CN117916526A - Burner and method for its manufacture - Google Patents
Burner and method for its manufacture Download PDFInfo
- Publication number
- CN117916526A CN117916526A CN202280060337.4A CN202280060337A CN117916526A CN 117916526 A CN117916526 A CN 117916526A CN 202280060337 A CN202280060337 A CN 202280060337A CN 117916526 A CN117916526 A CN 117916526A
- Authority
- CN
- China
- Prior art keywords
- swirl
- fuel
- channels
- central axis
- channel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 title claims description 11
- 238000000034 method Methods 0.000 title claims description 8
- 239000000446 fuel Substances 0.000 claims abstract description 61
- 238000002485 combustion reaction Methods 0.000 claims abstract description 31
- 239000000203 mixture Substances 0.000 claims abstract description 31
- 230000007704 transition Effects 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 6
- 238000002844 melting Methods 0.000 claims description 5
- 230000008018 melting Effects 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 4
- 238000005457 optimization Methods 0.000 claims description 2
- 239000000843 powder Substances 0.000 claims description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 5
- 239000001257 hydrogen Substances 0.000 description 4
- 229910052739 hydrogen Inorganic materials 0.000 description 4
- 239000000654 additive Substances 0.000 description 3
- 230000000996 additive effect Effects 0.000 description 3
- 239000003344 environmental pollutant Substances 0.000 description 3
- 239000007789 gas Substances 0.000 description 3
- 231100000719 pollutant Toxicity 0.000 description 3
- 239000007788 liquid Substances 0.000 description 2
- 238000004804 winding Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000018109 developmental process Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000000155 melt Substances 0.000 description 1
- 238000005496 tempering Methods 0.000 description 1
Classifications
-
- 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
-
- 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
Abstract
The invention relates to a burner having a combustion space (1), a plurality of swirl channels (2), wherein the swirl channels (2) comprise at least one fuel nozzle (3) for introducing fuel (G) into the respective swirl channel (2), and wherein the swirl channels (2) each extend from an inflow side (21) to an outflow side (22) leading to the combustion space (1), on which inflow side fuel (G) can be introduced into the swirl channels (2) from the respective fuel nozzle (3), and wherein the swirl channels (2) each can be flown by a fuel-air mixture composed of fuel (G) and air (L) flowing into the swirl channels (2) along a flow path (23) extending from the inflow side (21) to the outflow side (22), wherein the burner has a central axis (X) extending through the combustion space (1) and the swirl channels (2) emanating from the outflow side (22) are at least partially helically wound around the central axis (X) such that the fuel-air mixture flows from the inflow side (21) along the flow path (23) into the swirl channels (1) and is subjected to a swirl condition in each case of the swirl channels (1).
Description
Technical Field
The present invention relates to a combustor for a turbine and a method for manufacturing such a combustor, the combustor having a plurality of curved swirl passages through which a fuel-air mixture flowing through the swirl passages is swirled.
Background
A combustor (e.g., a combustor for a gas turbine) utilizes gas as fuel such that a gas-air mixture or, in general, a fuel-air mixture is mostly combusted in the combustor.
In principle, it is also possible to use liquid fuels in the burner.
Low pollutant burners typically mix air and fuel prior to combustion in order to avoid temperature spikes and thus pollutant emissions.
For this purpose, burners designed as swirl-flow burners are generally used in the prior art, which use radial or axial swirl cascades in order to impart swirl to the fuel-air mixture.
In the case of highly reactive fuels (e.g., hydrogen), low pollutant combustion is difficult because the fuel-air mixture burns as fast as flame flashback (flash back). For this reason, such fuels or such mixtures are often combusted without premixing.
Sometimes, a burner, also called a jet burner, is used to burn highly reactive fuels. For such jet burners, a swirl cascade is omitted or the mixture is generally subjected to swirl and the flame is stabilized on the free jet.
This has advantages in flashback strength, but at the expense of flame stability and emissions. Here, the air flows through individual tubes which are arranged completely straight and parallel to one another and in which it is mixed with the fuel. At the outlet of the burner, the fuel is combusted in a number of small jets. The jet burner has a greater flashback strength because the entire air or mixture is conducted axially.
In addition, residence time is shorter and NOx emissions at very high temperatures are lower compared to swirl-flow burners.
In contrast, swirl-flowing burners provide substantially better stability and better part-load emissions. The mixing section of a burner with swirl flow is typically long, which achieves good mixing of air and fuel.
