CA2555481A1 - Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber - Google Patents
Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber Download PDFInfo
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- CA2555481A1 CA2555481A1 CA002555481A CA2555481A CA2555481A1 CA 2555481 A1 CA2555481 A1 CA 2555481A1 CA 002555481 A CA002555481 A CA 002555481A CA 2555481 A CA2555481 A CA 2555481A CA 2555481 A1 CA2555481 A1 CA 2555481A1
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- Prior art keywords
- flow
- inside wall
- swirl
- premix burner
- cone shell
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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
- F23R3/28—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
- F23D—BURNERS
- F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
- F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
-
- 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
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
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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)
- Portable Nailing Machines And Staplers (AREA)
- Feeding And Controlling Fuel (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
The invention relates to a premixing burner arrangement for operating a burner chamber with a gaseous and/or liquid fuel. Said premix burner comprises a swirl generator (2) for a combustion air influx for forming a swirl and means (5) for jetting in fuel into the swirl. The swirl generator (2) comprises at least two partial conical shells (1) that complement each other to give a flow-type body and that together include a conical swirl chamber having a cone angle .gamma. and air inlet slots (4) that are tangential relative to the longitudinal extension of the cone. The invention is characterized in that at least in the flow-distal end zone of the swirl generator (2) a shaped element (7) enclosing the partial conical shells (1) and having an inner wall (6) facing the partial conical shells (1) is provided and in that the partial conical shells (1) run flush into the inner wall (6) thereby keeping the shape of the structure.
Description
Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber Technical field The invention relates to a premix burner for operating a combustion chamber with a gaseous and/or liquid fuel, having a swirl generator for inducing a swirl flow in an incoming combustion air flow and means for injecting fuel into the swirl flow, the swirl generator having at least two cone shell. segments which fit together to form a flow body and together enclose a conically formed swirl space with a cone angle y and air inlet slits directed tangentially to the length of the cone.
Prior art Premix burners of the aforementioned generic type are known from many prior publications, such as for example from EP 0 210 462 A1 and EP 0 321 809 B1, to mention just two. Premix burners of this type are based on the general operating principle of generating within a generally conically formed swirl generator, which provides at least two cone shell segments fitted together in such a way that they appropriately overlap one another, a swirl flow which comprises a mixture of fuel and air and is ignited within a combustion chamber downstream of the premix burner in the direction of flow, thereby forming a premix flame which is spatially as stable as possible. In this case, the spatial position oz the premix tlame is determined by the aerodynamic behavior of the swirl flow, the swirl coefficient of which increases with increasing propagation along the burner axis, consequently becomes unstable and ultimately, as the result of a discontinuous cross-sectional transition between the burner and the combustion chamber, breaks down into an annular swirl flow with the formation of a backf7nw zone, in the forward region of which, in the direction of flow, the premix flame forms.
Of special importance is the aerodynamic stability of the backflow zone forming, which however depends in a highly sensitive way on the design, shape and size of the swirl generator. For example, if the forwardmost front in the direction of flow of the backflow zone forming is not spatially stabilized successfully, thermoacoustic vibrations or pulsations occur to an increased extent within the combustion system, significantly impairing the overall combustion and the release of heat.
In consideration of this fact, the premix burner systems previously known and in use are restricted to overall sizes in which the maximum burner diameter at the burner outlet is only 180 mm. Premix burners of this type additionally have a relatively pointed, i.e.
small, cone angle, of less than or equal to 18°, so that the length of the burner tends to be great in relation to the diameter of the burner facing downstream, but is still well able to be handled for assembly and maintenance purposes.
However, whenever combustion chambers of large dimensions are to be fired, so far use has been made of so-called multiple burner arrangements, which provide for use of the above premix burners. Multiple burner arrangements of this type are disclosed for example by DE 42 23 828 Al or DE 44 12 315 A1. To operate multiple burner arrangements of this type, which are suitable for example for firing a silo combustion chamber, a sophisticated arrangement of the large number of premix burners respectively serving as main burners or pilot burners is required to achieve the end effect of allowing the combustion chamber to continue to be operated with lowest possible emission values in the entire load range.
However, there is the desire to reduce the complexity and with it also the number of the individual premix burners that are required for firing combustion chambers of large dimensions, without losses of quality in the combustion process having to be accepted at the same time. In addition, for reasons concerning the increasingly stringent environmental standards with regard to the reduction of emission values, the aim is to replace the previously operated single diffusion burners that are primarily used for firing silo combustion chambers of large dimensions by more modern, environmentally more acceptable burner systems. In particular with regard to the avoidance of high conversion and first-time acquisition costs, it is desirable to provide premix burners of the largest possible dimensions, in order for example to be able to continue to maintain the operation of such silo combustion chambers of large dimensions with only a single premix burner.
Theoretical studies and trials have shown that simply scaling for example a double cone burner known from EP
0 321 809 B1 does not achieve the objective, especially since, as already mentioned above, the length of the burner would increase disproportionately. Added to this is the fact that the width of the air inlet slits which extend tangentially in the burner axis and through which incoming combustion air flows into the swirl generator to generate the desired swirl flow would likewise increase proportionately, so that good mixing of the fuel and incoming combustion air with adequate quality can no longer be ensured.
