EP1856447B1 - Burner comprising a premix for combustion chamber - Google Patents
Burner comprising a premix for combustion chamber Download PDFInfo
- Publication number
- EP1856447B1 EP1856447B1 EP06708627.2A EP06708627A EP1856447B1 EP 1856447 B1 EP1856447 B1 EP 1856447B1 EP 06708627 A EP06708627 A EP 06708627A EP 1856447 B1 EP1856447 B1 EP 1856447B1
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- EP
- European Patent Office
- Prior art keywords
- burner
- burner shell
- shell section
- premix
- section
- 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.)
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- 238000002485 combustion reaction Methods 0.000 title claims description 16
- 239000000446 fuel Substances 0.000 claims description 17
- 230000008859 change Effects 0.000 claims description 4
- 238000013461 design Methods 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 241000237942 Conidae Species 0.000 claims description 3
- 230000001154 acute effect Effects 0.000 claims description 2
- 238000005452 bending Methods 0.000 claims description 2
- 230000007480 spreading Effects 0.000 claims description 2
- 238000003892 spreading Methods 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 claims 1
- 230000000295 complement effect Effects 0.000 claims 1
- 239000007769 metal material Substances 0.000 claims 1
- 238000005507 spraying Methods 0.000 claims 1
- 239000010959 steel Substances 0.000 claims 1
- 239000000243 solution Substances 0.000 description 4
- 238000010521 absorption reaction Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000035508 accumulation Effects 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009172 bursting Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
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- 238000009792 diffusion process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
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- 230000010355 oscillation Effects 0.000 description 1
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- 238000012549 training Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
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- 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
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- 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
Definitions
- the invention relates to a premix burner for producing an ignitable fuel-air mixture, with a swirl generator, which provides at least two supplementing to a flow body burner shells, each having a part cone shaped first burner shell portion and together define an axially conically widening swirl space, and the in axial longitudinal cone extension limit mutually tangential air inlet slots, passes through the combustion air supply into the swirl space, in which an axially spreading swirl flow is formed, and with means for injection of fuel, which are arranged at least partially along the tangential air inlet slots.
- a swirl generator which provides at least two supplementing to a flow body burner shells, each having a part cone shaped first burner shell portion and together define an axially conically widening swirl space, and the in axial longitudinal cone extension limit mutually tangential air inlet slots, passes through the combustion air supply into the swirl space, in which an axially spreading swirl flow is formed, and with means for injection of fuel, which are arranged at least partially along the tangential air inlet slots.
- Premix burners of the abovementioned type are known from a large number of published publications, for example, from EP 0 210 462 A1 as well as the EP 0 321 809 B1 , to name just a few.
- Premix burners of this type is based on the general operating principle, within a mostly designed as a conical swirl generator, which provides at least two with corresponding overlap overlapping Operakegelschalen to produce a consisting of a fuel-air mixture swirl flow, which within a downstream of the premix burner combustion chamber under training a spatially stable as possible premix flame is made to ignite.
- the spatial position of the premix flame is determined by the aerodynamic behavior of the swirl flow, whose swirl increases with increasing propagation along the burner axis, thus becomes unstable and ultimately bursting through an unsteady cross-sectional transition between the burner and combustion chamber in an annular swirling flow to form a remindströmzone, in whose front-flow area, the premix flame forms.
- thermoacoustic oscillations or pulsations within the combustion system occur, which considerably affect the overall combustion and the heat release.
- Vormischbrennersysteme be limited to sizes whose maximum burner diameter at the burner outlet is only 180 mm.
- premix burners have a relatively sharp, i. small cone angle of less than or equal to 18 °, so that the burner length in relation to the down-turned burner diameter rather large, but for assembly and maintenance purposes is still quite manageable.
- the partial cone shells intended for switching or deflecting the supply air into the swirl generator which are also referred to as burner bowls, are designed as thin-walled deflectors which have the shape of the lateral surface of conical halves or smaller conical segments and the swirl space on the radial side limit, the burner shells by their spatial arrangement each mutually tangential to the burner axis oriented air inlet slots with each other.
- a burner for operating a heat generator can be seen, with a swirl generator whose oriented in the flow direction inlet cross-section is rectangular and for reasons of improved mixing downstream of a flow in the square or round flow cross-section provides, which is preferably followed by a cross-section round mixing section.
- a swirl generator shown in perspective is shown, whose swirl space is bounded by curved burner shells 156 radially.
- the burner shell or swirl blade 156 shown in cross-section has three burner shell sections, which are integrally connected to one another, wherein the respective partial cone-shaped first burner shell section is flush with a second burner shell section curved in the opposite direction to the first burner shell section and a third burner shell section adjoins the second burner shell section flush with a curvature tangential to the second burner shell section.
- the invention has the object of developing a premix burner according to the features of the preamble of claim 1 such that despite enlarging the burner dimensions, the burner properties optimized in previously known premix burners should remain virtually unchanged.
- it is necessary to solve the aerodynamic problems occurring in premix burners with multiple shell arrangements and to eliminate the associated disadvantages and dangers.
- it is necessary to take measures that no reignition phenomena which cause gas accumulating in return flow zones occur.
