CN118043593A - Burner part with vortex generator and burner with said burner part - Google Patents
Burner part with vortex generator and burner with said burner part Download PDFInfo
- Publication number
- CN118043593A CN118043593A CN202280057596.1A CN202280057596A CN118043593A CN 118043593 A CN118043593 A CN 118043593A CN 202280057596 A CN202280057596 A CN 202280057596A CN 118043593 A CN118043593 A CN 118043593A
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- China
- Prior art keywords
- burner
- vortex generator
- wall
- main
- main vortex
- 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
- 239000000446 fuel Substances 0.000 claims abstract description 32
- 238000011144 upstream manufacturing Methods 0.000 claims description 11
- 238000000034 method Methods 0.000 claims 1
- 238000002485 combustion reaction Methods 0.000 description 18
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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
- F23R3/28—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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C7/00—Combustion apparatus characterised by arrangements for air supply
- F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
- F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using 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
- F23R3/02—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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
Abstract
The invention relates to a burner element (11) for use in a flow duct (02) of a burner (01) of a gas turbine. The component wall (14) extends from a front edge (12) to a rear edge (13) and from a first wall end (15) to an opposite second wall end (16) in a transverse direction intersecting the flow direction, wherein vortex generators (17, 18) are arranged on the component wall (14) close to the front edge (12), the vortex generators comprising a first main vortex generator (17 a) at a side facing the first wall end (15) and a second main vortex generator (17 b) adjacent to the first main vortex generator (17 a), and an additional vortex generator (18). The fuel nozzles (19) are arranged downstream of the respective main vortex generators (17). In order to improve the mixing, an additional vortex generator (18) is located between the first main vortex generator (17 a) and the first wall end (15), and the height on the component wall (14) is smaller than the height of the first main vortex generator (17 a), and there is no corresponding fuel nozzle.
Description
Technical Field
The present invention relates to a burner element for use in a burner. The task of the burner element is to induce or enhance swirling of the combustion air and fuel.
Background
In order to facilitate combustion with the aim of avoiding pollutants as much as possible, it is important to carry out a homogeneous mixing of the fuel in the combustion air before the combustion of the fuel. To achieve this, various solutions are used in the prior art. In many cases, these solutions are based on creating turbulence between the combustion air and the fuel. Although turbulence can result in flow resistance, it is generally not possible to achieve the desired substantially contaminant-free combustion without turbulence.
In order to mix combustion air with fuel, a turbulence element is typically arranged in the flow path to deflect the flow and cause swirling. In many cases, blade-like structures are used for this purpose.
It is also known to arrange turbulence waves on the surface along the flow path, which cause turbulence of the combustion air. For example, it is known to arrange so-called vortex generators on the walls of the flow channel, which correspondingly protrude into the flow channel.
Regardless of the type of flow pattern and the design of the necessary means for uniformly mixing the combustion air with the fuel, it is important to keep the flow resistance as low as possible while still ensuring adequate mixing. The object of the present invention is therefore to achieve improved mixing with as low a resistance as possible.
Disclosure of Invention
This object is achieved by an embodiment of the burner element according to the teachings of claim 1. A burner with corresponding burner components is defined in claim 12. Advantageous embodiments are the subject matter of the dependent claims.
This type of burner component is intended to be a component of a burner. The type of combustor is initially irrelevant, but the combustor components are advantageously used in the combustor of a gas turbine. It is obvious here that the burner is arranged on the upstream side of the combustion chamber. In this case, the burner has a flow passage in which combustion air flows in a flow direction from an upstream side to a downstream side. The flow direction of the combustion air defines the flow direction. The burner element is deliberately arranged within the flow channel of the burner and thus the flow direction, the upstream side and the downstream side are also applicable thereto. Next, the lateral direction is defined as the direction intersecting the flow direction.