A further very important and at the same time critical aspect of a desired increase in size or increase in output of the previously known premix burner systems concerns the downstream termination of the cone shell segments enclosing the swirl space of the swirl generator, which in the example of the double cone burner described in EP 0 321 809 B1 end in axially directed blocking-off elements. These blocking-off elements contribute to the formation of undesired separation vortices which, as coherent vortex structures, lead to combustion instabilities and, associated therewith, to thermoacoustic vibrations or pulsations.
There are also known, premix burner arrangements (for example US 5,588,826) which, as a difference from the premix burner described above, have a transitional geometry interposed between the swirl generator and the combustion chamber, for example in the form of a hollow-cylindrically formed mixing tube. However, transitional geometries of this type are extremely sensitive aerodynamically, since flow separations in this zone can lead to flashback or spontaneous ignition. Similarly, because of their complex production, transitional geometries of this type contribute decisively to the production costs.
Summary of the invention The invention is based on the object of developing a premix burner according to the features of the precharacterizing clause of claim 1 in such a way that, in spite of the increase in size of the burner dimensions, the optimized burner properties in the case of previously known premix burners are to be retained virtually unchanged. So the aim is to increase the size of the burner of previously known premix burner systems in order to reduce the number of burners in multiple burner arrangements, as described at the beginning, and also to reduce the associated system costs. Similarly, it is intended to be possible with the larger premix burner systems to replace previously known single diffusion burners, as are used for example for the firing of silo combustion chambers, by a single premix burner.
The solution achieving the object on which the invention is based is specified in claim 1. Features which advantageously develop the idea of the invention are the subject of the subclaims and are disclosed in the description, in particular with reference to the exemplary embodiments.
According to the invention, a premix burner according to the precharacterizing clause of claim 1 is developed in such a way that, at least at the downstream end region of the swirl generator, a shaped element enclosing the cone shell segments with an inside wall facing the cone shell segments is provided, and that the cone shell segments end in the inside wall in a flush manner while maintaining their shape.
A large number of theoretical studies and experimentally conducted trials to increase the size of the previously known form of premix burners, which usually have a maximum burner diameter on the burner outlet side of 180 mm, led to the realization that the downstream end structure of the cone shell segments has a significant influence on the stability of the premix burner flame forming, in particular in the endeavor to form the premix burner with as large a volume as possible.
So it is found that in most cases of the premix burners that are in use the end regions of the cone shell segments go over in the direction of flow into a hollow-cylindrical flow channel, which is adjoined either directly by the combustion chamber or by an additional mixing zone in the form of a mixing tube.
To avoid the separation vortices following on directly from the cone shell segments in the direction of flow, it has been realized according to the invention that, immediately after leaving the swirl generator, the swirl flow is able to spread out largely without making the swirl flow unstable if, while maintaining their shape, the individual cone shell segments keep in close contact with the inside wall of the flow channel adjoining the swirl generator. The concept of "maintaining their shape" means for the purposes of the invention that the shape of the cone shell segments formed in the manner of segments of a cone remains unchanged in the region where they come into contact with the inside wall of the shaped element enclosing the cone shell segments, as though the cone shell segments would penetrate unhindered through the shaped element in a radially outward direction.
The inside wall of the shaped element also serves for forming a flow channel adjoining the cone shell segments downstream. Depending on the shape and size of the shaped element, it also serves as a mixing tube or as a joining element, in the sense of a flanged piece, by means of which the swirl generator can be connected to a combustion chamber following on in the direction of flow, such as for example a silo combustion chamber, or some other channel structure.
To be able to make the premix burner as compact as possible, i.e. with a burner length that is as small as possible, cone angles of at least 11°, but preferably in the range of 20° and greater, are used, at which angles the cone shell segments surround the swirl space in a conically widening manner. For example, burners with a burner diameter in the outlet region of greater than 500 mm which have a burner length of well below one meter can be made possible . To ensure good mixing _ 7 _ of the mixture of fuel and air within the swirl generator, it is also advantageous to increase the number of cone shell segments and, associated with it, the number of air inlet slits, in order in this way to achieve the smallest possible slit width per air inlet slit.
Brief description of the drawings Without restricting the general idea of the invention, the invention is described below by way of example on the basis of exemplary embodiments with reference to the drawings, in which:
Figures 1 + 2 show a perspective representation of a premix burner with a cylindrically formed shaped element, Figures 3 + 4 show a perspective representation of a premix burner with a frustoconically formed shaped element, Figure 5 shows a sectional representation through a premix burner with a frustoconically formed shaped element, and Figures 6 + 7 show a perspective representation of a premix burner with a shaped element having an inlet region formed in a funnel-shaped manner.
Ways of implementing the invention, commercial usability Shown in Figure 1 is a perspective representation of a premix burner, with the viewing direction from the downstream side into the swirl space of a swirl generator 2 that is enclosed by a multiplicity of cone _ g _ shell segments 1. Figure 2 shows the same premix burner, but from a different viewing angle, that is looking at the swirl generator 2 from the outside, said generator being enclosed by eight cone shell segments 1 in the exemplary embodiment represented. The further refinements of the exemplary embodiment represented in Figures 1 and 2 are the same in each case, so that there is no further distinction between Figure 1 and Figure 2.