- the burner shells bounding the swirl space radially are burner bowls describing aerodynamically exclusively vanes that describe a partial conical shape, so that the supply air flow flowing through the air inlet slots into the swirl chamber is largely loss-free, i. without any edge vortex formation, between two the air inlet slot bounding burner shells is performed. Due to the burner shell geometry, which are formed in the usual way as a thin inlet air flow diverting baffles, a supply air flow flowing through the air inlet slots along a supply air flow facing surface of the burner shell is initially accelerated continuously as it enters the air inlet slot and gradually redirected until the air flow through the burner shell leaves to the swirl space.
- the burner shell geometry has differently shaped, the air inlet slot laterally limiting surface areas through which the radially in the air inlet slot incoming air flow is largely without resistance and without formation of near-surface flow edge vortex in the swirl space to form an axially extending to the burner swirl flow is deflected.
- any backflow zones which form in previously known premix burners with multi-shell arrangements can be avoided, in which gas accumulations can be formed, which can lead to damage to the premix burner structure and, in particular, to the burner shells by way of spontaneous deflagrations.
- a burner shell designed in each case according to the invention has three burner shell sections of different shape, which are connected in one piece with each other, wherein the respective first conical cup section is flush with one opposite the first Burner cup portion curved second burner cup portion is added and a third burner cup portion is flush with the second burner cup portion, with a tangent to the second burner cup portion curvature.
- the third burner shell section limits one side of each one of the tangential air inlet slots and provides a leading edge for the combustion air supply.
- the determined by the partial cone shape curvature of the partially conical first burner shell section is continuous, ie transitionless, in the curvature of the second Brennerschalenabiteses and all places of a curvature change describe a line, the so-called inflection point line along which the means are provided for fuel injection.
- such a trained burner shell can be produced in the context of a casting process or by way of a forming or material removal process.
- FIG. 1 is a burner shell according to the invention formed schematically with a first burner shell section 1, which is described by the shell shape of a cone part.
- a sub-segment 2 of a conical body is shown as an auxiliary construction, along the conical mantle surface 3 of the first burner shell section 1 conforms.
- the first burner shell section 1 corresponds to the shape of those burner shells which have been in use up to now, the embodiments according to FIGS FIG. 1 longer trained side edge 4 of the trailing edge of the burner shell corresponds, as well as indicated by the polyline 5 leading edge of the burner shell section 1 of the leading edge corresponds to a previously common burner shell.
- FIG. 1 shown burner shell along its curved upper side edge 6 and its lower side edge 7 attached for purposes of attachment to corresponding premix burner components.
- the burner shell according to the invention provides two further burner shell sections 8, 9, which are seamless and integral to the line-shaped end region of the first, partially conical shape indicated by the line 5 connect the trained burner bowl section 1.
- the second burner bowl section 8 immediately adjacent to the first burner bowl section 1 has a curvature that is oriented opposite to the curvature of the first part-cone-shaped burner shell section 1. From the graphical representation of the embodiment according to FIG. 1 it can be seen that the first burner shell section 1 is convex and the second and third burner shell sections 8, 9 are curved concavely to the plane of the drawing. In this case, the second burner shell section has the curvature of a quarter ellipse.
- FIG. 1 To illustrate the concave curvature of the second burner shell section 8 is in FIG. 1 a prismatic body 10 shown, the second burner shell section 8 facing surface of the curvature corresponds to a quarter ellipse.
- FIG. 1 illustrated sub-segment body 2 as well as the prismatic body 10 represent exclusively auxiliary body, which serve to better illustrate the geometric shape of the burner shell.
- the third burner shell section which adjoins the virtually extending boundary line 11 of the second burner shell section 8, is flush, which provides a curvature which adjoins the second burner section tangentially.
- the third burner shell section 9 essentially has a triangular-shaped basic shape with a front boundary edge 12, which at the same time also serves as the leading edge of the burner shell designed in accordance with the invention.
- burner shell to a combination of a pure cone-shaped burner shell portion, a curved sheet with a Surface shape of a quarter ellipse and a tangential extension, which is represented by the third burner shell portion 9.
- burner shell which is otherwise made of a heat-resistant sheet material and preferably along its entire surface extent has a substantially constant thickness, enclosing radially a portion of the conically extending swirl space of a premix burner.
- the viewer of the in FIG. 1 shown burner shell facing surface is thus remote from the swirl space.
- fuel line which serves for a fuel supply through each provided along the inflection point line 5 passage openings 13.
- FIG. 2 shows an upper part of the solution according to trained burner shell.
- the curvature behavior of the respective burner shell sections 1, 8 and 9 can be seen from the curvature profile of the uppermost side edge of the burner shell.
- the third burner shell section 9 closes at the upper end of the burner shell under a acute angle to the second burner section 8 and extends substantially the curvature of the second burner shell section 8 at the location of the transition line 11 in a tangential continuation.
- FIG. 2 are taken from the burner cup passing through openings 13, which are arranged along the inflection point line 5, is injected through the gaseous fuel.
- FIG. 3 shows a three-dimensional view of a burner shell described above from a viewing angle, which shows the surface of the burner shell facing the swirl space.