With regard to the arrangement of the burner element in the flow channel, the burner element has a front edge on the upstream side and a downstream edge on the downstream side. The front and rear edges are meant to be located at the respective ends of the burner element. The burner component further includes a component wall extending in a flow direction from the front edge to the rear edge. The component wall also extends in a transverse direction from a first wall end to an opposite second wall end. By arrangement in the flow channel, combustion air flows along the component wall.
In order to enhance the mixing of the fuel in the combustion air, a plurality of vortex generators are arranged on the component wall and protrude into the flow channel. Here, the vortex generators (in the sense of the invention, whether or not there are other vortex generators located elsewhere) are arranged near the front edge and are spaced apart from each other in the transverse direction. Each vortex generator is considered to be close to the front edge if it is arranged at the same lateral position within an edge portion of 20% of the distance from the front edge to the rear edge.
Next, the vortex generators have a group divided into a main vortex generator and an additional vortex generator. Here, the first main vortex generator is arranged as one of the main vortex generators on the side facing the first wall end. A second primary vortex generator is disposed adjacent the first vortex generator.
The combustor component also includes a plurality of fuel nozzles. Here, the fuel nozzles (in the sense of the invention, whether or not there are other nozzles located elsewhere) are each arranged downstream of the respective primary vortex generator. This means that there is always an arrangement of the primary vortex generators adjacent to the front edge and the fuel nozzles downstream of the respective primary vortex generators.
It is also advantageous in practice to arrange the fuel nozzles themselves downstream of the swirl generator, it has been found that a further increase in mixing can be achieved by means of an additional swirl generator without any fuel nozzles. Here, the additional vortex generator is located between the first wall end and the first main vortex generator. If the size of the additional vortex generator is too large, the improvement brought about by the addition of the additional vortex generator translates into disadvantages in terms of mixing of the fuel in the combustion air. Thus, the height of the additional vortex generator on the component wall needs to be smaller than the height of the adjacent first main vortex generator.
The vortex generators may be formed in different shapes, wherein it is advantageous to choose a triangular design with a front curve on the combustion wall at the upstream side and a rear curve intersecting the combustion wall at the downstream side. Thereby, the height of the vortex generator increases from the upstream side to the downstream side.
This advantageously results in the top surface of the vortex generator extending from the front curve to the free end of the rear curve. The height of the vortex generator is thus defined by the distance from the component wall to the free end of the rear curve. According to a triangular design, the vortex generator advantageously comprises two further opposite side surfaces, each extending from the rear curve to one of the two ends of the front curve.
Regarding the location of the vortex generators (main vortex generator and additional vortex generator) close to the front edge, it is further advantageous to arrange them at the same location with respect to the flow direction. Here, it is particularly advantageous if the rear edge of each of the vortex generators is located at the same distance as the front edge (assuming a distance in the range of +/-10%).
Regarding the location of the vortex generators, it is also advantageous to arrange them close to or at the front edge. For a given preferred arrangement of vortex generators of different dimensions and their rear curves at the same location in the flow direction, it is evident that advantageously the largest main vortex generator is arranged with a distance from the front edge to at least one front curve of less than 10% of the distance from the front edge to the corresponding rear curve of the largest main vortex generator.
Depending on the dimensions of the burner element, in particular on the width in the transverse direction from the first wall end to the second wall end, it is advantageous to arrange at least three and at most six main vortex generators, each having a respective fuel nozzle, which is arranged downstream of the respective main vortex generator. In this case, it is particularly advantageous to use four or five main vortex generators. Thus, the third vortex generator is arranged adjacent to the second vortex generator on the side facing the second wall end and the fourth vortex generator is arranged adjacent to the third vortex generator on the side facing the second wall end. The fifth vortex generator, if applicable, is arranged adjacent to the fourth vortex generator on the side facing the end of the second wall.
If a third main vortex generator is used and in particular a fourth main vortex generator is used, it is advantageous to start further increasing in size from the first main vortex generator to the second main vortex generator such that the third main vortex generator is larger than the second main vortex generator and the fourth main vortex generator is larger than the third main vortex generator.
