Ltd | Fuel/air mixing arrangement for combustion apparatus |
| GB2333832A (en) * | 1998-01-31 | 1999-08-04 | Europ Gas Turbines Ltd | Multi-fuel gas turbine engine combustor |
| GB2334087A (en) * | 1998-02-03 | 1999-08-11 | Combustion Technology Internat | Combustor restrictor |
| GB9818160D0 (en) * | 1998-08-21 | 1998-10-14 | Rolls Royce Plc | A combustion chamber |
| FR2824625B1 (en) * | 2001-05-10 | 2003-08-15 | Inst Francais Du Petrole | DEVICE AND METHOD FOR INJECTING A LIQUID FUEL INTO AN AIRFLOW FOR A COMBUSTION CHAMBER |
| US6691515B2 (en) * | 2002-03-12 | 2004-02-17 | Rolls-Royce Corporation | Dry low combustion system with means for eliminating combustion noise |
| US7093445B2 (en) * | 2002-05-31 | 2006-08-22 | Catalytica Energy Systems, Inc. | Fuel-air premixing system for a catalytic combustor |
| US6786047B2 (en) * | 2002-09-17 | 2004-09-07 | Siemens Westinghouse Power Corporation | Flashback resistant pre-mix burner for a gas turbine combustor |
| US6868676B1 (en) * | 2002-12-20 | 2005-03-22 | General Electric Company | Turbine containing system and an injector therefor |
| GB2435508B (en) * | 2006-02-22 | 2011-08-03 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
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| GB2437977A (en) * | 2006-05-12 | 2007-11-14 | Siemens Ag | A swirler for use in a burner of a gas turbine engine |
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| US20080163627A1 (en) * | 2007-01-10 | 2008-07-10 | Ahmed Mostafa Elkady | Fuel-flexible triple-counter-rotating swirler and method of use |
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| US8096132B2 (en) * | 2008-02-20 | 2012-01-17 | Flexenergy Energy Systems, Inc. | Air-cooled swirlerhead |
| EP2107300A1 (en) * | 2008-04-01 | 2009-10-07 | Siemens Aktiengesellschaft | Swirler with gas injectors |
| DE102008019117A1 (en) | 2008-04-16 | 2009-10-22 | Man Turbo Ag | Method for operating a premix burner and a premix burner for carrying out the method |
| EP2230458A1 (en) * | 2009-03-17 | 2010-09-22 | Siemens Aktiengesellschaft | Burner assembly for fluid fuels and method for producing a burner assembly |
| DE102009045950A1 (en) * | 2009-10-23 | 2011-04-28 | Man Diesel & Turbo Se | swirl generator |
-
2009
- 2009-12-15 DE DE102009054669A patent/DE102009054669A1/en not_active Withdrawn
-
2010
- 2010-09-28 EP EP10786994.3A patent/EP2513562B1/en active Active
- 2010-09-28 CA CA2782196A patent/CA2782196C/en active Active
- 2010-09-28 JP JP2012543473A patent/JP2013517440A/en active Pending
- 2010-09-28 US US13/509,329 patent/US20120227407A1/en not_active Abandoned
- 2010-09-28 WO PCT/DE2010/050074 patent/WO2011072665A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| JP2013517440A (en) | 2013-05-16 |
| EP2513562B1 (en) | 2018-07-18 |
| EP2513562A1 (en) | 2012-10-24 |
| CA2782196A1 (en) | 2011-06-23 |
| DE102009054669A1 (en) | 2011-06-16 |
| WO2011072665A1 (en) | 2011-06-23 |
| US20120227407A1 (en) | 2012-09-13 |
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