The premix burner represented has a central receiving unit 3 , which takes the form of a receiving sleeve and is intended for a central fuel supply unit, for example in the form of a fuel nozzle for liquid fuels or fuel lance for a pilot flame (not represented), to be pushed in and held. The cone shell segments 1, connected by their upstream ends to the receiving unit 3, mutually enclose air inlet slits 4 and are placed with respect to a burner axis A extending centrally through the premix burner in such a way that they delimit a swirl space widening sonically in the direction of flow at a cone angle y. Each individual cone shell segment 1 has, moreover, depending on the type of fuel, at least one fuel supply line 5, by means of which fuel can be admixed into the incoming combustion air flow passing through the air inlet slits 2.
While maintaining their shape, the individual cone shell segments 1 open out with their downstream end on an inside wall 6 of a cylindrically formed shaped element 7 surrounding,the cone shell segments 1. The individual cone shell segments 1 are connected to the inside wall 6 of the shaped element 7 along a line of intersection 8, which is obtained by a virtual penetration of each individual cone shell segment 1 with the inside wall 6 of the cylindrical shaped element 7. In this way, the swirl flow formed inside the swirl generator 2 does not undergo any disturbance _ g _ after flowing over the individual cone shell segments 1.
Provided upstream of the shaped element 7, for purposes of an improved incoming air flow through the air inlet slits 4 of the swirl generator 2, is a second shaped element 9, which is likewise formed in a hollow-cylindrical manner and has a greater inside diameter than the first shaped element 7. The transition between the inside diameters of the shaped elements 7 and 9 takes place by means of a discontinuous stage 10, which is adjoined, moreover, by the fuel supply lines 5 of each individual cone shell segment 1.
The downstream contour of the shaped element 7 is formed in a cylindrical manner and offers the possibility of a constructionally simple connection, for example to a combustion chamber (not represented) arranged downstream in the direction of flow of the premix burner represented.
Shown in a perspective representation in Figures 3 and 4 is a further exemplary embodiment of a premix burner formed according to the invention, in which, as a difference from the exemplary embodiment that is represented in Figures 1 and 2, the region of the shaped element 7 is formed as a frustoconical portion tapering conically in the direction of flow. To avoid repetition, the reference numerals that have already been introduced are not described. The exemplary embodiment represented in Figures 3 and 4 has in the region of the shaped element 7 an inside wall 6, which is hatched in the perspective representations and is adjoined by the downstream ends of the cone shell segments 1, while maintaining their shape. Adjoining the inside wall 6 of the shaped element 7 downstream is a shaped element 11 which is formed in a hollow-cylindrical manner and serves as a coupling piece or flanged piece for a following combustion chamber. The inside wall 6 placed with respect to the cone shell segments 1 has the effect that the lines of intersection 8 of the cone shell segments 1 with which they adjoin the inside wall 6 are smaller or shorter in the direction of flow than in the case of the aforementioned exemplary embodiment, in which the cone shell segments adjoin along a cylindrically formed inside wall directed soaxially in relation to the burner axis.
A graphic cross-sectional representation of the embodiment shown in Figures 3 and 4 can be seen in Figure 5. Clearly evident is the shape-maintaining adjoinment of each individual cone shell segment 1 to the inside wall 6 of the shaped element 7 tapering sonically in the direction of flow in the form of a cone, which element goes over in the direction of flow into a straight-cylindrical region 11.
Depicted in Figures 6 and 7 is a further exemplary embodiment of a premix burner, provided with a shaped element 7 which has an upstream region, the so-called inflow region 12, which has an inside wall 6 tapering in the form of a funnel in the direction of flow. The curvature of the inside wall 6 in this inflow region 12 corresponds approximately to the contour of a quarter ellipse. The inflow region 12 is adjoined in the direction of flow as part of the shaped element 7 by a flow region 12' with a largely constant flow cross section, to which finally an inlet flange of a combustion chamber can be attached (not represented).
As also in the variants described above, while retaining their cone shell segment shape, the cone shell segments 1 of the swirl generator 2 end in the adjoining inside wall 6 of the shaped element 7 in a flush manner, as though the cone shell segments would penetrate unhindered through the inside wall 6, but the cone shell segments 1 terminate respectively by means of the lines of intersection 8 at the inside wall 6.
In the case of the inflow region 12 formed as a quarter ellipse, the downstream end regions of the cone shell segments 1 closely follow the elliptical curvature of the inside wall 6 in this region 12. For the meaning of the reference numerals that have already been introduced and are additionally provided in Figures 6 and 7, reference is made to the aforementioned figures.
The connection according to the invention of each individual cone shell segment by its downstream end region to an inside wall of a shaped element surrounding the cone shell segments, while maintaining its shape, leads to minimal irritation of the swirl flow passing through the cone shell segments. As a difference from the previously known premix burners, there are no blocking-off effects in the axial direction through the burner axis associated with the way according to the invention in which the cone shell segments end in the corresponding inside wall while maintaining their shape.