With regard to a further specific position of the additional swirl generator without any fuel nozzles, it is advantageous to arrange it in the middle between the first wall end and the first main swirl generator. If the position is within a tolerance of 15% of the distance from the first wall end to the first primary vortex generator, the position is considered to be given.
It has to be noted that regarding the position of the vortex generator in the transverse direction, the center or back curve of the vortex generator should be considered.
With regard to the arrangement of the additional vortex generators at half the distance from the first wall end to the first main vortex generator, it is further advantageous to arrange the first main vortex generator at half the distance from the first wall end to the second main vortex generator. Here, the preferred position is also considered to be given if the first main vortex generator is arranged midway between the first wall end and the second main vortex generator with a tolerance of 15% of the distance from the first wall end to the second main vortex generator.
As the influence of this arrangement of additional vortex generators decreases at each further main vortex generator, it is preferred to arrange the preferred third main vortex generator at a distance from the second main vortex generator of at least 1.2 times and at most 1.5 times the distance between the second main vortex generator and the first main vortex generator.
With respect to the fuel nozzles, it is advantageous to arrange the fuel nozzles close to the respective primary vortex generators. Thus, the distance between the vortex generator and the corresponding fuel nozzle should be less than half the length of the vortex generator. It is particularly preferred that the distance from the respective main vortex generator to the centre of the fuel nozzle is less than half the distance between the front curve and the rear curve of the respective main vortex generator.
The burner element which is deliberately arranged in the flow channel can be designed with different shapes (apart from the element wall with swirl generator and fuel nozzle). It is advantageous to design the burner element to have the shape of a vane. This enables the flow of combustion air to be guided with low resistance.
The burner element of the invention enables the realization of a burner of the invention with such a burner element as described above.
A preferred embodiment of the burner of the present invention has a central burner axis and an annular flow passage extending from an upstream side to a downstream side. The flow channel is bounded at a radially inner side by the inner flow channel wall and at a radially outer side by the outer flow channel wall. Here, a plurality of burner elements according to the description above are arranged in the flow channel. The first wall end of the burner component is attached to the inner flow channel wall and the second wall end of the burner component is attached to the outer flow channel wall.
Obviously, the burner element may be implemented as a separate part, for example, mounted between the inner channel wall and the outer channel wall. Alternatively, the inner and outer channel walls of the burner may be constructed integrally with the burner part, for example by additive manufacturing. Other production options obviously also make it possible to combine burner elements with inner and outer channel walls.
Drawings
In the following figures, examples of burner components of the invention and their use in burners are shown.
FIG. 1 depicts a portion of an exemplary combustor having combustor components;
FIGS. 2 and 3 illustrate an exemplary embodiment of a burner assembly of the present invention in perspective view;
FIG. 4 depicts the vortex generator and fuel nozzle in detail.
Detailed Description
In fig. 1, a part of a burner 01 is depicted. This embodiment of the burner 01 of the invention comprises a main burner 03 surrounding an annular pilot burner 06. The main burner 03 has an annular flow channel 02, the annular flow channel 02 being defined by an inner channel wall 04 and an outer channel wall 05. A plurality of the burner elements 11 according to the invention are circumferentially distributed in the flow duct 02.
As can be seen in fig. 2 and 3, the burner element 11 has the shape of a vane, wherein the element wall 14 extends from the front edge 12 of the burner element to the rear edge 13 of the burner element. The component wall is also defined by a first side end 15 and by an opposite second side end 16. The direction from the front edge on the upstream side to the rear edge 13 on the downstream side defines the flow direction. A transverse direction intersecting the flow direction is defined from the first side end 15 to the second side end 16.