Disclosure of Invention
The present invention is therefore based on the object of overcoming the abovementioned disadvantages and providing a burner which achieves both a higher tempering strength and a good mixing of air and fuel and at the same time has a stable combustion behavior, so that in particular hydrogen or hydrogen can also be burned as a low-emission fuel.
This object is solved by a combination of features according to patent claim 1.
According to the invention, a burner is therefore proposed, which has a combustion space, a plurality of swirl channels, wherein the swirl channels comprise at least one fuel nozzle for introducing fuel into the respective swirl channel. In this case, a plurality of swirl passages form, in particular, a swirl generator. The swirl channels each extend from an inflow side, on which fuel can be introduced into the respective swirl channel from the respective fuel nozzle, to an outflow side which leads to the combustion space. The combustion space, which may also be referred to as a combustion zone, may be enclosed or delimited by a combustion chamber. Furthermore, the combustion space essentially only determines the volume in which the combustion of the fuel-air mixture or the gas-air mixture takes place. The swirl channels are each capable of being flown by fuel and a fuel-air mixture of air flowing into the swirl channels along a flow path extending from a respective inflow side to a respective outflow side.
In such a combustor, the swirl passage, passages, or all of the swirl passages may include one or more fuel nozzles.
The fuel is a liquid fuel or a gas. The fuel gas is preferably hydrogen or hydrogen gas.
Furthermore, the burner comprises a central axis extending through the combustion space. According to the invention, it is essential that the swirl channel emanating from the outflow side is at least partially helically wound around the central axis. Alternatively, at least part of the spiral formation of the vortex channel may be described such that the vortex channel and/or the flow path defined by the vortex channel are each at least partly helically formed or at least partly formed as a spiral. Thus, the swirl channel may also be referred to as a curved swirl channel. From the inflow side, the flow channels or the flow paths defined by these flow channels lead into the combustion space on the outflow side with a twist or obliquely with respect to the central axis. This results in the fuel-air mixture flowing from the inflow side to the outflow side along the flow path being subjected in each case to a swirl caused by the helically wound portion of the swirl channel and flowing into the combustion space in a swirling manner. Thus, the swirling fuel-air mixture preferably flows through each individual swirl passage.
In the process, a plurality of individual or free jets are produced by the swirl channel on the outflow side or in the combustion space, but said jets are already subjected to swirl by swirling or winding around the central axis.
Thus, by their spiral winding around the central axis, the swirl chambers already have a curvature which imparts a rotational component to the air or fuel-air mixture as it flows through the flow channel.
At the outlet of the burner, or when the fuel-air mixture flows out of the swirl channel into the combustion space, the combustion mode of the burner resembling swirl flow, in which the swirl formed by the free jet bursts, is opened and the flame in the combustion space is stabilized in the shear layer of the swirl.
Since the burner comprises a plurality of swirl channels, which in their entirety may also be referred to as swirl generators, the fuel-air mixture is not fed to the combustion space by means of separate feed lines but by means of a plurality of swirl channels formed, for example, as tubes, so that the burner according to the invention has a good flashback strength or a similar good flashback resistance similar to the jet burners known from the prior art, wherein by means of swirl application low emission combustion continues to take place.
Since on the inflow side fuel and preferably also air is introduced into the swirl channel, the fuel and the air are mixed along the flow path through the swirl channel to form the desired fuel-air mixture.
By providing a plurality of vortex channels forming a vortex generator, which are each at least partially helically formed, the vortex generator is formed as a plurality of spirals having a number of turns corresponding to the number of vortex channels. The deflector or the swirl duct may additionally be arranged in layers or planes which overlap one another, so that, for example, the inner plane of the swirl duct can be surrounded by the outer plane of the swirl duct. Here, the vortex passage may be of a left-handed type or a right-handed type.
In an advantageous embodiment, it is provided that in the portion of the swirl duct extending helically around the central axis, the flow path and/or the central line of the swirl duct each have a deflection angle of more than 0 ° and less than 90 °, in particular more than 60 ° and less than 90 °, in particular even 60 °.
The turning angle of the swirl channel or the turning angle of the flow path and/or the centre line of the swirl channel is defined in accordance with the turning angle of the spiral.
Furthermore, all flow paths and/or centerlines preferably have the same turning angle.
If the vortex channel is fabricated by an additive manufacturing method such as Selective Laser Melting (SLM), the maximum or minimum pitch or turning angle may be constrained by the technical limitations of the manufacturing method. For example, it is not possible to produce swirl channels with a divert angle of less than 40 ° by SLM methods, at least when applied, or only with a great outlay.