List of reference numerals 1 cone shell segments 2 swirl generator 3 receiving unit 4 air inlet slits fuel supply line 6 inside wall 7 shaped element 8 plane of intersection 9 shaped element step 11 hollow-cylindrically formed shaped element 12 inflow region
Prior art Premix burners of the aforementioned generic type are known from many prior publications, such as for example from EP 0 210 462 A1 and EP 0 321 809 B1, to mention just two. Premix burners of this type are based on the general operating principle of generating within a generally conically formed swirl generator, which provides at least two cone shell segments fitted together in such a way that they appropriately overlap one another, a swirl flow which comprises a mixture of fuel and air and is ignited within a combustion chamber downstream of the premix burner in the direction of flow, thereby forming a premix flame which is spatially as stable as possible. In this case, the spatial position oz the premix tlame is determined by the aerodynamic behavior of the swirl flow, the swirl coefficient of which increases with increasing propagation along the burner axis, consequently becomes unstable and ultimately, as the result of a discontinuous cross-sectional transition between the burner and the combustion chamber, breaks down into an annular swirl flow with the formation of a backf7nw zone, in the forward region of which, in the direction of flow, the premix flame forms.
Of special importance is the aerodynamic stability of the backflow zone forming, which however depends in a highly sensitive way on the design, shape and size of the swirl generator. For example, if the forwardmost front in the direction of flow of the backflow zone forming is not spatially stabilized successfully, thermoacoustic vibrations or pulsations occur to an increased extent within the combustion system, significantly impairing the overall combustion and the release of heat.
In consideration of this fact, the premix burner systems previously known and in use are restricted to overall sizes in which the maximum burner diameter at the burner outlet is only 180 mm. Premix burners of this type additionally have a relatively pointed, i.e.
small, cone angle, of less than or equal to 18°, so that the length of the burner tends to be great in relation to the diameter of the burner facing downstream, but is still well able to be handled for assembly and maintenance purposes.
However, whenever combustion chambers of large dimensions are to be fired, so far use has been made of so-called multiple burner arrangements, which provide for use of the above premix burners. Multiple burner arrangements of this type are disclosed for example by DE 42 23 828 Al or DE 44 12 315 A1. To operate multiple burner arrangements of this type, which are suitable for example for firing a silo combustion chamber, a sophisticated arrangement of the large number of premix burners respectively serving as main burners or pilot burners is required to achieve the end effect of allowing the combustion chamber to continue to be operated with lowest possible emission values in the entire load range.
However, there is the desire to reduce the complexity and with it also the number of the individual premix burners that are required for firing combustion chambers of large dimensions, without losses of quality in the combustion process having to be accepted at the same time. In addition, for reasons concerning the increasingly stringent environmental standards with regard to the reduction of emission values, the aim is to replace the previously operated single diffusion burners that are primarily used for firing silo combustion chambers of large dimensions by more modern, environmentally more acceptable burner systems. In particular with regard to the avoidance of high conversion and first-time acquisition costs, it is desirable to provide premix burners of the largest possible dimensions, in order for example to be able to continue to maintain the operation of such silo combustion chambers of large dimensions with only a single premix burner.
Theoretical studies and trials have shown that simply scaling for example a double cone burner known from EP
0 321 809 B1 does not achieve the objective, especially since, as already mentioned above, the length of the burner would increase disproportionately. Added to this is the fact that the width of the air inlet slits which extend tangentially in the burner axis and through which incoming combustion air flows into the swirl generator to generate the desired swirl flow would likewise increase proportionately, so that good mixing of the fuel and incoming combustion air with adequate quality can no longer be ensured.
A further very important and at the same time critical aspect of a desired increase in size or increase in output of the previously known premix burner systems concerns the downstream termination of the cone shell segments enclosing the swirl space of the swirl generator, which in the example of the double cone burner described in EP 0 321 809 B1 end in axially directed blocking-off elements. These blocking-off elements contribute to the formation of undesired separation vortices which, as coherent vortex structures, lead to combustion instabilities and, associated therewith, to thermoacoustic vibrations or pulsations.
There are also known, premix burner arrangements (for example US 5,588,826) which, as a difference from the premix burner described above, have a transitional geometry interposed between the swirl generator and the combustion chamber, for example in the form of a hollow-cylindrically formed mixing tube. However, transitional geometries of this type are extremely sensitive aerodynamically, since flow separations in this zone can lead to flashback or spontaneous ignition. Similarly, because of their complex production, transitional geometries of this type contribute decisively to the production costs.
Summary of the invention The invention is based on the object of developing a premix burner according to the features of the precharacterizing clause of claim 1 in such a way that, in spite of the increase in size of the burner dimensions, the optimized burner properties in the case of previously known premix burners are to be retained virtually unchanged. So the aim is to increase the size of the burner of previously known premix burner systems in order to reduce the number of burners in multiple burner arrangements, as described at the beginning, and also to reduce the associated system costs. Similarly, it is intended to be possible with the larger premix burner systems to replace previously known single diffusion burners, as are used for example for the firing of silo combustion chambers, by a single premix burner.
The solution achieving the object on which the invention is based is specified in claim 1. Features which advantageously develop the idea of the invention are the subject of the subclaims and are disclosed in the description, in particular with reference to the exemplary embodiments.