As shown, a plurality of vortex generators 17, 18 are arranged near the front edge 12. Here, there are four main vortex generators 17a, 17b, 17c and 17d. Their size and height increases from a first primary vortex generator 17a to a second primary vortex generator 17b to a third primary vortex generator 17c on the side facing the first wall end 15. The fourth main vortex generator 17d has a reduced size in contrast to the change from the first main vortex generator 17a to the third main vortex generator 17 c. In this embodiment, the downstream ends of the vortex generators 17, 18 are arranged at the same position in the flow direction. As a result, the upstream end portion of the third main vortex generator 17c, which is the largest main vortex generator, is arranged very close to the front edge 12, whereby the distance from the front edge 12 increases for the first main vortex generator 17a (and also for the fourth main vortex generator 17d having a reduced size).
The main vortex generators 17 are categorized by the arrangement of a respective fuel nozzle 19a to 19d downstream of each main vortex generator 17a to 17 d. It can be seen that the distance from the fuel nozzle 19 to the respective primary vortex generator 17 is much smaller than the size of the vortex generator 17.
The mixing is improved by an additional vortex generator 18 arranged between the first main vortex generator 17a and the first wall end 15. With respect to the main vortex generator 17, no fuel nozzles are arranged at the additional vortex generator 18. Furthermore, the additional vortex generator 18 is reduced in size compared to the first main vortex generator 17 a.
In fig. 4, a detailed view of the primary vortex generator 17 arranged on the component wall 14 is depicted. As can be seen, the main vortex generator 17 has a triangular shape with a front curve 22 as a transition from the top surface 24 of the main vortex generator 17 to the component wall 14 and a rear curve 23 extending across the component wall and thus defining the height of the main vortex generator 17. This creates two opposite side walls 25 extending from the rear curve 23 to one of the two opposite ends of the front curve 22. Downstream of the primary swirl generator 17, a fuel nozzle 19 is arranged.
Claims (13)
1. A burner component (11), the burner component (11) being for use in a burner (01), in particular a burner for a gas turbine, the burner component (11) being intentionally arranged within a flow channel (02) having a flow direction, the burner component (11) having a front edge (12) on an upstream side and a rear edge (13) on a downstream side, the burner component (11) having a component wall (14), the component wall (14) extending from the front edge (12) to the rear edge (13) and from a first wall end (15) to an opposite second wall end (16) in a transverse direction intersecting the flow direction; the burner element (11) comprises:
-vortex generators (17, 18) arranged on the component wall (14) close to the front edge (12), spaced apart from each other in the transverse direction, protruding into the flow channel (02), the vortex generators (17, 18) comprising a first main vortex generator (17 a) at a side facing the first wall end (15) and a second main vortex generator (17 b) adjacent to the first main vortex generator (17 a), and an additional vortex generator (18); and
-Fuel nozzles (19), said fuel nozzles (19) being each arranged downstream of a respective primary vortex generator (17),
It is characterized in that the method comprises the steps of,
The additional vortex generator (18) is located between the first main vortex generator (17 a) and the first wall end (15), and has a height on the component wall (14) that is smaller than the height of the first main vortex generator (17 a) and no corresponding fuel nozzle.
2. Burner element (11) according to claim 1, wherein the vortex generators (17, 18) have a triangular design with a front curve (22) on the element wall (14) at the upstream side and a rear curve (23) intersecting the element wall (14) at the downstream side.
3. Burner part (11) according to claim 2, wherein the vortex generators (17, 18) have a top surface (24) extending from the front curve (22) to a free end of the rear curve (23) and two side surfaces (25) each extending from one end of the front curve (22) to the rear curve (23).
4. A burner part (11) according to one of claims 1 to 3, wherein the vortex generators (17, 18) are arranged in the same position with respect to the flow direction.
5. Burner element (11) according to claim 4, wherein the vortex generators (17, 18) are arranged close to the front edge (12).
6. Burner element (11) according to one of claims 1 to 5, comprising at least three and at most six, in particular four or five main vortex generators (17), each of the main vortex generators (17) having a respective fuel nozzle (19) arranged downstream.
7. The burner component (11) of claim 6 wherein the second primary vortex generator (17 b) is larger in size than the first vortex generator (17 a) and a third primary vortex generator (17 c) adjacent the second vortex generator (17 b) is larger in size than the second vortex generator (17 b).
8. Burner part (11) according to one of claims 1 to 7, wherein the additional vortex generator (18) is arranged midway between the first wall end (15) and the first main vortex generator (17 a) with a tolerance of 15%, and wherein the first main vortex generator (17 a) is arranged midway between the first wall end (15) and the second main vortex generator (17 b) with a tolerance of 15%.
9. Burner part (11) according to claim 8, wherein the distance between the third main vortex generator (17 c) and the second main vortex generator (17 b) is at least 1.2 times and at most 1.5 times the distance between the second main vortex generator (17 b) and the first main vortex generator (17 a).
10. Burner part (11) according to one of claims 1 to 8, wherein the distance from the rear curve (23) to the respective fuel nozzle (19) is less than half the length of the respective main vortex generator (17) in the flow direction, in particular less than half the respective distance from the front curve (22) to the rear curve (23).
11. Burner element (11) according to one of claims 1 to 8, said burner element (11) having a blade shape.
12. Burner (01) with at least one burner element (11) according to one of the preceding claims.
13. Burner (01) according to claim 12, the burner (01) having a central burner axis and having an annular flow channel (02) and comprising an inner flow channel wall (04) and an outer flow channel wall (05), wherein a plurality of burner elements (11) according to one of the preceding claims are arranged in the flow channel (02), wherein the first wall end (15) is attached to the inner flow channel wall (04) and the second wall end (16) is attached to the outer flow channel wall (05).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| IN202141038875 | 2021-08-27 | ||
| IN202141038875 | 2021-08-27 | ||
| PCT/EP2022/063370 WO2023025423A1 (en) | 2021-08-27 | 2022-05-18 | Burner component having vortex generators and burner with such burner component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN118043593A true CN118043593A (en) | 2024-05-14 |
Family
ID=82020264
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202280057596.1A Pending CN118043593A (en) | 2021-08-27 | 2022-05-18 | Burner part with vortex generator and burner with said burner part |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP4341614A1 (en) |
| CN (1) | CN118043593A (en) |
| WO (1) | WO2023025423A1 (en) |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH688868A5 (en) * | 1993-04-08 | 1998-04-30 | Asea Brown Boveri | Through-flow channel with eddy generator |
| US5647215A (en) * | 1995-11-07 | 1997-07-15 | Westinghouse Electric Corporation | Gas turbine combustor with turbulence enhanced mixing fuel injectors |
| EP1239219A4 (en) * | 1999-12-15 | 2003-03-12 | Osaka Gas Co Ltd | Fluid distributor, burner device, gas turbine engine, and cogeneration system |
| RU2548521C2 (en) * | 2009-05-05 | 2015-04-20 | Сименс Акциенгезелльшафт | Swirler, combustion chamber and gas turbine with improved mixing |
| US20110023494A1 (en) * | 2009-07-28 | 2011-02-03 | General Electric Company | Gas turbine burner |
| EP2644997A1 (en) * | 2012-03-26 | 2013-10-02 | Alstom Technology Ltd | Mixing arrangement for mixing fuel with a stream of oxygen containing gas |
| US20140123653A1 (en) * | 2012-11-08 | 2014-05-08 | General Electric Company | Enhancement for fuel injector |
| IT201700061780A1 (en) * | 2017-06-06 | 2018-12-06 | Ansaldo Energia Spa | BURNER GROUP FOR A GAS TURBINE WITH TURBULENCE GENERATORS |
-
2022
- 2022-05-18 WO PCT/EP2022/063370 patent/WO2023025423A1/en active Application Filing
- 2022-05-18 EP EP22729575.5A patent/EP4341614A1/en active Pending
- 2022-05-18 CN CN202280057596.1A patent/CN118043593A/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| WO2023025423A1 (en) | 2023-03-02 |
| EP4341614A1 (en) | 2024-03-27 |
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