- a burner shell in plan view facing view is the FIG. 4 to be referred to in the following together with FIG. 3 Reference is made.
- a stylized by the flow arrow radially incident on the leading edge 12 of the burner shell air flow L is accelerated in the third and second burner section 9, 8 in the flow direction and further deflected by the partially conical first burner shell section 1 successively until the flow L the burner shell over leaves the burner bowl section 1 towards the burner chamber or swirl space.
- gaseous fuel is added through the openings 13 to the air flow L, resulting in an effective mixing of fuel and air already in this flow region.
- the burner shell geometry according to the solution thus avoids any backflow zones within the air flow along the surface of the burner shell facing the air flow L.
- the burner shell geometry is also designed such that the manufacture of the burner shells is possible without special tools, for example without special press-forming tools.
- the shell geometry is always described by a family of straight lines, which are oriented axially or in the longitudinal extent of the burner shell, whereby the burner shell can be produced by means of a CNC bending machine.
- FIG. 5 a premix burner is shown in three-dimensional representation, the eight an inner swirl space radially defining burner shells B, which are individually formed in the manner described above.
- Two mutually adjacent burner shells B include an air inlet slot LS, through which an air flow can penetrate into the swirl space. It is obvious that the absorption capacity of the premix burner by providing eight individual air inlet slots LS is much greater than in the case of so-called double-cone burners in which only two partial cone shells limit the swirl space.
- the individual burner shells B are firmly connected on the one hand with their upper boundary edge with a cylindrically shaped centrally arranged holding structure 15, through which means for axial fuel feed can be used in the axial direction.
- the burner shells B are connected along their lower boundary edge with a mold element 16 through which the swirl flow forming within the swirl generator is transferred to a mixing tube (not further shown) or directly into a combustion chamber (not shown) for further mixing or ignition.
- a mixing tube not further shown
- a combustion chamber not shown
- gaseous fuel is fed into the region of the air inlet slots LS through the linearly arranged openings 13 to form a fuel-air mixture.
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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)
Description
Die Erfindung bezieht sich auf einen Vormischbrenner zum Erzeugen eines zündfähigen Brennstoff-Luftgemisches, mit einem Drallerzeuger, der wenigstens zwei sich zu einem Durchströmungskörper ergänzende Brennerschalen vorsieht, die jeweils einen teilkegelförmig ausgebildeten ersten Brennerschalenabschnitt aufweisen und gemeinsam einen sich axialwärts kegelförmig erweiternden Drallraum eingrenzen, und die in axialer Kegellängserstreckung gegenseitig tangentiale Lufteintrittsschlitze begrenzen, durch die Verbrennungszuluft in den Drallraum gelangt, in dem sich eine axialwärts ausbreitende Drallströmung ausbildet, sowie mit Mitteln zur Eindüsung von Brennstoff, die wenigstens abschnittsweise längs der tangential verlaufenden Lufteintrittschlitze angeordnet sind.The invention relates to a premix burner for producing an ignitable fuel-air mixture, with a swirl generator, which provides at least two supplementing to a flow body burner shells, each having a part cone shaped first burner shell portion and together define an axially conically widening swirl space, and the in axial longitudinal cone extension limit mutually tangential air inlet slots, passes through the combustion air supply into the swirl space, in which an axially spreading swirl flow is formed, and with means for injection of fuel, which are arranged at least partially along the tangential air inlet slots.
Vormischbrenner der vorstehend genannten Gattung sind aus einer Vielzahl vor veröffentlichter Druckschriften bekannt, so bspw. aus der
Von besonderer Bedeutung ist die aerodynamische Stabilität der sich ausbildenden Rückströmzone, die jedoch in höchst sensibler Weise vom Design, Form und Größe des Drallerzeugers abhängt. Gelingt es beispielsweise nicht, die in Strömungsrichtung vorderste Front der sich ausbildenden Rückströmzone räumlich zu stabilisieren, so treten verstärkt thermoakustische Schwingungen bzw. Pulsationen innerhalb des Verbrennungssystems auf, die die gesamte Verbrennung sowie die Wärmefreisetzung wesentlich beeinträchtigen.Of particular importance is the aerodynamic stability of the forming Rückströmzone, but highly sensitive to the design, shape and size of the swirl generator depends. If, for example, it is not possible to spatially stabilize the upstream front of the forming backflow zone in the direction of flow, then thermoacoustic oscillations or pulsations within the combustion system occur, which considerably affect the overall combustion and the heat release.
Eingedenk dieser Tatsache sind die bisher bekannten und im Einsatz befindlichen Vormischbrennersysteme auf Baugrößen beschränkt, deren maximaler Brennerdurchmesser am Brenneraustritt lediglich 180 mm beträgt. Derartige Vormischbrenner weisen darüber hinaus einen verhältnismäßig spitzen, d.h. kleinen Kegelwinkel von kleiner gleich 18° auf, so dass die Brennerlänge im Verhältnis zum stromab gewandten Brennerdurchmesser eher groß, jedoch zu Montage- und Wartungszwecken noch durchaus handhabbar ist.Bearing this in mind, the previously known and in use Vormischbrennersysteme be limited to sizes whose maximum burner diameter at the burner outlet is only 180 mm. Moreover, such premix burners have a relatively sharp, i. small cone angle of less than or equal to 18 °, so that the burner length in relation to the down-turned burner diameter rather large, but for assembly and maintenance purposes is still quite manageable.