According to the invention, a premix burner according to the precharacterizing clause of claim 1 is developed in such a way that, at least at the downstream end region of the swirl generator, a shaped element enclosing the cone shell segments with an inside wall facing the cone shell segments is provided, and that the cone shell segments end in the inside wall in a flush manner while maintaining their shape.
A large number of theoretical studies and experimentally conducted trials to increase the size of the previously known form of premix burners, which usually have a maximum burner diameter on the burner outlet side of 180 mm, led to the realization that the downstream end structure of the cone shell segments has a significant influence on the stability of the premix burner flame forming, in particular in the endeavor to form the premix burner with as large a volume as possible.
So it is found that in most cases of the premix burners that are in use the end regions of the cone shell segments go over in the direction of flow into a hollow-cylindrical flow channel, which is adjoined either directly by the combustion chamber or by an additional mixing zone in the form of a mixing tube.
To avoid the separation vortices following on directly from the cone shell segments in the direction of flow, it has been realized according to the invention that, immediately after leaving the swirl generator, the swirl flow is able to spread out largely without making the swirl flow unstable if, while maintaining their shape, the individual cone shell segments keep in close contact with the inside wall of the flow channel adjoining the swirl generator. The concept of "maintaining their shape" means for the purposes of the invention that the shape of the cone shell segments formed in the manner of segments of a cone remains unchanged in the region where they come into contact with the inside wall of the shaped element enclosing the cone shell segments, as though the cone shell segments would penetrate unhindered through the shaped element in a radially outward direction.
The inside wall of the shaped element also serves for forming a flow channel adjoining the cone shell segments downstream. Depending on the shape and size of the shaped element, it also serves as a mixing tube or as a joining element, in the sense of a flanged piece, by means of which the swirl generator can be connected to a combustion chamber following on in the direction of flow, such as for example a silo combustion chamber, or some other channel structure.
To be able to make the premix burner as compact as possible, i.e. with a burner length that is as small as possible, cone angles of at least 11°, but preferably in the range of 20° and greater, are used, at which angles the cone shell segments surround the swirl space in a conically widening manner. For example, burners with a burner diameter in the outlet region of greater than 500 mm which have a burner length of well below one meter can be made possible . To ensure good mixing _ 7 _ of the mixture of fuel and air within the swirl generator, it is also advantageous to increase the number of cone shell segments and, associated with it, the number of air inlet slits, in order in this way to achieve the smallest possible slit width per air inlet slit.
Brief description of the drawings Without restricting the general idea of the invention, the invention is described below by way of example on the basis of exemplary embodiments with reference to the drawings, in which:
Figures 1 + 2 show a perspective representation of a premix burner with a cylindrically formed shaped element, Figures 3 + 4 show a perspective representation of a premix burner with a frustoconically formed shaped element, Figure 5 shows a sectional representation through a premix burner with a frustoconically formed shaped element, and Figures 6 + 7 show a perspective representation of a premix burner with a shaped element having an inlet region formed in a funnel-shaped manner.
Ways of implementing the invention, commercial usability Shown in Figure 1 is a perspective representation of a premix burner, with the viewing direction from the downstream side into the swirl space of a swirl generator 2 that is enclosed by a multiplicity of cone _ g _ shell segments 1. Figure 2 shows the same premix burner, but from a different viewing angle, that is looking at the swirl generator 2 from the outside, said generator being enclosed by eight cone shell segments 1 in the exemplary embodiment represented. The further refinements of the exemplary embodiment represented in Figures 1 and 2 are the same in each case, so that there is no further distinction between Figure 1 and Figure 2.
The premix burner represented has a central receiving unit 3 , which takes the form of a receiving sleeve and is intended for a central fuel supply unit, for example in the form of a fuel nozzle for liquid fuels or fuel lance for a pilot flame (not represented), to be pushed in and held. The cone shell segments 1, connected by their upstream ends to the receiving unit 3, mutually enclose air inlet slits 4 and are placed with respect to a burner axis A extending centrally through the premix burner in such a way that they delimit a swirl space widening sonically in the direction of flow at a cone angle y. Each individual cone shell segment 1 has, moreover, depending on the type of fuel, at least one fuel supply line 5, by means of which fuel can be admixed into the incoming combustion air flow passing through the air inlet slits 2.
While maintaining their shape, the individual cone shell segments 1 open out with their downstream end on an inside wall 6 of a cylindrically formed shaped element 7 surrounding,the cone shell segments 1. The individual cone shell segments 1 are connected to the inside wall 6 of the shaped element 7 along a line of intersection 8, which is obtained by a virtual penetration of each individual cone shell segment 1 with the inside wall 6 of the cylindrical shaped element 7. In this way, the swirl flow formed inside the swirl generator 2 does not undergo any disturbance _ g _ after flowing over the individual cone shell segments 1.
Provided upstream of the shaped element 7, for purposes of an improved incoming air flow through the air inlet slits 4 of the swirl generator 2, is a second shaped element 9, which is likewise formed in a hollow-cylindrical manner and has a greater inside diameter than the first shaped element 7. The transition between the inside diameters of the shaped elements 7 and 9 takes place by means of a discontinuous stage 10, which is adjoined, moreover, by the fuel supply lines 5 of each individual cone shell segment 1.
