EP0252315A1 - Combustion chamber device with a precombustion chamber for an understoichiometric combustion - Google Patents

Combustion chamber device with a precombustion chamber for an understoichiometric combustion Download PDF

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Publication number
EP0252315A1
EP0252315A1 EP87108265A EP87108265A EP0252315A1 EP 0252315 A1 EP0252315 A1 EP 0252315A1 EP 87108265 A EP87108265 A EP 87108265A EP 87108265 A EP87108265 A EP 87108265A EP 0252315 A1 EP0252315 A1 EP 0252315A1
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EP
European Patent Office
Prior art keywords
combustion
housing
fuel
combustion chamber
air
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Granted
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EP87108265A
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German (de)
French (fr)
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EP0252315B1 (en
Inventor
Jakob Dr. Keller
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BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • 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
    • F23C7/02—Disposition of air supply not passing through burner

Definitions

  • the present invention relates to a combustion chamber device with a pre-combustion chamber for substoichiometric combustion, the combustion mixture which is incompletely burned in a housing of the pre-combustion chamber being completely burned in a post-combustion chamber with a large excess of air.
  • this disadvantage is to be avoided in that, by means of a special design of the pre-combustion chamber by means of an air and fuel layer, its wall is shielded from the ignited combustion mixture and the temperature near the wall is thereby reduced to values which are permissible for the material of the combustion chamber walls are.
  • the pre-combustion chamber according to the invention for substoichiometric combustion is characterized in that the housing of the pre-combustion chamber is essentially a rotating body which is formed by rotating a heart-shaped generator with a cut tip about its axis of symmetry or about an axis of rotation parallel to this axis of symmetry and lying outside the generator by cutting off the tip of the heart during the rotation of the generators, a circular-cylindrical or circular-cylindrical outlet duct results in a combustion air duct extending over the boundary of this outlet duct, the outlet openings of which are arranged along the aforementioned boundary of the outlet duct in such a way that the combustion air in the edge region of the outlet channel can flow into the housing at a tangent to the inner boundary, such that injection nozzles for a liquid fuel are present, the axes of the nozzles being oriented such that the fuel jets shield the combustion air flowing into the housing from the ignited combustion mixture, and that means for supplying additional air into the pre
  • the injection nozzles are arranged at the end of injection lines, which branch off from a fuel ring line surrounding the outlet duct and open directly radially inward of the outlet opening of the combustion air duct into the housing, the axes of the injection nozzles being essentially parallel to the tangent to the respective are directed adjacent wall part of the housing, and wherein for the supply of additional air, an annular additional air channel arranged at the end of the outlet channel is present.
  • the injection nozzles are arranged at the end of a fuel line which opens into the housing coaxially with the axis of symmetry thereof, the axes of the injection nozzles being directed in such a way that the fuel jets shield the combustion air blown into the housing from the ignited fuel mixture, and where the additional air is taken from the combustion air intended for the afterburning chamber.
  • the housing 2 of the pre-combustion chamber 1 shown schematically in FIG. 1 shows the shape of a heart with a cut-off tip in an axial section through the axis of rotation of the rotary body. In their place, the housing ends in an outlet channel 3 for the incompletely burned fuel mixture generated in the housing 2.
  • a fuel ring line 4 for the liquid fuel is provided in the lower part of the housing 2 at a distance from the same. This passes from a fuel tank (not shown) via a feed line 5 into the ring line 4. From this ring line, a number branches off, uniformly distributed over the circumference, hook-shaped curved injection lines 6, which end within the outlet channel 3 in injection nozzles 7, from which fuel jets 8 are approximately parallel emerge towards the inner surface of the housing 2. Radially inward of the injection lines 6 is a rotation Body-shaped baffle 9 which, together with the outer surface of the housing 2, defines an annular combustion air duct 10 in its lower part. The flow arrows 11 symbolize the combustion air, which is preheated in the channel 10 and, after a deflection at the lower end of the housing 2, flows upward approximately parallel to the housing wall and mixes with the fuel jet 8.
  • Another rotationally symmetrical baffle plate 12 which surrounds the injection lines 6, delimits with the first-mentioned baffle plate 9 an annular additional air duct 13 through which air, represented by the flow arrows 14, is admixed to the preburned fuel mixture in the region of the outlet duct 3 in a stoichiometric ratio.
  • This mixture then arrives in a post-combustion chamber 16, part of the housing of which is shown, for complete combustion.
  • the mechanism of shielding the wall of the housing 2 against the high combustion temperatures that occur during the substoichiometric pre-combustion is based on the tangential injection of the combustion air that takes place over the entire inner circumference of the housing 2, which creates a vortex ring with a toroidal vortex core 15, the Cross section in Fig. 1 is symbolized by the two circles with dashed double hatching.
  • this vortex core contains very hot gases, the centrifugal effect causing a stratification of the combustion gases of different temperatures or densities, which can only slowly balance out from the inside out.
  • Such a compensation of the temperature or density from the inside out is, however, in stationary operation suppressed by the constantly supplied fuel / air mixture.
  • the vortex core 15 also acts as an ignition source, by means of which the substoichiometric fuel / air mixture is ignited.
  • Fuel injection radially inward of the combustion air layer close to the wall isolates it from the core of the incompletely burned combustion mixture to approximately the lower half of the housing 2, so that the latter cannot continue to burn with air from the layer close to the wall and only becomes ignitable again after additional air has been mixed in from the additional air duct 13 , whereby it can be completely burned in the afterburning chamber 16.
  • the speed of the air injection into the pre-combustion chamber 1 should be significantly higher than the flame propagation speed, which creates a spiral flame front, which ideally does not hit the inner surface of the housing 2. At the time of ignition, the mixing process has progressed so far that lean mixture zones no longer occur.
  • Fig. 2 shows a pre-combustion chamber 17 of a simplified design, in which the liquid fuel through a Axis of symmetry of the housing 18 coaxial fuel line 19 is fed to the injection nozzles 20 arranged at the end thereof. While the air for the pre-combustion is blown into the housing 18 close to the wall from below, as in the embodiment according to FIG. 1, the fuel is injected in the opposite direction from above at high speed.
  • the nozzle axes are oriented in such a way that the air jets near the wall are also shielded from the burning mixture ignited in the center.
  • Such a pre-combustion chamber 17 can advantageously be combined with gas burners arranged uniformly distributed over the circumference, two of which are shown in FIG.
  • the fuel gas flowing in through the gas burner is indicated by the arrows 22, the combustion air by the arrows 23.
  • the combustion air flow is dimensioned such that it is sufficient at least for the complete combustion of the gas and for the post-combustion of the incompletely burned combustion mixture flowing out of the pre-combustion chamber in the after-combustion chamber 24.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