Gilt es jedoch groß dimensionierte Brennkammern zu befeuern, so bedient man sich bis anhin so genannte Mehrfachbrenneranordnungen, die den Einsatz der vorstehenden Vormischbrenner vorsehen. Derartige im Aufbau komplexe Mehrfachbrenneranordnungen gehen beispielsweise aus der
Theoretische Überlegungen sowie auch Versuche haben gezeigt, dass eine einfache Skalierung beispielsweise eines aus der
In den meisten in Einsatz befindlichen Vormischbrennern sind die zur Um- bzw. Einlenkung der Zuluft in den Drallerzeuger vorgesehenen Teilkegelschalen, die auch als Brennerschalen bezeichnet werden, als dünnwandige Umlenkbleche ausgebildet, die die Form der Mantelfläche von Kegelhälften oder kleineren Kegelsegmenten aufweisen und radialseits den Drallraum begrenzen, wobei die Brennerschalen durch ihre räumliche Anordnung jeweils gegenseitig tangential zur Brennerachse orientierte Lufteintrittsschlitze miteinander einschließen.In most of the premix burners in use, the partial cone shells intended for switching or deflecting the supply air into the swirl generator, which are also referred to as burner bowls, are designed as thin-walled deflectors which have the shape of the lateral surface of conical halves or smaller conical segments and the swirl space on the radial side limit, the burner shells by their spatial arrangement each mutually tangential to the burner axis oriented air inlet slots with each other.
Im Bestreben das Schluck- und Leistungsvermögen derartiger Vormischbrenner zu verbessern, sind Drallerzeuger mit mehr als zwei Brennerschalen bekannt, so genannte mehrschalige Vormischbrenner, die auch einen größeren Brennerdurchmesser gewährleisten können. Es zeigt sich jedoch, dass sich bei derartigen Mehrschalenanordnungen keine zufrieden stellenden Durchmischungsergebnisse einstellen, zumal aerodynamische Probleme auftreten, die höchstwahrscheinlich auf lokal im Bereich der einzelnen Brennerschalen sich ausbildende Rückströmzonen zurückzuführen sind. Dies führt einerseits zu Wirkungsgradverlusten, birgt aber auch Gefahren in sich, sofern sich brennbares Gas in derartigen Rückströmzonen ansammeln und letztlich zünden kann.In an effort to improve the absorption and performance of such premix burners, swirl generators with more than two burner bowls are known, so-called multi-shell premix burners, which can also ensure a larger burner diameter. However, it has been found that satisfactory mixing results do not occur in such multi-shell arrangements, especially since aerodynamic problems occur. which are most likely due to locally formed in the region of the individual burner shells Rückströmzonen. On the one hand, this leads to losses in efficiency, but also poses dangers if combustible gas can accumulate in such return flow zones and ultimately ignite.
Der
Der Erfindung liegt die Aufgabe zugrunde einen Vormischbrenner gemäß den Merkmalen des Oberbegriffes des Anspruches 1 derart weiterzubilden, dass trotz Vergrößerung der Brennerdimensionen die bei bisher bekannten Vormischbrennern optimierten Brennereigenschaften nahezu unverändert erhalten bleiben sollen. So gilt es, die bei Vormischbrennern mit Mehrfachschalenanordnungen auftretenden aerodynamischen Probleme zu lösen und die damit verbundenen Nachteile und Gefahren zu beseitigen. Insbesondere gilt es Massnahmen zu treffen, dass keine durch sich in Rückströmzonen ansammelndes Gas verursachende Rückzünderscheinungen auftreten.The invention has the object of developing a premix burner according to the features of the preamble of
Die Lösung der der Erfindung zugrunde liegenden Aufgabe ist im Anspruch 1 angegeben. Den Erfindungsgedanken vorteilhaft weiterbildende Merkmale sind Gegenstand der Unteransprüche sowie der Beschreibung insbesondere unter Bezugnahme auf die Ausführungsbeispiele zu entnehmen.The solution of the problem underlying the invention is specified in
Grundsätzlich sind die den Drallraum radialwärts begrenzenden Brennerschalen aerodynamisch ausschliesslich durch eine Teilkegelform beschreibende Brennerschalen derart ausgebildet, dass der durch die Lufteintrittsschlitze in den Drallraum einströmende Zuluftstrom weitgehend verlustfrei, d.h. ohne jegliche Randwirbelbildung, zwischen zwei den Lufteintrittsschlitz begrenzende Brennerschalen geführt wird. Durch die Brennerschalengeometrie, die in üblicher Weise als dünne die Zuluftströmung umleitende Umlenkbleche ausgebildet sind, wird ein durch die Lufteintrittsschlitze hindurchströmender Zuluftstrom längs einer den Zuluftstrom zugewandten Oberfläche der Brennerschale bei Eintritt in den Lufteintrittsschlitz zunächst kontinuierlich beschleunigt und sukzessive umgelenkt, bis die Luftströmung die Brennerschale hin zum Drallraum verlässt. Die Brennerschalengeometrie weist unterschiedlich geformte, den Lufteintrittsschlitz seitlich begrenzende Oberflächenbereiche auf, durch die die radial in den Lufteintrittsschlitz einströmende Luftströmung weitgehend widerstandslos und ohne Ausbildung von oberflächennahen Strömungsrandwirbel in den Drallraum zur Ausbildung einer sich axialwärts zum Brenner ausbreitenden Drallströmung umgelenkt wird. Auf diese Weise können