The downstream contour of the shaped element 7 is formed in a cylindrical manner and offers the possibility of a constructionally simple connection, for example to a combustion chamber (not represented) arranged downstream in the direction of flow of the premix burner represented.
Shown in a perspective representation in Figures 3 and 4 is a further exemplary embodiment of a premix burner formed according to the invention, in which, as a difference from the exemplary embodiment that is represented in Figures 1 and 2, the region of the shaped element 7 is formed as a frustoconical portion tapering conically in the direction of flow. To avoid repetition, the reference numerals that have already been introduced are not described. The exemplary embodiment represented in Figures 3 and 4 has in the region of the shaped element 7 an inside wall 6, which is hatched in the perspective representations and is adjoined by the downstream ends of the cone shell segments 1, while maintaining their shape. Adjoining the inside wall 6 of the shaped element 7 downstream is a shaped element 11 which is formed in a hollow-cylindrical manner and serves as a coupling piece or flanged piece for a following combustion chamber. The inside wall 6 placed with respect to the cone shell segments 1 has the effect that the lines of intersection 8 of the cone shell segments 1 with which they adjoin the inside wall 6 are smaller or shorter in the direction of flow than in the case of the aforementioned exemplary embodiment, in which the cone shell segments adjoin along a cylindrically formed inside wall directed soaxially in relation to the burner axis.
A graphic cross-sectional representation of the embodiment shown in Figures 3 and 4 can be seen in Figure 5. Clearly evident is the shape-maintaining adjoinment of each individual cone shell segment 1 to the inside wall 6 of the shaped element 7 tapering sonically in the direction of flow in the form of a cone, which element goes over in the direction of flow into a straight-cylindrical region 11.
Depicted in Figures 6 and 7 is a further exemplary embodiment of a premix burner, provided with a shaped element 7 which has an upstream region, the so-called inflow region 12, which has an inside wall 6 tapering in the form of a funnel in the direction of flow. The curvature of the inside wall 6 in this inflow region 12 corresponds approximately to the contour of a quarter ellipse. The inflow region 12 is adjoined in the direction of flow as part of the shaped element 7 by a flow region 12' with a largely constant flow cross section, to which finally an inlet flange of a combustion chamber can be attached (not represented).
As also in the variants described above, while retaining their cone shell segment shape, the cone shell segments 1 of the swirl generator 2 end in the adjoining inside wall 6 of the shaped element 7 in a flush manner, as though the cone shell segments would penetrate unhindered through the inside wall 6, but the cone shell segments 1 terminate respectively by means of the lines of intersection 8 at the inside wall 6.
In the case of the inflow region 12 formed as a quarter ellipse, the downstream end regions of the cone shell segments 1 closely follow the elliptical curvature of the inside wall 6 in this region 12. For the meaning of the reference numerals that have already been introduced and are additionally provided in Figures 6 and 7, reference is made to the aforementioned figures.
The connection according to the invention of each individual cone shell segment by its downstream end region to an inside wall of a shaped element surrounding the cone shell segments, while maintaining its shape, leads to minimal irritation of the swirl flow passing through the cone shell segments. As a difference from the previously known premix burners, there are no blocking-off effects in the axial direction through the burner axis associated with the way according to the invention in which the cone shell segments end in the corresponding inside wall while maintaining their shape.
List of reference numerals 1 cone shell segments 2 swirl generator 3 receiving unit 4 air inlet slits fuel supply line 6 inside wall 7 shaped element 8 plane of intersection 9 shaped element step 11 hollow-cylindrically formed shaped element 12 inflow region
Claims (10)
1. A premix burner for operating a combustion chamber with a gaseous and/or liquid fuel, having a swirl generator (2) for inducing a swirl flow in an incoming combustion air flow and means (5) for injecting fuel into the swirl flow, the swirl generator (2) having at least two cone shell segments (1) which fit together to form a flow body and together enclose a sonically formed swirl space with a cone angle .gamma. and air inlet slits (4) directed tangentially to the length of the cone, characterized in that the cone angle .gamma. is greater than or equal to 20° and the swirl generator (2) has a downstream burner diameter of greater than 180 mm, and in that, at least at the downstream end region of the swirl generator (2), a shaped element (7) enclosing the cone shell segments (1) with an inside wall (6) facing the cone shell segments (1) is provided, and in that the cone shell segments (1) end in the inside wall (6) in a flush manner while maintaining their shape.
2. The premix burner as claimed in claim 1, characterized in that the shaped element (7) encloses the cone shell segments (1) at their downstream end region in an annular manner in such a way that the inside wall (6) of the shaped element (7) is connected in each case to the cone shell segment (1) by means of a line of intersection (8) through the respective cone shell segment (1), along which the cone shell segment (1) virtually penetrates the inside wall (6) while maintaining its shape.
3. The premix burner as claimed in claim 1 or 2, characterized in that the inside wall (6) is frustoconically formed and has a contour tapering sonically in the direction of flow.
4. ~The premix burner as claimed in claim 1 or 2, characterized in that the inside wall (6) has adjoining the swirl generator (2) directly downstream an inflow region (12) in which the inside wall (6) is formed tapering in a funnel-shaped manner in the direction of flow.