The precombustion chamber (1), in which liquid fuel is combusted understoichiometrically, is arranged upstream of a secondary combustion chamber (16), in which complete combustion takes place overstoichiometrically. The understoichiometric combustion air volume (11) for the precombustion chamber (2) is blown in close to the wall from the outlet channel (3) upwards into the housing (2), which is heart-shaped in axial section. The injection nozzles (7) for the fuel are arranged in such a way that the fuel jets (8) shield the layer of combustion air close to the wall from the partially combusted fuel mixture flowing over it through the outlet channel (3) into the secondary combustion chamber (16). At the end of the outlet channel (3), the additional air volume required for complete combustion in the secondary combustion chamber (16) is mixed in with the partially combusted fuel mixture. <IMAGE>

Description

Die vorliegende Erfindung betrifft eine Brennkammerein­richtung mit einer Vorbrennkammer für unterstöchiometri­sche Verbrennung, wobei das in einem Gehäuse der Vor­brennkammer unvollständig verbrannte Brenngemisch in einer Nachbrennkammer mit grossem Luftüberschuss voll­ständig verbrannt wird.The present invention relates to a combustion chamber device with a pre-combustion chamber for substoichiometric combustion, the combustion mixture which is incompletely burned in a housing of the pre-combustion chamber being completely burned in a post-combustion chamber with a large excess of air.

Stand der TechnikState of the art

Bei hohen Temperaturen ablaufende Verbrennungsvorgänge verursachen unzulässig hohe NOx-Emissionen, deren Ver­meidung bzw. Verringerung heutzutage aus Gründen des Umweltschutzes in gewissen Ländern behördlicherseits vorgeschrieben wird. Davon betroffen sind hauptsächlich industrielle Feuerungsanlagen und insbesondere auch Gas­turbinen. Für letztere sind bei Gasfeuerungen daher Vor­mischbrenner entwickelt worden. Diese Technik der Vor­mischverbrennung ist die aussichtsreichste Methode für eine namhafte Verringerung der NOx-Bildung bei gasförmi­gen Brennstoffen.Combustion processes taking place at high temperatures cause impermissibly high NO x emissions, the avoidance or reduction of which is now mandatory by the authorities in certain countries for reasons of environmental protection. This mainly affects industrial combustion plants and especially gas turbines. Premix burners have therefore been developed for the latter in gas firing systems. This premix combustion technique is the most promising method for a significant reduction in NO x formation in gaseous fuels.

Für flüssige Brennstoffe ist diese Technik wegen der kurzen Zündverzugszeiten - bei hohem Druck tritt eine Dieselzündung auf - praktisch nicht anwendbar. Für eine schadstoffarme Verbrennung flüssiger Brennstoffe mussten daher andere Möglichkeiten gefunden werden. Ein aussichts­reiches Verfahren scheint darin zu bestehen, dass man die Verbrennung in zwei Phasen ablaufen lässt. Bei dieser sogenannten Zweistufenverbrennung wird der Brennstoff in einer Vorbrennkammer bei unterstöchiometrischen Ge­mischbedingungen vorverbrannt, z.B. bei einer Luftzahl λ= 0,7. Bei einer solchen, stark unterstöchiometrischen Verbrennung entsteht nur sehr wenig NOx, wogegen bei einem annähernd stöchiometrischen Gemisch, d.h., mit λ in der Nähe von 1, sehr viel NOx gebildet wird. Bei Ver­brennungsvorgängen mit λ > > 1, also mit grossem Luftüber­schuss und entsprechend kühler Flamme, entsteht ebenfalls nur wenig NOx.For liquid fuels, this technology is practically not applicable due to the short ignition delay times - diesel ignition occurs at high pressure. Therefore, other options had to be found for low-pollutant combustion of liquid fuels. A promising process seems to be that the combustion is carried out in two phases. In this so-called two-stage combustion, the fuel is pre-burned in a pre-combustion chamber under substoichiometric mixture conditions, for example with an air ratio λ = 0.7. With such a strongly sub-stoichiometric combustion, very little NO x is produced , whereas with an approximately stoichiometric mixture, ie with λ in the vicinity of 1, a large amount of NO x is formed. In combustion processes with λ>> 1, i.e. with a large excess of air and a correspondingly cool flame, there is also only little NO x .

Die bei der Bildung von NOx beteiligten Reaktionen laufen relativ langsam ab, so dass eine hohe Produktionsrate von NOx, die bei λ = 1 auftritt, durch sehr rasche Zu­mischung von Luft in das am Ende der Vorbrennkammer aus­strömende Gemisch aus Verbrennungsgasen und noch unver­branntem Brennstoff vermieden werden kann. Das dadurch gebildete überstöchiometrische Brennstoff/Luft-Gemisch mit λ > > 1 wird dann in einer zweiten Brennkammer nach­verbrannt. Die damit angestrebte Reduktion der NOx-Bil­dung durch eine solche zweistufige Verbrennung hat sich experimentell bestätigt, siehe hiezu den Aufsatz von R.E.Johns "Gasturbine Engines Emissions-Problems, Progress and Future" in der Zeitschrift "Progr. Energy Combust. Sci.", Vol. IV, 1978, pp. 73-113. Bei der praktischen Anwendung dieser Idee tritt jedoch die Schwierigkeit auf, dass die Vorverbrennung extrem hohe Temperaturen mit entsprechend sehr hoher Erhitzung der Vorbrennkammer­wände erzeugt. Die bei normalen Brennkammern üblichen Kühlmethoden, wie Filmkühlung und Konvektionskühlung, sind für solche Vorbrennkammern ungeeignet, weil die dabei in das Brenngemisch gelangende Kühlluft die Luft­zahl in den nahestöchiometrischen Bereich bringt, was wiederum zu stärkerer NOx-Bildung führt, die ja aber durch die unvollständige Vorverbrennung verringert wer­den soll.The reactions involved in the formation of NO x take place relatively slowly, so that a high production rate of NO x , which occurs at λ = 1, due to the very rapid admixture of air into the mixture of combustion gases and still unburned fuel flowing out at the end of the pre-combustion chamber can be avoided. The resulting over-stoichiometric fuel / air mixture with λ>> 1 is then burned in a second combustion chamber. The desired reduction in NO x formation through such a two-stage combustion has been confirmed experimentally, see the article by REJohns "Gas Turbine Engines Emissions Problems, Progress and Future" in the journal "Progr. Energy Combust. Sci.", Vol IV, 1978, pp. 73-113. In the practical application of this idea, however, there arises a problem that the pre-combustion is extremely high temperature generated with a correspondingly very high heating of the pre-combustion chamber walls. The usual cooling methods for normal combustion chambers, such as film cooling and convection cooling, are unsuitable for such pre-combustion chambers because the cooling air that enters the combustion mixture brings the air ratio into the near-stoichiometric range, which in turn leads to stronger NO x formation, which, however, is due to the incomplete Pre-combustion should be reduced.

Darstellung der ErfindungPresentation of the invention

Mit der vorliegenden Erfindung soll dieser Nachteil ver­mieden werden, indem durch eine spezielle Gestaltung der Vorbrennkammer durch eine Luft- und Brennstoffschicht eine Abschirmung ihrer Wandung gegenüber dem entzündeten Brenngemisch erreicht und dadurch die Temperatur in Wand­nähe auf Werte reduziert wird, die für den Werkstoff der Brennkammerwände zulässig sind.With the present invention, this disadvantage is to be avoided in that, by means of a special design of the pre-combustion chamber by means of an air and fuel layer, its wall is shielded from the ignited combustion mixture and the temperature near the wall is thereby reduced to values which are permissible for the material of the combustion chamber walls are.

Die erfindungsgemässe Vorbrennkammer für unterstöchio­metrische Verbrennung ist dadurch gekennzeichnet, dass das Gehäuse der Vorbrennkammer im wesentlichen ein Rota­tionskörper ist, der durch Drehung einer herzförmigen Erzeugenden mit abgeschnittener Spitze um ihre Symmetrie­achse oder um eine zu dieser Symmetrieachse parallele und ausserhalb der Erzeugenden liegende Drehachse ge­bildet wird, wobei sich durch das Abschneiden der Herz­spitze bei der Drehung der Erzeugenden ein kreiszylindri­scher oder kreisringzylindrischer Austrittskanal ergibt, dass ein sich über die Berandung dieses Austritts­kanals erstreckender Verbrennungsluftkanal vorhanden ist, dessen Austrittsöffnungen längs der genannten Be­randung des Austrittskanals so angeordnet sind, dass die Verbrennungsluft im Randbereich des Austrittskanals tangential zur inneren Begrenzung des Gehäuses in dieses einströmen kann, dass Einspritzdüsen für einen flüssigen Brennstoff vorhanden sind, wobei die Achsen der Düsen derart orientiert sind, dass die Brennstoffstrahlen die in das Gehäuse einströmende Verbrennungsluft gegenüber dem entzündeten Brenngemisch abschirmt, und dass Mittel zur Zufuhr von Zusatzluft in das vorverbrannte Brenn­gemisch nach dessen Austritt aus dem Austrittskanal vor­handen sind.The pre-combustion chamber according to the invention for substoichiometric combustion is characterized in that the housing of the pre-combustion chamber is essentially a rotating body which is formed by rotating a heart-shaped generator with a cut tip about its axis of symmetry or about an axis of rotation parallel to this axis of symmetry and lying outside the generator by cutting off the tip of the heart during the rotation of the generators, a circular-cylindrical or circular-cylindrical outlet duct results in a combustion air duct extending over the boundary of this outlet duct, the outlet openings of which are arranged along the aforementioned boundary of the outlet duct in such a way that the combustion air in the edge region of the outlet channel can flow into the housing at a tangent to the inner boundary, such that injection nozzles for a liquid fuel are present, the axes of the nozzles being oriented such that the fuel jets shield the combustion air flowing into the housing from the ignited combustion mixture, and that means for supplying additional air into the pre-combusted fuel mixture are present after it has emerged from the outlet duct.

Bei einer bevorzugten Ausführungsform einer solchen Brenn­kammereinrichtung sind die Einspritzdüsen am Ende von Einspritzleitungen angeordnet, welche von einer den Aus­trittskanal umgebenden Brennstoffringleitung abzweigen und unmittelbar radial einwärts der Austrittsöffnung des Verbrennungsluftkanals in das Gehäuse einmünden, wobei die Achsen der Einspritzdüsen im wesentlichen pa­rallel zur Tangente an den jeweils benachbarten Wandteil des Gehäuses gerichtet sind, und wobei für die Zufuhr von Zusatzluft ein am Ende des Austrittskanals angeord­neter, ringförmiger Zusatzluftkanal vorhanden ist.In a preferred embodiment of such a combustion chamber device, the injection nozzles are arranged at the end of injection lines, which branch off from a fuel ring line surrounding the outlet duct and open directly radially inward of the outlet opening of the combustion air duct into the housing, the axes of the injection nozzles being essentially parallel to the tangent to the respective are directed adjacent wall part of the housing, and wherein for the supply of additional air, an annular additional air channel arranged at the end of the outlet channel is present.

Bei einer baulich einfacheren Ausführung sind die Ein­spritzdüsen am Ende einer Brennstoffleitung angeordnet, die koaxial zur Symmetrieachse des Gehäuses in dieses einmündet, wobei die Achsen der Einspritzdüsen so ge­richtet sind, dass die Brennstoffstrahlen die in das Gehäuse eingeblasene Verbrennungsluft gegenüber dem ent­zündeten Brenngemisch abschirmen, und wobei die Zusatz­luft der für die Nachbrennkammer bestimmten Verbrennungs­luft entnommen wird.In a structurally simpler embodiment, the injection nozzles are arranged at the end of a fuel line which opens into the housing coaxially with the axis of symmetry thereof, the axes of the injection nozzles being directed in such a way that the fuel jets shield the combustion air blown into the housing from the ignited fuel mixture, and where the additional air is taken from the combustion air intended for the afterburning chamber.

Kurze Beschreibung der ZeichnungenBrief description of the drawings

Im folgenden wird die Erfindung anhand von in den Zeich­nungen dargestellten Ausführungsformen näher erläutert. Es zeigen:

  • Fig. 1 schematisch eine Vorbrennkammer mit einer am Austrittskanal angeordneten Ringleitung für die Brennstoffzuführung, und die
  • Fig. 2 ebenfalls schematisch eine erfindungsgemässe Brennkammereinrichtung mit einer Vorbrennkammer mit zentraler Brennstoffeinspritzung und einer für Gasbetrieb eingerichteten Nachbrennkammer.
The invention is explained in more detail below with reference to embodiments shown in the drawings. Show it:
  • Fig. 1 shows schematically a pre-combustion chamber with a ring line arranged on the outlet channel for the fuel supply, and the
  • Fig. 2 also schematically shows a combustion chamber device according to the invention with a pre-combustion chamber with central fuel injection and an after-combustion chamber set up for gas operation.

Wege zur Ausführung der ErfindungWays of Carrying Out the Invention

Das Gehäuse 2 der in Fig. 1 schematisch dargestellten Vorbrennkammer 1 zeigt in einem durch die Drehachse des Rotationskörpers gelegten Axialschnitt die Form eines Herzens mit abgeschnittener Spitze. An deren Stelle endet das Gehäuse in einem Austrittskanal 3 für das im Gehäuse 2 erzeugte, unvollständig verbrannte Brenngemisch.The housing 2 of the pre-combustion chamber 1 shown schematically in FIG. 1 shows the shape of a heart with a cut-off tip in an axial section through the axis of rotation of the rotary body. In their place, the housing ends in an outlet channel 3 for the incompletely burned fuel mixture generated in the housing 2.

Im unteren Teil des Gehäuses 2 ist mit einem Abstand zu demselben eine Brennstoffringleitung 4 für den flüssi­gen Brennstoff vorgesehen. Dieser gelangt aus einem nicht dargestellten Brennstofftank über eine Zuführleitung 5 in die Ringleitung 4. Von dieser Ringleitung zweigt eine Anzahl gleichmässig über den Umfang verteilter, haken­förmig gekrümmter Einspritzleitungen 6 ab, die innerhalb des Austrittskanals 3 in Einspritzdüsen 7 enden, aus denen Brennstoffstrahlen 8 annähernd parallel zur Innen­fläche des Gehäuses 2 austreten. Radial einwärts der Einspritzleitungen 6 befindet sich ein als Rotations­ körper ausgebildetes Leitblech 9, das zusammen mit der Aussenfläche des Gehäuses 2 in dessen unterem Teil einen ringförmigen Verbrennungsluftkanal 10 begrenzt. Die Strö­mungspfeile 11 versinnbildlichen die Verbrennungsluft, die im Kanal 10 vorgewärmt wird und nach einer Umlenkung am unteren Ende des Gehäuses 2 innerhalb desselben etwa parallel zur Gehäusewand nach oben strömt und sich mit dem Brennstoffstrahl 8 vermischt.A fuel ring line 4 for the liquid fuel is provided in the lower part of the housing 2 at a distance from the same. This passes from a fuel tank (not shown) via a feed line 5 into the ring line 4. From this ring line, a number branches off, uniformly distributed over the circumference, hook-shaped curved injection lines 6, which end within the outlet channel 3 in injection nozzles 7, from which fuel jets 8 are approximately parallel emerge towards the inner surface of the housing 2. Radially inward of the injection lines 6 is a rotation Body-shaped baffle 9 which, together with the outer surface of the housing 2, defines an annular combustion air duct 10 in its lower part. The flow arrows 11 symbolize the combustion air, which is preheated in the channel 10 and, after a deflection at the lower end of the housing 2, flows upward approximately parallel to the housing wall and mixes with the fuel jet 8.

Ein weiteres rotationssymmetrisches Leitblech 12, das die Einspritzleitungen 6 umschliesst, begrenzt mit dem erstgenannten Leitblech 9 einen ringförmigen Zusatzluft­kanal 13, durch den dem vorverbrannten Brenngemisch im Bereich des Austrittskanals 3 Luft, dargestellt durch die Strömungspfeile 14, in überstöchiometrischem Verhält­nis zugemischt wird. Dieses Gemisch gelangt dann in einer Nachbrennkammer 16, von der ein Teil des Gehäuses dar­gestellt ist, zur vollständigen Verbrennung.Another rotationally symmetrical baffle plate 12, which surrounds the injection lines 6, delimits with the first-mentioned baffle plate 9 an annular additional air duct 13 through which air, represented by the flow arrows 14, is admixed to the preburned fuel mixture in the region of the outlet duct 3 in a stoichiometric ratio. This mixture then arrives in a post-combustion chamber 16, part of the housing of which is shown, for complete combustion.

Der Mechanismus der Abschirmung der Wand des Gehäuses 2 gegen die hohen Verbrennungstemperaturen, die bei der unterstöchiometrischen Vorverbrennung auftreten, beruht auf der über den ganzen inneren Umfang des Gehäuses 2 stattfindenden, tangentialen Einblasung der Verbrennungs­luft, die einen Wirbelring erzeugt mit einem torusför­migen Wirbelkern 15, dessen Querschnitt in Fig. 1 durch die beiden Kreise mit strichlierter Doppelschraffur sym­bolisiert wird. Dieser Wirbelkern enthält bei gezündetem Brennstoff sehr heisse Gase, wobei die Zentrifugalwir­kung eine Schichtung der Verbrennungsgase von unterschied­licher Temperatur bzw. Dichte verursacht, die sich nur sehr langsam von innen nach aussen ausgleichen können. Ein solcher Ausgleich der Temperatur bzw. Dichte von innen nach aussen wird jedoch im stationären Betrieb durch das ständig nachgelieferte Brennstoff/Luft-Gemisch unterdrückt. Es findet also eine stationäre Selbstab­schirmung statt, die den Gehäusewerkstoff vor unzulässi­ger Ueberhitzung schützt. Der Wirbelkern 15 wirkt im stationären Betrieb auch als Zündquelle, durch die das unterstöchiometrische Brennstoff/Luft-Gemisch entflammt wird. Durch Brennstoffeinspritzung radial einwärts der wandnahen Verbrennungsluftschicht wird diese etwa bis zur unteren Hälfte des Gehäuses 2 vom Kern des unvoll­ständig verbrannten Brenngemisches isoliert, so dass letzteres nicht mit Luft aus der wandnahen Schicht weiter­brennen kann und erst nach Zumischung von Zusatzluft aus dem Zusatzluftkanal 13 wieder zündfähig wird, wo­durch es in der Nachbrennkammer 16 vollständig verbrannt werden kann.The mechanism of shielding the wall of the housing 2 against the high combustion temperatures that occur during the substoichiometric pre-combustion is based on the tangential injection of the combustion air that takes place over the entire inner circumference of the housing 2, which creates a vortex ring with a toroidal vortex core 15, the Cross section in Fig. 1 is symbolized by the two circles with dashed double hatching. When the fuel is ignited, this vortex core contains very hot gases, the centrifugal effect causing a stratification of the combustion gases of different temperatures or densities, which can only slowly balance out from the inside out. Such a compensation of the temperature or density from the inside out is, however, in stationary operation suppressed by the constantly supplied fuel / air mixture. So there is a stationary self-shielding, which protects the housing material against unacceptable overheating. In stationary operation, the vortex core 15 also acts as an ignition source, by means of which the substoichiometric fuel / air mixture is ignited. Fuel injection radially inward of the combustion air layer close to the wall isolates it from the core of the incompletely burned combustion mixture to approximately the lower half of the housing 2, so that the latter cannot continue to burn with air from the layer close to the wall and only becomes ignitable again after additional air has been mixed in from the additional air duct 13 , whereby it can be completely burned in the afterburning chamber 16.

Die Geschwindigkeit der Lufteinblasung in die Vorbrenn­kammer 1 soll wesentlich höher sein als die Flammenaus­breitungsgeschwindigkeit, was eine spiralförmige Flammen­front erzeugt, die im Idealfall nicht auf die Innenfläche des Gehäuses 2 trifft. Zum Zeitpunkt der Zündung ist der Mischvorgang bereits so weit fortgeschritten, dass keine mageren Gemischzonen mehr auftreten.The speed of the air injection into the pre-combustion chamber 1 should be significantly higher than the flame propagation speed, which creates a spiral flame front, which ideally does not hit the inner surface of the housing 2. At the time of ignition, the mixing process has progressed so far that lean mixture zones no longer occur.