Furthermore, an advantageous variant of the burner provides that the swirl channels each comprise a portion on the outflow side which is helically wound around the central axis and on the inflow side comprises a portion which runs parallel to the central axis. Here, the swirl channels each have a transition between the helically wound or curved portion and the portion extending parallel to the central axis (i.e. the straight portion), which transition is smooth, so that the fuel-air mixture flowing through the swirl channels from the straight or parallel portion to the central axis to the helically wound or curved portion is deflected continuously or steadily, rather than abruptly, along the transition or in the region of the transition.
Furthermore, it is preferably provided that the swirl channels each comprise a circular cross section and are formed as swirl tubes.
A variant is also advantageous in which the fuel nozzles each extend into a respective swirl channel on the inflow side.
In this case, it is further advantageous in one embodiment if the swirl chambers each comprise, on the inflow side, an inflow portion, in particular funnel-shaped, into which the respective fuel nozzle extends, wherein between the outer surface of the respective fuel nozzle and the inner surface of the respective swirl channel, an air passage, preferably annular in cross section, is defined in the inflow portion thereof, through which air can flow into the respective swirl channel.
Furthermore, fluid guiding elements, in particular designed as wings, can be provided in the swirl channels and/or on the fuel nozzle for flow optimization.
The fluid elements are designed to influence the flow of fluid through them in a predetermined manner. For example, the fluid element may be provided with an airfoil profile on the fuel nozzle in the region of the air passage, which directs the air flowing through the air passage in a predetermined manner into the fuel injected or introduced by the fuel nozzle in order to thereby improve the mixing of the air with the fuel.
Preferably, the swirl channels each extend in a predetermined plane or in the inner and outer side surfaces of the hollow cylinder. Thus, it may be provided that the swirl channel or its centre line/flow path is arranged on at least one annular path coaxial with the centre axis. Thus, it is also possible to provide a plurality of routes, each of which is annular and coaxial with the central axis, wherein a plurality of flow paths extend over each of the routes.
In order to be able to provide as many swirl channels as possible, the swirl channels of the plurality of swirl channels rest against one another. Thus, the swirl channels immediately adjacent to one another rest against one another, for example with the outer surfaces of their walls.
In particular when the swirl channels or the swirl generators formed by the swirl channels are manufactured by an additive manufacturing method, it may further be provided that the swirl channels are not only abutted against one another but also partially formed integrally with one another. The swirl channels each have walls that delimit the respective swirl channel in the radial direction. In this case, it is then provided that the walls of the swirl ducts which lie against one another or adjacent to one another are formed integrally and/or in one piece.
In order to improve the mixing of fuel and air, it may be further provided that the fuel nozzles are designed to introduce fuel substantially transversely into the respective swirl channels on the inflow side.
As already mentioned, it is preferably provided that the vortex channel is manufactured from metal by Selective Laser Melting (SLM).
Another aspect of the invention relates to a method for manufacturing a burner according to the invention. Here, the swirl channels are produced by Selective Laser Melting (SLM), i.e. by additive manufacturing, of metal powder which melts in layers in order to form the swirl channels or a swirl generator formed by the swirl channels. Here, the swirl channels are manufactured separately and serve to provide a swirl generator arranged around the central axis. Alternatively, the swirl channels can also be produced integrally and/or in one piece in groups, and groups of swirl channels coupled to one another are arranged about the central axis for providing a swirl generator. Alternatively to the manufacture of individual vortex channels and alternatively to the manufacture of groups of joined vortex channels, the entire vortex generator (i.e. all vortex channels) may be manufactured in one piece and/or joined and arranged around the central axis.
The features disclosed above may be combined as desired, as long as this is technically possible and these features are not contradictory.
Drawings
Further advantageous further developments of the invention are indicated in the dependent claims or are presented in more detail with the description of the preferred embodiments by means of the figures. Wherein:
Fig. 1 shows a variant of a burner;
Fig. 2 shows a section of a variant of the burner.
These figures are exemplary schematic. Like reference numerals in the figures refer to like functional and/or structural features.
Detailed Description
In fig. 1, a burner is shown, which comprises a swirl generator comprising a plurality of swirl channels 2, which are embodied here as swirl tubes, which are arranged about a central longitudinal axis X and into which, at their inflow side 21, fuel nozzles 3 each extend, through which fuel G can be injected into the swirl channels 2. Here, the swirl channels 2 each comprise, on the inflow side, a funnel-shaped inflow portion 27 in which an air passage 28 is formed between the inner wall or inner surface of the respective swirl channel 2 and the outer wall or outer surface of the respective fuel nozzle 3, through which air L can flow into the respective swirl channel 2 substantially parallel to the fuel G. The fuel G and the air L are mixed in the swirl channels 2 and flow as a fuel-air mixture along the respective flow paths 23 from the inflow side 21 to the outflow side 23 of the respective swirl channels 2.
There, the fuel-air mixture initially flows through a portion 24 (straight portion 24) which initially runs parallel to the central axis of the respective swirl channel 2 and merges by means of a stable, smooth transition 25 into a portion 26 which is helically wound around the central axis X, which may also be referred to as a curved portion 26.
In the process, the fuel-air mixture is given a swirl or rotation while flowing through the curved portion 26, so that each fuel-air mixture flow flowing out from the swirl passage 2 into the outflow-side combustion space 1 is subjected to a swirl. Here, the fuel-air mixture flow through the individual swirl channels 2 forms only a partial flow of the entire fuel-air mixture flow through the swirl channels 2.
In the combustion space 1, the fuel-air mixture flowing in together with the entire fuel-air mixture flow is combusted, wherein the entire flow is swirled by subjecting the individual partial flows to a swirl, resulting in low-emission combustion, wherein a high flashback resistance is simultaneously achieved by a plurality of swirl channels 2 extending along the central axis X, so that during combustion the flame is not essentially flashback from the combustion space 1 back into the swirl channels 2.
In fig. 2, an enlarged section of a portion 24 of a burner, which may be a burner according to fig. 1, is shown extending parallel to the central axis. At least a part of the swirl duct 2 is furthermore shown in a half-section, so that this section extends through a wall 29 of a part of the swirl duct 2, whereby in particular the fuel nozzle 3 is visible in the region of the inflow portion 27 formed as a funnel.
As described previously, in the region of the inflow portion 27, air passages 26 each extending annularly around the fuel nozzle 3 through which air L flows into the corresponding swirl passage 2 are formed between the outer surface of the fuel nozzle 27 and the inner surface of the swirl passage 2. There, at least one fluid guiding element 4, each formed in the manner of an airfoil, is provided on the fuel nozzle 3, which extends into the annular air passage 26 and guides the inflowing air L in a flow-optimizing manner into the associated swirl channel 2.
List of reference numerals
1. Fuel space
2. Vortex channel
3. Fuel nozzle
21. Inflow side
22. Outflow side
23. Flow path
24 Straight portions/portions extending parallel to the central axis
25 Transition portion
26 Curved portion/spiral wound portion
27. Inflow part
28. Air passage
29. Wall with a wall body
X central axis
G fuel
L air
Claims (13)
1. A burner having a combustion space (1), a plurality of swirl channels (2), wherein the swirl channels (2) comprise at least one fuel nozzle (3) for introducing fuel (G) into the respective swirl channel (2),
Wherein the swirl channels (2) each extend from an inflow side (21) on which fuel (G) can be introduced into the swirl channels (2) from a respective fuel nozzle (3) to an outflow side (22) which leads to the combustion space (1),
And the swirl channels (2) can each be flown through by a fuel-air mixture of the fuel (G) and air (L) flowing into the swirl channels (2) along a flow path (23) extending from the inflow side (21) to the outflow side (22),
Wherein the burner has a central axis (X) extending through the combustion space (1) and the swirl channel (2) emanating from the outflow side (22) is at least partially helically wound around the central axis (X) such that the fuel-air mixture flowing from the inflow side (21) to the outflow side (23) along the flow path (23) is in each case subjected to a swirl caused by the swirl channel (2) and flows into the combustion space (1) in a swirling manner.
2. The burner according to claim 1,
Wherein in the portion (26) of the swirl channel extending helically around the central axis (X), the flow path (23) and/or the central line of the swirl channel (2) each comprise a turning angle α of more than 0 ° and less than 90 °, in particular more than 60 ° and less than 90 °, further in particular exactly 60 °.
3. The burner according to claim 1 or 2,
Wherein the swirl channels (2) each comprise on the outflow side a portion (26) which is helically wound around the central axis and on the inflow side a portion (24) which extends parallel to the central axis,
Wherein the respective transition (25) between the helically wound portion (26) and the portion (24) extending parallel to the central axis is smooth.
4. A burner according to any one of the preceding claims,
Wherein the swirl channels (2) each have a circular cross section and are formed as swirl tubes.
5. A burner according to any one of the preceding claims,
Wherein each of the fuel nozzles (3) extends into a respective swirl channel (2) on the inflow side.
6. A burner according to any one of the preceding claims,
Wherein the swirl channels (2) each comprise, on the inflow side, an inflow portion (27), in particular funnel-shaped, into which the respective fuel nozzle (3) extends,
Wherein between the outer surface of the respective fuel nozzle (3) and the inner surface of the respective swirl channel (2) an air passage (28) is defined in the inflow portion (27) thereof, which air passage is able to flow into the respective swirl channel (2), in cross section, in particular extending annularly around the fuel nozzle (2).
7. A burner according to any one of the preceding claims,
Wherein a fluid guiding element (4) is arranged in the swirl channel (2) and/or on the fuel nozzle (3) for flow optimization.
8. A burner according to any one of the preceding claims,
Wherein the swirl channel (2) is arranged on at least one annular path coaxial with the central axis (X).
9. A burner according to any one of the preceding claims,
Wherein the vortex channels (2) of the plurality of vortex channels (2) abut against each other.
10. The burner according to the preceding claim,
Wherein the swirl channels (2) each comprise a wall (29) delimiting the respective swirl channel (1) in the radial direction and the walls (29) of the swirl channels (2) against each other are formed integrally and/or in one piece.
11. A burner according to any one of the preceding claims,
Wherein the fuel nozzle (3) is designed to inject the fuel (G) substantially transversely into the respective swirl channel (2) on the inflow side.
12. A burner according to any one of the preceding claims,
Wherein the swirl channel (2) is produced from metal by selective laser melting.
13. A method for manufacturing a burner according to the preceding claim,
Wherein the swirl channel (2) is produced from a metal powder by selective laser melting,
And the swirl channels (2) are manufactured separately and arranged around the central axis (X),
Or the swirl channels (2) are produced integrally and/or in one piece in groups, and the groups of swirl channels (2) that are connected to one another are arranged around the central axis (X),
Or all the swirl channels (2) are produced integrally and/or in one piece in a joined manner and are arranged around the central axis (X).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102021123513.8 | 2021-09-10 | ||
| DE102021123513.8A DE102021123513A1 (en) | 2021-09-10 | 2021-09-10 | Burner and method for its manufacture |
| PCT/EP2022/073684 WO2023036622A1 (en) | 2021-09-10 | 2022-08-25 | Burner and method for its production |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117916526A true CN117916526A (en) | 2024-04-19 |
Family
ID=83283081
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202280060337.4A Pending CN117916526A (en) | 2021-09-10 | 2022-08-25 | Burner and method for its manufacture |
Country Status (3)
| Country | Link |
|---|---|
| CN (1) | CN117916526A (en) |
| DE (1) | DE102021123513A1 (en) |
| WO (1) | WO2023036622A1 (en) |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4222232A (en) * | 1978-01-19 | 1980-09-16 | United Technologies Corporation | Method and apparatus for reducing nitrous oxide emissions from combustors |
| US5596873A (en) * | 1994-09-14 | 1997-01-28 | General Electric Company | Gas turbine combustor with a plurality of circumferentially spaced pre-mixers |
| EP2233836B1 (en) | 2009-03-23 | 2015-07-29 | Siemens Aktiengesellschaft | Swirler, method for reducing flashback in a burner with at least one swirler and burner |
| JP2011058775A (en) * | 2009-09-14 | 2011-03-24 | Hitachi Ltd | Gas turbine combustor |
| US9217373B2 (en) | 2013-02-27 | 2015-12-22 | General Electric Company | Fuel nozzle for reducing modal coupling of combustion dynamics |
| WO2014191495A1 (en) | 2013-05-31 | 2014-12-04 | Siemens Aktiengesellschaft | Annular combustion chamber for a gas turbine, with tangential injection for late lean injection |
| US9631816B2 (en) * | 2014-11-26 | 2017-04-25 | General Electric Company | Bundled tube fuel nozzle |
| US11015809B2 (en) * | 2014-12-30 | 2021-05-25 | General Electric Company | Pilot nozzle in gas turbine combustor |
| US11371706B2 (en) * | 2017-12-18 | 2022-06-28 | General Electric Company | Premixed pilot nozzle for gas turbine combustor |
-
2021
- 2021-09-10 DE DE102021123513.8A patent/DE102021123513A1/en active Pending
-
2022
- 2022-08-25 WO PCT/EP2022/073684 patent/WO2023036622A1/en active Application Filing
- 2022-08-25 CN CN202280060337.4A patent/CN117916526A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| DE102021123513A1 (en) | 2023-03-16 |
| WO2023036622A1 (en) | 2023-03-16 |
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