5. ~The premix burner as claimed in claim 4, characterized in that the inside wall (6) has in the inflow region (12) a curvature contour formed in longitudinal section as a quarter ellipse.
6. ~The premix burner as claimed in claim 4 or 5, characterized in that downstream of the inflow region (12) the inside wall (6) goes over into a flow portion (12') which has a flow cross section remaining the same in the direction of flow.
7. ~The premix burner as claimed in claim 1 or 2, characterized in that the inside wall (6) is cylindrically formed.
8. ~The premix burner as claimed in claim 3 or 7, characterized in that the first shaped element (7) is adjoined in the direction of flow by a further~
shaped element (11), with a further inside wall, which axially has a constant flow cross section.
shaped element (11), with a further inside wall, which axially has a constant flow cross section.
9. ~The premix burner as claimed in one of claims 1 to 8, characterized in that at least four, preferably eight, cone shell segments (1) are provided to form the swirl space.
10. ~The use of the premix burner as claimed in one of claims 1 to 9, for firing a silo combustion chamber.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH2102004 | 2004-02-12 | ||
| CH00210/04 | 2004-02-12 | ||
| PCT/EP2005/050579 WO2005078348A1 (en) | 2004-02-12 | 2005-02-09 | Premixing burner arrangement for operating a burner chamber and method for operating a burner chamber |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2555481A1 true CA2555481A1 (en) | 2005-08-25 |
Family
ID=34842438
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002555481A Abandoned CA2555481A1 (en) | 2004-02-12 | 2005-02-09 | Premix burner arrangement for operating a combustion chamber and method for operating a combustion chamber |
Country Status (10)
| Country | Link |
|---|---|
| US (1) | US20070042307A1 (en) |
| EP (1) | EP1714081B1 (en) |
| CN (1) | CN1942710A (en) |
| AT (1) | ATE391887T1 (en) |
| BR (1) | BRPI0507640A (en) |
| CA (1) | CA2555481A1 (en) |
| DE (1) | DE502005003648D1 (en) |
| MX (1) | MXPA06008994A (en) |
| MY (1) | MY141577A (en) |
| WO (1) | WO2005078348A1 (en) |
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| CN101137868A (en) * | 2005-03-09 | 2008-03-05 | 阿尔斯通技术有限公司 | Premix burner for producing an ignitable fuel/air mixture |
| CN101137869A (en) * | 2005-03-09 | 2008-03-05 | 阿尔斯托姆科技有限公司 | Premix burner for operating a combustion chamber |
| DE102007043626A1 (en) * | 2007-09-13 | 2009-03-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine lean burn burner with fuel nozzle with controlled fuel inhomogeneity |
| CN101709884B (en) * | 2009-11-25 | 2012-07-04 | 北京航空航天大学 | Premixing and pre-evaporating combustion chamber |
| TW201229437A (en) * | 2011-01-11 | 2012-07-16 | Pro Iroda Ind Inc | Device for increasing flame height |
| TW201303226A (en) * | 2011-07-06 | 2013-01-16 | Pro Iroda Ind Inc | Flame set with lifting device |
| JP2015512500A (en) * | 2012-03-29 | 2015-04-27 | アルストム テクノロジー リミテッドＡＬＳＴＯＭ Ｔｅｃｈｎｏｌｏｇｙ Ｌｔｄ | Gas turbine combustor |
| US8813967B2 (en) * | 2012-05-02 | 2014-08-26 | Alstom Technology Ltd | Adjustable mill classifier |
| EP2685160B1 (en) | 2012-07-10 | 2018-02-21 | Ansaldo Energia Switzerland AG | Premix burner of the multi-cone type for a gas turbine |
| EP2685163B1 (en) * | 2012-07-10 | 2020-03-25 | Ansaldo Energia Switzerland AG | Premix burner of the multi-cone type for a gas turbine |
| EP2685161B1 (en) * | 2012-07-10 | 2018-01-17 | Ansaldo Energia Switzerland AG | Combustor arrangement, especially for a gas turbine |
| RU2570989C2 (en) * | 2012-07-10 | 2015-12-20 | Альстом Текнолоджи Лтд | Gas turbine combustion chamber axial swirler |
| EP2703721B1 (en) | 2012-08-31 | 2019-05-22 | Ansaldo Energia IP UK Limited | Premix burner |
| US20150153066A1 (en) * | 2013-12-04 | 2015-06-04 | Victory Energy Operations. L.L.C. | Method of providing heat to a heat exchanger apparatus via a burner |
| DE102021002508A1 (en) * | 2021-05-12 | 2022-11-17 | Martin GmbH für Umwelt- und Energietechnik | Nozzle for injecting gas into an incinerator with a tube and a swirler, flue with such a nozzle and method for using such a nozzle |
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| US2166276A (en) * | 1937-10-06 | 1939-07-18 | American Blower Corp | Tunnel fan |
| FR2082028A5 (en) * | 1969-12-29 | 1971-12-10 | Snecma | |