Wie bereits oben erwähnt, wird dem nur teilweise ver­brannten Brenngemisch im Bereich des Austrittskanals 3 aus dem Zusatzluftkanal 13 soviel Luft zugemischt, dass die vollständige Verbrennung in einer Nachbrennkammer stark überstöchiometrisch mit λ > > 1 stattfinden kann. In den so verdünnten Abgasen ist dadurch eine NOx-Bil­dung weitgehend unterdrückt.As already mentioned above, so much air is mixed into the only partially burned combustion mixture in the area of the outlet duct 3 from the additional air duct 13 that the complete combustion can take place in a post-combustion chamber in a highly stoichiometric manner with λ>> 1. NO x formation is largely suppressed in the exhaust gases thus diluted.

Die Fig. 2 zeigt eine Vorbrennkammer 17 vereinfachter Bauart, bei der der flüssige Brennstoff durch eine zur Symmetrieachse des Gehäuses 18 koaxiale Brennstofflei­tung 19 den am Ende derselben angeordneten Einspritz­düsen 20 zugeführt wird. Während die Luft für die Vor­verbrennung gleich wie bei der Ausführung nach Fig. 1 von unten her wandnah in das Gehäuse 18 eingeblasen wird, erfolgt die Brennstoffeinspritzung in umgekehrter Rich­tung von oben her mit grosser Geschwindigkeit. Die Düsen­achsen sind dabei so gerichtet, dass ebenfalls eine Ab­schirmung der wandnahen Luftstrahlen gegen das im Zentrum entflammte Brenngemisch stattfindet. Eine solche Vor­brennkammer 17 kann vorteilhaft mit über den Umfang gleich­mässig verteilt angeordneten Gasbrennern kombiniert wer­den, von denen in Fig. 2 zwei mit 21 bezeichnete darge­stellt sind. Das durch die Gasbrenner zuströmende Brenn­gas ist dabei durch die Pfeile 22, die Verbrennungsluft durch die Pfeile 23 angedeutet. Der Verbrennungsluft­strom ist so bemessen, dass er mindestens zur vollständi­gen Verbrennung des Gases und zur Nachverbrennung des aus der Vorbrennkammer ausströmenden, unvollständig ver­brannten Brenngemisches in der Nachbrennkammer 24 genügt.Fig. 2 shows a pre-combustion chamber 17 of a simplified design, in which the liquid fuel through a Axis of symmetry of the housing 18 coaxial fuel line 19 is fed to the injection nozzles 20 arranged at the end thereof. While the air for the pre-combustion is blown into the housing 18 close to the wall from below, as in the embodiment according to FIG. 1, the fuel is injected in the opposite direction from above at high speed. The nozzle axes are oriented in such a way that the air jets near the wall are also shielded from the burning mixture ignited in the center. Such a pre-combustion chamber 17 can advantageously be combined with gas burners arranged uniformly distributed over the circumference, two of which are shown in FIG. The fuel gas flowing in through the gas burner is indicated by the arrows 22, the combustion air by the arrows 23. The combustion air flow is dimensioned such that it is sufficient at least for the complete combustion of the gas and for the post-combustion of the incompletely burned combustion mixture flowing out of the pre-combustion chamber in the after-combustion chamber 24.

Claims (3)

1. Brennkammereinrichtung mit einer Vorbrennkammer für unterstöchiometrische Verbrennung, wobei das in einem Gehäuse (2; 18) der Vorbrennkammer (1; 17) unvoll­ständig verbrannte Brenngemisch in einer Nachbrenn­kammer (16; 24) mit grossem Luftüberschuss vollständig verbrannt wird, dadurch gekennzeichnet, dass das Gehäuse (2, 18) der Vorbrennkammer (1; 17) im wesentlichen ein Rotationskörper ist, der durch Drehung einer herz­förmigen Erzeugenden mit abgeschnittener Spitze um ihre Symmetrieachse oder um eine zu dieser Symmetrie­achse parallele und ausserhalb der Erzeugenden lie­gende Drehachse gebildet wird, wobei sich durch das Abschneiden der Herzspitze bei der Drehung der Erzeu­genden ein kreiszylindrischer oder kreisringzylindri­scher Austrittskanal (3) ergibt, dass ein sich über die Berandung dieses Austrittskanals (3) erstrecken­der Verbrennungsluftkanal (10) vorhanden ist, dessen Austrittsöffnungen längs der genannten Berandung des Austrittskanals (3) so angeordnet sind, dass die Ver­brennungsluft im Randbereich des Austrittskanals (3) tangential zur inneren Begrenzung des Gehäuses (2; 18) in dieses einströmen kann, dass Einspritzdüsen (7; 20) für einen flüssigen Brennstoff vorhanden sind, wobei die Achsen der Düsen derart orientiert sind, dass die Brennstoffstrahlen die in das Gehäuse (2; 18) einströmende Verbrennungsluft gegenüber dem ent­zündeten Brenngemisch abschirmt, und dass Mittel zur Zufuhr von Zusatzluft in das vorverbrannte Brennge­misch nach dessen Austritt aus dem Austrittskanal (3) vorhanden sind.1. Combustion chamber device with a pre-combustion chamber for substoichiometric combustion, the combustion mixture which is incompletely burned in a housing (2; 18) of the pre-combustion chamber (1; 17) being completely burned in a post-combustion chamber (16; 24) with a large excess of air, characterized in that Housing (2, 18) of the pre-combustion chamber (1; 17) is essentially a rotary body which is formed by rotating a heart-shaped generator with a cut-off tip about its axis of symmetry or about an axis of rotation parallel to this axis of symmetry and lying outside the generator, whereby by cutting off the tip of the heart when the generatrix rotates a circular-cylindrical or circular-cylindrical outlet channel (3) shows that there is a combustion air channel (10) extending over the edge of this outlet channel (3), the outlet openings of which along the aforementioned edge of the outlet channel (3) are arranged that the combustion air in the edge region of the outlet channel (3) tangential to the inner boundary of the housing (2; 18) can flow into it that there are injection nozzles (7; 20) for a liquid fuel, the axes of the nozzles being oriented such that the fuel jets shield the combustion air flowing into the housing (2; 18) from the ignited fuel mixture, and that means for supplying additional air into the pre-combusted fuel mixture are present after it has left the outlet channel (3). 2. Brennkammereinrichtung nach Anspruch 1, dadurch ge­kennzeichnet, dass die Einspritzdüsen (7) am Ende von Einspritzleitungen (6) angeordnet sind, welche von einer den Austrittskanal (3) umgebenden Brenn­stoffringleitung (4) abzweigen und unmittelbar radial einwärts der Austrittsöffnung des Verbrennungsluft­kanals (10) in das Gehäuse (2) einmünden, dass die Achsen der Einspritzdüsen (7) im wesentlichen parallel zur Tangente an den jeweils benachbarten Wandteil des Gehäuses (2) gerichtet sind, und dass für die Zufuhr von Zusatzluft ein am Ende des Austrittskanals (3) angeordneter, ringförmiger Zusatzluftkanal (13) vorhanden ist.2. Combustion chamber device according to claim 1, characterized in that the injection nozzles (7) are arranged at the end of injection lines (6) which branch off from a fuel ring line (4) surrounding the outlet channel (3) and directly radially inward of the outlet opening of the combustion air channel (10 ) open into the housing (2), that the axes of the injection nozzles (7) are directed essentially parallel to the tangent to the respectively adjacent wall part of the housing (2), and that for the supply of additional air, an at the end of the outlet channel (3) arranged, annular auxiliary air duct (13) is present. 3. Brennkammereinrichtung nach Anspruch 1, dadurch ge­kennzeichnet, dass die Einspritzdüsen (20) am Ende einer Brennstoffleitung (19) angeordnet sind, die koaxial zur Symmetrieachse des Gehäuses (18) in dieses einmündet, dass die Achsen der Einspritzdüsen (20) so gerichtet sind, dass die Brennstoffstrahlen die in das Gehäuse (18) eingeblasene Verbrennungsluft gegenüber dem entzündeten Brenngemisch abschirmen, und dass die Zusatzluft der für die Nachbrennkammer (24) bestimmten Verbrennungsluft (23) entnommen wird.3. Combustion chamber device according to claim 1, characterized in that the injection nozzles (20) are arranged at the end of a fuel line (19) which opens coaxially to the axis of symmetry of the housing (18) in that the axes of the injection nozzles (20) are directed so that the fuel jets shield the combustion air blown into the housing (18) against the ignited combustion mixture, and that the additional air is taken from the combustion air (23) intended for the afterburning chamber (24).
EP87108265A 1986-07-08 1987-06-08 Combustion chamber device with a precombustion chamber for an understoichiometric combustion Expired - Lifetime EP0252315B1 (en)

Applications Claiming Priority (2)

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CH2748/86 1986-07-08
CH2748/86A CH671449A5 (en) 1986-07-08 1986-07-08

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CH671449A5 (en) 1989-08-31
EP0252315B1 (en) 1992-10-07
DE3782097D1 (en) 1992-11-12
US4894005A (en) 1990-01-16
JPS6325418A (en) 1988-02-02

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