jegliche sich bei bisher bekannten Vormischbrennern mit Mehrschalenanordnungen ausbildende Rückströmzonen vermieden werden, in denen sich darüber hinaus Gasansammlungen auszubilden vermögen, die im Wege spontaner Verpuffungen zu Beschädigungen an der Vormischbrennerstruktur und insbesondere an den Brennerschalen führen können.In principle, the burner shells bounding the swirl space radially are burner bowls describing aerodynamically exclusively vanes that describe a partial conical shape, so that the supply air flow flowing through the air inlet slots into the swirl chamber is largely loss-free, i. without any edge vortex formation, between two the air inlet slot bounding burner shells is performed. Due to the burner shell geometry, which are formed in the usual way as a thin inlet air flow diverting baffles, a supply air flow flowing through the air inlet slots along a supply air flow facing surface of the burner shell is initially accelerated continuously as it enters the air inlet slot and gradually redirected until the air flow through the burner shell leaves to the swirl space. The burner shell geometry has differently shaped, the air inlet slot laterally limiting surface areas through which the radially in the air inlet slot incoming air flow is largely without resistance and without formation of near-surface flow edge vortex in the swirl space to form an axially extending to the burner swirl flow is deflected. In this way, any backflow zones which form in previously known premix burners with multi-shell arrangements can be avoided, in which gas accumulations can be formed, which can lead to damage to the premix burner structure and, in particular, to the burner shells by way of spontaneous deflagrations.
So weist eine jeweils lösungsgemäss ausgebildete Brennerschale drei unterschiedlich geformte Brennerschalenabschnitte auf, die einstückig miteinander verbunden sind, wobei der jeweils teilkegelförmig ausgebildete erste Brennerschalenabschnitt bündig mit einem entgegengesetzt zum ersten Brennerschalenabschnitt gekrümmten zweiten Brennerschalenabschnitt ergänzt ist und sich ein dritter Brennerschalenabschnitt an den zweiten Brennerschalenabschnitt bündig anschließt, mit einer sich an den zweiten Brennerschalenabschnitt tangential angleichenden Krümmung. Der dritte Brennerschalenabschnitt begrenzt dabei einseitig jeweils einen der tangentialen Lufteintrittschlitze und sieht eine für die Verbrennungszuluft dienende Anströmkante vor. Hierbei geht die durch die Teilkegelform bestimmte Krümmung des teilkegelförmig ausgebildeten ersten Brennerschalenabschnittes stetig, d.h. übergangslos, in die Krümmung des zweiten Brennerschalenabschnittes über und alle Orte eines Krümmungswechsels beschreiben eine Linie, die so genannte Wendepunktslinie, längs der die Mittel zur Brennstoffeinspeisung vorgesehen sind.Thus, a burner shell designed in each case according to the invention has three burner shell sections of different shape, which are connected in one piece with each other, wherein the respective first conical cup section is flush with one opposite the first Burner cup portion curved second burner cup portion is added and a third burner cup portion is flush with the second burner cup portion, with a tangent to the second burner cup portion curvature. The third burner shell section limits one side of each one of the tangential air inlet slots and provides a leading edge for the combustion air supply. Here, the determined by the partial cone shape curvature of the partially conical first burner shell section is continuous, ie transitionless, in the curvature of the second Brennerschalenabschnittes and all places of a curvature change describe a line, the so-called inflection point line along which the means are provided for fuel injection.
Vorzugsweise lässt sich eine derart ausgebildete Brennerschale im Rahmen eines Giessvorganges oder im Wege eines Umform- oder Materialabtragevorganges herstellen. Zur Vereinfachung der weiteren Beschreibung wird auf die Darstellung eines Ausführungsbeispieles unter Bezugnahme auf die nachstehenden Figuren verwiesen.Preferably, such a trained burner shell can be produced in the context of a casting process or by way of a forming or material removal process. To simplify the further description, reference is made to the representation of an embodiment with reference to the following figures.
Die Erfindung wird nachstehend ohne Beschränkung des allgemeinen Erfindungsgedankens anhand von Ausführungsbeispielen unter Bezugnahme auf die Zeichnung exemplarisch beschrieben. Es zeigen:
- Fig. 1
- schematisierte perspektivische Darstellung einer lösungsgemäss ausgebildeten Brennerschale,
- Fig. 2
- Detaildarstellung eines Teilbereiches des viertelelliptisch ausgeformten Brennerschalenbereiches mit angrenzendem tangential erweiterten dreiecksförmig ausgebildeten Brennerschalenbereich,
- Fig. 3
- 3D-Darstellung einer lösungsgemäss ausgebildeten Brennerschale,
- Fig. 4
- Darstellung einer lösungsgemäss ausgebildeten Brennerschale in Erstreckung längs zur Brennerschale, sowie
- Fig. 5
- 3D-Darstellung eines Drallerzeugers mit Mehrschalenanordnung.
- Fig. 1
- schematic perspective view of a solution according to trained burner shell,
- Fig. 2
- Detailed representation of a partial region of the quarter-elliptically shaped burner shell region with adjoining tangentially extended triangular-shaped burner shell region,
- Fig. 3
- 3D representation of a burner shell designed in accordance with the invention,
- Fig. 4
- Representation of a burner shell formed in accordance with the invention in extension along the burner shell, as well as
- Fig. 5
- 3D representation of a swirl generator with multi-shell arrangement.
In
In lösungsgemässer Weiterbildung der bis anhin im Einsatz befindlichen Brennerschale mit der durch den ersten Brennerschalenabschnitt 1 vorgegebenen Form, sieht die lösungsgemässe Brennerschale zwei weitere Brennerschalenabschnitte 8, 9 vor, die sich nahtlos und einstückig an die durch den Linienzug 5 angedeuteten linienhaften Endbereich des ersten, teilkegelförmig ausgebildeten Brennerschalenabschnittes 1 anschliessen. Der unmittelbar an den ersten Brennerschalenabschnitt 1 anschliessende zweite Brennerschalenabschnitt 8 weist eine Krümmung auf, die entgegengesetzt zur Krümmung des ersten teilkegelförmig ausgebildeten Brennerschalenabschnittes 1 orientiert ist. Aus der graphischen Darstellung des Ausführungsbeispiels gemäss
Alternativ zur der in
Des Weiteren schliesst sich an die virtuell verlaufende Begrenzungslinie 11 des zweiten Brennerschalenabschnittes 8 der dritte Brennerschalenabschnitt bündig an, der eine sich an den zweiten Brennerabschnitt tangential angleichende Krümmung vorsieht. Der dritte Brennerschalenabschnitt 9 weist im Wesentlichen eine dreiecksförmig ausgebildete Grundform auf mit einer vorderen Begrenzungskante 12, die zugleich auch als Anströmkante der lösungsgemäss ausgebildeten Brennerschale dient.Furthermore, the third burner shell section, which adjoins the virtually extending
Im Wesentlichen handelt es sich somit bei der in
Da das Krümmungsverhalten des ersten Brennerabschnittes entgegengesetzt zu jenem der jeweils zweiten und dritten Brennerschalenabschnitte orientiert ist, verläuft längs der virtuell durch die komplex geformte Brennerschale verlaufende Linie 5 ein stetiger, d.h. übergangsloser Wechsel des Krümmungsverhaltens der Brennerschalenoberfläche, so dass die Gesamtheit aller längs der Linie 5 angeordneten Orte jeweils Wendepunkte darstellen und der Linienzug 5 somit Wendepunktslinie aufgefasst werden kann.Since the curvature behavior of the first burner section is oriented opposite to that of the respective second and third burner shell sections, along the
Die in
Am Krümmungsverlauf der obersten Seitenkante der Brennerschale ist das Krümmungsverhalten der jeweiligen Brennerschalenabschnitte 1, 8 und 9 zu entnehmen. Der Wechsel der konkaven Krümmung des ersten Brennerschalenabschnittes 1 zur konvex ausgebildeten Krümmung des zweiten Brennerabschnittes 8 sowie der sich daran mit gleicher Krümmung anschliessenden dritten Brennerschalenabschnittes 9 erfolgt längs des Linienzuges 5, der, wie vorstehend erwähnt, als Wendepunktslinie aufzufassen ist. Der dritte Brennerschalenabschnitt 9 schliesst am oberen Ende der Brennerschale unter einem spitzen Winkel an den zweiten Brennerabschnitt 8 an und erweitert im Wesentlichen die Krümmung des zweiten Brennerschalenabschnittes 8 am Ort der Übergangslinie 11 in tangentialer Fortsetzung. Ebenso der Detaildarstellung in
In
Eine durch den Strömungspfeil stilisiert dargestellte radial auf die Anströmkante 12 der Brennerschale auftreffende Luftströmung L wird im Bereich des dritten und zweiten Brennerabschnittes 9, 8 in Strömungsrichtung beschleunigt und im weiteren durch den teilkegelförmig ausgebildeten ersten Brennerschalenabschnitt 1 sukzessive umgelenkt, bis die Strömung L die Brennerschale über den Brennerschalenabschnitt 1 hin zum Brennerraum bzw. Drallraum verlässt. Am Bereich der grössten Strömungsgeschwindigkeit, der sich im Bereich der Wendepunktslinie 5 einstellt, wird gasförmiger Brennstoff durch die Öffnungen 13 dem Luftstrom L zugegeben, wodurch sich bereits in diesem Strömungsbereich eine effektive Durchmischung von Brennstoff und Luft ergibt.A stylized by the flow arrow radially incident on the leading
Die lösungsgemässe Brennerschalengeometrie vermeidet somit jegliche Rückströmzonen innerhalb der Luftströmung längs der der Luftströmung L zugewandten Fläche der Brennerschale.The burner shell geometry according to the solution thus avoids any backflow zones within the air flow along the surface of the burner shell facing the air flow L.
Die Brennerschalengeometrie ist überdies derart ausgelegt, dass die Herstellung der Brennerschalen ohne Spezialwerkzeuge, beispielsweise ohne spezielle Pressformwerkzeuge möglich ist. So ist die Schalengeometrie stets durch eine Schar von Geraden beschreibbar, die axial bzw. in Längserstreckung der Brennerschale orientiert sind, wodurch die Brennerschale mittels einer CNC-Biegemaschine herstellbar ist.The burner shell geometry is also designed such that the manufacture of the burner shells is possible without special tools, for example without special press-forming tools. Thus, the shell geometry is always described by a family of straight lines, which are oriented axially or in the longitudinal extent of the burner shell, whereby the burner shell can be produced by means of a CNC bending machine.
In
- 11
- erster Brennerschalenabschnittfirst burner shell section
- 22
- Kegelsegmentcone segment
- 33
- Manteloberflächecoat surface
- 44
- Abströmkantetrailing edge
- 55
- Linienzug, WendepunktsliniePolyline, Turning Point Line
- 6,76.7
- obere und untere Seitenkante des ersten Brennerschalenabschnittesupper and lower side edge of the first burner cup section
- 88th
- zweiter Brennerschalenabschnittsecond burner shell section
- 99
- dritter Brennerschalenabschnittthird burner cup section
- 1010
- prismatischer Hilfskörper mit viertelelliptischer OberflächePrismatic auxiliary body with a quarter-elliptical surface
- 1111
- Trennlinieparting line
- 1212
- Anströmkanteleading edge
- 1313
- Öffnungopening
- 1414
- Brennstoffleitungfuel line
- 1515
- Tragstruktursupporting structure
- 1616
- Formelementforming element
- BB
- Brennerschaleburner shell
- LL
- Luftströmungairflow
- LSLS
- LufteintrittsschlitzAir inlet slot
Claims (11)
- Premix burner for producing an ignitable fuel/air mixture, comprising a swirl generator which provides at least two burner shells (B) which complement one another to form a throughflow body, which in each case have a first burner shell section (1) designed in a partial cone shape and together enclose an axially conically widening swirl space and which mutually define in the axial cone longitudinal extension tangential air inlet slots (LS), through which the combustion feed air (L) passes into the swirl space, in which an axially spreading swirl flow forms, and comprising means for spraying fuel which are arranged at least in sections along the tangentially running air inlet slots (LS), a second burner shell section (8) curved in opposition to the first burner shell section (1) in each case designed in a partial cone shape being added in a flush manner to said first burner shell section (1), and a third burner shell section (9) adjoining the second burner shell section (8) in a flush manner, said third burner shell section (9) having a curvature tangentially adapted to the second burner shell section (8), and the third burner shell section (9) defining on the one side in each case one of the tangential air inlet slots (LS) and providing a leading edge (12) serving for the combustion feed air (L), and the curvature, determined by the partial cone shape of the first burner shell section (1) designed in a partial cone shape merging continuously, i.e. smoothly, into the curvature of the second burner shell section (8), and all the locations of a change of curvature describing a line, the "turning point line" (5), characterized in that the means for the fuel feed (14) are provided along the turning point line (5).
- Premix burner according to Claim 1, characterized in that the third burner shell section (9) is of essentially triangular design and closely joins the second burner shell section (8) in the region of the smallest partial cone circumference of the first burner shell section (1) at an acute angle.
- Premix burner according to Claim 2, characterized in that the third burner shell section (9) has a longest triangle side which is connected in one piece to the second burner shell section (8), in that the third burner shell section (9) has a shortest triangle side which closely joins a shaped element (16) in a flush manner, said shaped element (16) enclosing all the burner shells (B) at the downstream end region of the swirl generator, and in that a third triangle side is provided which forms the leading edge (12).
- Premix burner according to one of Claims 1 to 3, characterized in that the burner shell consists a single- or multi-layer surface material.
- Premix burner according to Claim 4, characterized in that the surface material is a metallic material, preferably steel, which can be processed by a bending operation.
- Premix burner according to one of Claims 1 to 5, characterized in that the second and third burner shell sections (8, 9) form a convexly curved surface which faces the air inlet slot (LS) and merges continuously into a surface of concave design which faces the swirl space and is formed by the first burner shell section (1).
- Premix burner according to one of Claims 1 to 6, characterized in that, if n burner shells (B) enclosing the swirl space are provided, the respective first burner shell section corresponds to one nth of a complete cone shell.
- Device according to one of Claims 1 to 7, characterized in that the second burner shell section (8) closely joins a tangentially running surface line (5) of the first burner shell section (1) in a flush manner, and the third burner shell section (9) closely joins a tangentially running edge contour (11).
- Device according to one of Claims 1 to 8, characterized in that the second burner shell section (8) has a curvature and a shape which can be described by a quarter ellipse segment.
- Device according to one of Claims 1 to 8, characterized in that the second burner shell segment (8) has a curvature and a shape which can be described by a quarter circle segment.
- Device according to one of Claims 1 to 10, characterized in that the shape of all three burner shell sections (1, 8, 9) joined in one piece can be described by a system of straight lines running in the longitudinal direction of the burner shell.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH4092005 | 2005-03-09 | ||
PCT/EP2006/060437 WO2006094939A1 (en) | 2005-03-09 | 2006-03-03 | Burner comprising a premix for combustion chamber |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1856447A1 EP1856447A1 (en) | 2007-11-21 |
EP1856447B1 true EP1856447B1 (en) | 2014-09-24 |
Family
ID=34974801
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP06708627.2A Not-in-force EP1856447B1 (en) | 2005-03-09 | 2006-03-03 | Burner comprising a premix for combustion chamber |
Country Status (5)
Country | Link |
---|---|
US (1) | US7632091B2 (en) |
EP (1) | EP1856447B1 (en) |
CN (1) | CN101137869A (en) |
AR (1) | AR052687A1 (en) |
WO (1) | WO2006094939A1 (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
EP1985924A1 (en) * | 2007-04-23 | 2008-10-29 | Siemens Aktiengesellschaft | Swirler |
EP2154428A1 (en) * | 2008-08-11 | 2010-02-17 | Siemens Aktiengesellschaft | Fuel nozzle insert |
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 |
EP2685160B1 (en) * | 2012-07-10 | 2018-02-21 | Ansaldo Energia Switzerland AG | Premix burner of the multi-cone type for a gas turbine |
CN104471317B (en) * | 2012-08-06 | 2016-09-07 | 西门子公司 | Air in the burner with the eddy flow maker with overlapping blades end in perimeter and the local improvement of fuel mixing |
EP2703721B1 (en) | 2012-08-31 | 2019-05-22 | Ansaldo Energia IP UK Limited | Premix burner |
EP2796789B1 (en) * | 2013-04-26 | 2017-03-01 | General Electric Technology GmbH | Can combustor for a can-annular combustor arrangement in a gas turbine |
US10782017B2 (en) | 2018-04-24 | 2020-09-22 | Trane International Inc. | Wing vaned flame shaper |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3217781A (en) * | 1963-04-05 | 1965-11-16 | Armco Steel Corp | Gas mixer for blast furnace stoves |
US4136565A (en) * | 1978-04-20 | 1979-01-30 | Eaton Corporation | Variable geometry fluid flowmeter |
EP0210462B1 (en) | 1985-07-30 | 1989-03-15 | BBC Brown Boveri AG | Dual combustor |
CH674561A5 (en) | 1987-12-21 | 1990-06-15 | Bbc Brown Boveri & Cie | |
CH680946A5 (en) * | 1989-12-19 | 1992-12-15 | Asea Brown Boveri | |
US5161946A (en) * | 1990-12-03 | 1992-11-10 | Industrial Technology Research Institute | Swirl generator with axial vanes |
DE4223828A1 (en) | 1992-05-27 | 1993-12-02 | Asea Brown Boveri | Method for operating a combustion chamber of a gas turbine |
DE4412315B4 (en) | 1994-04-11 | 2005-12-15 | Alstom | Method and device for operating the combustion chamber of a gas turbine |
US5479773A (en) * | 1994-10-13 | 1996-01-02 | United Technologies Corporation | Tangential air entry fuel nozzle |
DE19516798A1 (en) * | 1995-05-08 | 1996-11-14 | Abb Management Ag | Premix burner with axial or radial air flow |
DE19654008B4 (en) * | 1996-12-21 | 2006-08-10 | Alstom | burner |
ATE244380T1 (en) * | 1997-11-21 | 2003-07-15 | Alstom | BURNER FOR OPERATION OF A HEAT GENERATOR |
DE19859829A1 (en) * | 1998-12-23 | 2000-06-29 | Abb Alstom Power Ch Ag | Burner for operating a heat generator |
EP1714081B1 (en) * | 2004-02-12 | 2008-04-09 | Alstom Technology Ltd | Premixing burner arrangement for operating a burner chamber and method for operating a burner chamber |
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 |
-
2006
- 2006-03-03 CN CNA2006800072624A patent/CN101137869A/en active Pending
- 2006-03-03 WO PCT/EP2006/060437 patent/WO2006094939A1/en not_active Application Discontinuation
- 2006-03-03 EP EP06708627.2A patent/EP1856447B1/en not_active Not-in-force
- 2006-03-09 AR ARP060100894A patent/AR052687A1/en unknown
-
2007
- 2007-09-06 US US11/850,849 patent/US7632091B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20080070176A1 (en) | 2008-03-20 |
CN101137869A (en) | 2008-03-05 |
US7632091B2 (en) | 2009-12-15 |
AR052687A1 (en) | 2007-03-28 |
WO2006094939A1 (en) | 2006-09-14 |
EP1856447A1 (en) | 2007-11-21 |
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