| US3845903A (en) * | 1973-08-15 | 1974-11-05 | Dunham Bush Inc | One piece radial vane diffuser and method of manufacturing the same |
| CA999812A (en) * | 1975-06-27 | 1976-11-16 | Thomas D. Brown | Oil burner assembly with air swirler providing blue flame combustion |
| JPS5535885A (en) * | 1978-09-06 | 1980-03-13 | Kobe Steel Ltd | Combustion method capable of minimizing production of nitrogen oxide and smoke |
| US4464108A (en) * | 1980-11-21 | 1984-08-07 | Donald Korenyi | Combustion apparatus |
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| CH660403A5 (en) * | 1983-08-30 | 1987-04-15 | Bbc Brown Boveri & Cie | AXIAL SWIRL FOR GENERATING TURNING FLOWS. |
| US5349813A (en) * | 1992-11-09 | 1994-09-27 | Foster Wheeler Energy Corporation | Vibration of systems comprised of hot and cold components |
| US5470224A (en) * | 1993-07-16 | 1995-11-28 | Radian Corporation | Apparatus and method for reducing NOx , CO and hydrocarbon emissions when burning gaseous fuels |
| DE4424639A1 (en) * | 1994-07-13 | 1996-01-18 | Abb Research Ltd | Method and device for fuel distribution in a burner suitable for both liquid and gaseous fuels |
| DE4435266A1 (en) * | 1994-10-01 | 1996-04-04 | Abb Management Ag | burner |
| DE4440558A1 (en) * | 1994-11-12 | 1996-05-15 | Abb Research Ltd | Premix burner |
| DE19527453B4 (en) * | 1995-07-27 | 2009-05-07 | Alstom | premix |
| DE19547912A1 (en) * | 1995-12-21 | 1997-06-26 | Abb Research Ltd | Burners for a heat generator |
| DE19608349A1 (en) * | 1996-03-05 | 1997-09-11 | Abb Research Ltd | Pressure atomizer nozzle |
| DK0836049T3 (en) * | 1996-10-08 | 2002-04-08 | Enel Spa | Injection nozzle for powdered coal |
| GB9709205D0 (en) * | 1997-05-07 | 1997-06-25 | Boc Group Plc | Oxy/oil swirl burner |
| DE19736902A1 (en) * | 1997-08-25 | 1999-03-04 | Abb Research Ltd | Burners for a heat generator |
| US6502399B2 (en) * | 1997-09-10 | 2003-01-07 | Mitsubishi Heavy Industries, Ltd. | Three-dimensional swirler in a gas turbine combustor |
| US6004097A (en) * | 1997-09-26 | 1999-12-21 | Sure Alloy Steel Corp. | Coal mill exhauster fan |
| DE59708077D1 (en) * | 1997-12-22 | 2002-10-02 | Alstom | burner |
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| EP0985877A1 (en) * | 1998-09-10 | 2000-03-15 | Abb Research Ltd. | Device and method for minimizing thermoacoustic oscillations in gas turbine combustion chambers |
| DE19859829A1 (en) * | 1998-12-23 | 2000-06-29 | Abb Alstom Power Ch Ag | Burner for operating a heat generator |
| DE10040869A1 (en) * | 2000-08-21 | 2002-03-07 | Alstom Power Nv | Method and device for suppressing flow vortices within a fluid power machine |
| DE10049205A1 (en) * | 2000-10-05 | 2002-05-23 | Alstom Switzerland Ltd | Process for supplying fuel to a premix burner for operating a gas turbine comprises introducing premix gas separately via two axially divided regions along the burner shell |
| DE10164099A1 (en) * | 2001-12-24 | 2003-07-03 | Alstom Switzerland Ltd | Burner with staged fuel injection |
| US7070637B1 (en) * | 2003-01-21 | 2006-07-04 | The Board Of Trustees Of The University Of Illinois | Apparatus for separating particles from a fluid |
-
2005
- 2005-02-09 WO PCT/EP2005/050579 patent/WO2005078348A1/en active IP Right Grant
- 2005-02-09 DE DE502005003648T patent/DE502005003648D1/en active Active
- 2005-02-09 MX MXPA06008994A patent/MXPA06008994A/en active IP Right Grant
- 2005-02-09 BR BRPI0507640-4A patent/BRPI0507640A/en not_active IP Right Cessation
- 2005-02-09 CN CNA2005800109198A patent/CN1942710A/en active Pending
- 2005-02-09 AT AT05726413T patent/ATE391887T1/en not_active IP Right Cessation
- 2005-02-09 CA CA002555481A patent/CA2555481A1/en not_active Abandoned
- 2005-02-09 EP EP05726413A patent/EP1714081B1/en not_active Not-in-force
- 2005-02-14 MY MYPI20050525A patent/MY141577A/en unknown
-
2006
- 2006-08-14 US US11/503,163 patent/US20070042307A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| MXPA06008994A (en) | 2006-12-14 |
| MY141577A (en) | 2010-05-14 |
| EP1714081B1 (en) | 2008-04-09 |
| US20070042307A1 (en) | 2007-02-22 |
| DE502005003648D1 (en) | 2008-05-21 |
| ATE391887T1 (en) | 2008-04-15 |
| CN1942710A (en) | 2007-04-04 |
| EP1714081A1 (en) | 2006-10-25 |
| WO2005078348A1 (en) | 2005-08-25 |
| BRPI0507640A (en) | 2007-07-10 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |