EP0845639A1 - Combustor - Google Patents

Combustor Download PDF

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Publication number
EP0845639A1
EP0845639A1 EP97810817A EP97810817A EP0845639A1 EP 0845639 A1 EP0845639 A1 EP 0845639A1 EP 97810817 A EP97810817 A EP 97810817A EP 97810817 A EP97810817 A EP 97810817A EP 0845639 A1 EP0845639 A1 EP 0845639A1
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EP
European Patent Office
Prior art keywords
combustion chamber
cross
sectional constriction
stage
chamber according
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Granted
Application number
EP97810817A
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German (de)
French (fr)
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EP0845639B1 (en
Inventor
Oliver Christian Dr. Paschereit
Wolfgang Dr. Polifke
Thomas Dr. Sattelmayer
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General Electric Technology GmbH
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ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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Publication of EP0845639A1 publication Critical patent/EP0845639A1/en
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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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a combustion chamber according to Preamble of claim 1.
  • Helmholtz resonators in themselves are a significant reduction of pressure pulsations with vibrations close to the design frequency cause must not be misunderstood that in addition to the disadvantage of the necessary space for such a facility also the effect on the environment the design frequency is limited.
  • the invention seeks to remedy this.
  • the invention how it is characterized in the claims, the task lies based on a combustion chamber of the type mentioned propose a configuration that reflects the reflection of Pressure pulsations at the end of the combustion chamber minimized.
  • the main advantage of the invention is that that due to the low-reflection design of the combustion chamber end the feedback of the pressure pulsations on the burner, which lead to renewed fluctuations in heat release and so that pressure pulsations can cause is prevented.
  • the basic idea of the invention is based on the idea that low-frequency vibrations are significantly absorbed, if it passes through a nozzle followed by a free jet be transmitted.
  • the invention a combustion chamber with two in the flow direction downstream stages.
  • Arranged burner which can be of any design can.
  • premix burners for further consideration premix burners based on.
  • Fuel and combustion air react within the first stage with each other.
  • the size of this first Step must be dimensioned so that before reaching it Output in the direction of flow the heat from the combustion process is largely released.
  • the CO burnout must on the other hand, not be completed.
  • This for its part must be dimensioned so that the CO content on the desired value drops before the working gases then and impeller blades of a downstream turbine.
  • the transition is one of two stages existing combustion chamber, between the first and second Step formed with a cross-sectional constriction, at which the low frequency vibrations are absorbed by this due to the narrowing called the contraction of the nozzle is trained, then transmitted with a free jet will.
  • the acoustic energy is transformed into the energy of the fluctuating vortex strength transferred at the nozzle outlet. This Eventually energy is dissipated into heat.
  • the combustion chamber is switched by more than two sequentially Steps are formed, so are the respective transitions of the individual stages in terms of cross-sectional narrowing or Nozzle contraction according to the two levels specified here To interpret principles.
  • the only figure shows one designed as an annular combustion chamber Combustion chamber, which consists of two stages, being intermediate a nozzle contraction acts between the two.
  • the figure shows how this results from the shaft axis 60 and rotary motion 61 of the rotor, not shown, shows that it is an annular combustion chamber in the present case essentially the shape of a coherent annular or has quasi-annular cylinder.
  • a such combustion chamber also from a number axially, quasi-axially or helically arranged and individually self-contained Combustion chambers exist.
  • the combustion chamber also consist of a single tube.
  • the one shown in the figure Annular combustion chamber consists of a first stage 20 and a second downstream stage 40. intermediate between a cross-sectional constriction 30 acts on the two stages 20, 40, which will be discussed in more detail below.
  • the first Stage 20 initially has a number on the head side in the circumferential direction side-by-side premix burner 10 whose design and function from EP-0 321 809 B1 emerges, this document integrating component present description is.
  • Another premix burner which is also predestined to be used here arrive, emerges from EP-0 704 657 A2, whereby this too Document integral part of this description is.
  • the mixture formation taking place in the burner 10 forms between an air stream 12 and a fuel 10 that combustion mixture that in the first stage 20 to Hot gases 21 is burned. After flowing through the already cross-sectional constriction 30 mentioned flow the hot gases 21st then to the second stage 40, in which the final burnout takes place before the working gases 41 formed there finally act on a downstream turbine 50.
  • the design of the cross-sectional constriction 30 is permitted by the Pressure loss coefficient and the requirements for that Flow field defined. A nozzle shape is also possible minimized pressure loss coefficient or an orifice with a or more holes.
  • Crucial for the design of the Cross-sectional constriction 30 is, however, the area ratio contraction in the direction of flow. A minimal reflection is reached when the Mach number at outlet 31 of the cross-sectional constriction 30 equal to the area ratio of the cross-sectional constriction 30, this area ratio being made up of the quotient between exit area A2 divided by the Entry area A1 of the cross-sectional constriction 30 is determined becomes. This specification ensures that there is sufficient progress the nozzle contraction reaches a minimal reflection, i.e.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

The chamber comprises a cross-sectional narrowing (30) in the flow direction which enables the transition of the hot gases (21) between the first stage (20) and the succeeding stage (40). The cross-sectional narrowing has a structure with the Mach number at the outlet (31) being equal to the surface ratio of the narrowing. The surface ratio is a quotient of the outlet surface (A2) over the inlet surface (A1). The axial length (L) of the cross-sectional narrowing is 5% greater than the diameter at the inlet surface. The combustion chamber is of the ring type and is operable with at least one pre-mix burner (10).

Description

Technisches GebietTechnical field

Die vorliegende Erfindung betrifft eine Brennkammer gemäss Oberbegriff des Anspruchs 1.The present invention relates to a combustion chamber according to Preamble of claim 1.

Stand der TechnikState of the art

Die Wärmefreisetzung beim Betrieb von Brennkammern, insbesondere bei Vormischverbrennungen, verursacht Druckpulsationen, deren Schädlichkeit dem Fachmann bestens bekannt ist. Hiergegen sind bereits verschiedene Vorschläge bekanntgeworden, welche dahin zielen, die Reflexion von durch die Wärmefreisetzung verursachten Druckpulsationen an den Brennkammerenden zu verhindern. In diesem Zusammenhang werden oft Helmholtz-Resonatoren eingesetzt.The heat release during the operation of combustion chambers, in particular with premix burns, causes pressure pulsations, the harmfulness of which is well known to the person skilled in the art. Against this various proposals have already become known, which aim at the reflection of through the heat release caused pressure pulsations at the combustion chamber ends to prevent. In this context, Helmholtz resonators are often used used.

Obwohl Helmholtz-Resonatoren an sich eine signifikante Verminderung von Druckpulsationen bei Schwingungen nahe der Auslegungsfrequenz bewirken, darf nicht verkannt werden, dass neben dem Nachteil der dafür notwendigen Platzverhältnisse für eine solche Einrichtung auch die Wirkung auf die Umgebung der Auslegungsfrequenz beschränkt ist. Although Helmholtz resonators in themselves are a significant reduction of pressure pulsations with vibrations close to the design frequency cause must not be misunderstood that in addition to the disadvantage of the necessary space for such a facility also the effect on the environment the design frequency is limited.

Insbesondere bei kompakten Ringbrennkammern ist eine solche Einrichtung aus Platzgründen schwer einsetzbar, so dass taugliche Massnahmen zur Verhinderung von thermodynamischen Schwingungen bei Brennkammern der neueren Generation nach wie vor fehlen, resp. noch nicht in tauglicher Form vorgeschlagen worden sind.Such is particularly the case with compact annular combustion chambers Furniture difficult to use due to lack of space, so that suitable Measures to prevent thermodynamic Vibrations in combustion chambers of the newer generation continue before missing, respectively. not yet suggested in suitable form have been.

Darstellung der ErfindungPresentation of the invention

Hier will die Erfindung Abhilfe schaffen. Der Erfindung, wie sie in den Ansprüchen gekennzeichnet ist, liegt die Aufgabe zugrunde, bei einer Brennkammer der eingangs genannten Art eine Ausgestaltung vorzuschlagen, welche die Reflexion von Druckpulsationen am Brennkammerende minimiert.The invention seeks to remedy this. The invention how it is characterized in the claims, the task lies based on a combustion chamber of the type mentioned propose a configuration that reflects the reflection of Pressure pulsations at the end of the combustion chamber minimized.

Der wesentliche Vorteil der Erfindung ist darin zu sehen, dass durch die reflexionsarme Ausgestaltung des Brennkammerendes die Rückkopplung der Druckpulsationen auf den Brenner, welche zu erneuten Schwankungen in der Wärmefreisetzung und damit Druckpulsationern führen können, unterbunden wird.The main advantage of the invention is that that due to the low-reflection design of the combustion chamber end the feedback of the pressure pulsations on the burner, which lead to renewed fluctuations in heat release and so that pressure pulsations can cause is prevented.

Der Grundgedanke der Erfindung basiert auf der Idee, dass niederfrequente Schwingungen signifikant absorbiert werden, wenn sie durch eine Düse mit anschliessendem Freistrahl transmittiert werden.The basic idea of the invention is based on the idea that low-frequency vibrations are significantly absorbed, if it passes through a nozzle followed by a free jet be transmitted.

Aus akustischen Gründen ergibt die Umsetzung des Grundgedankes der Erfindung eine Brennkammer mit zwei in Strömungsrichtung nachgeschalteten Stufen. Am Kopf der ersten Stufe sind Brenner angeordnet, die an sich von beliebiger Bauform sein können. Im Zuge der Tatsache, dass Brennkammern der neueren Generation zur Minimierung der Schadstoff-Emissionen vorzugsweise mit einer Vormischverbrennung betrieben werden, sind hier für die weitere Betrachtung Vormischbrenner zugrundegelegt. Brennstoff und Verbrennungsluft reagieren innerhalb der ersten Stufe miteinander. Die Grösse dieser ersten Stufe muss so dimensioniert sein, dass vor Erreichen deren Ausgang in Strömungsrichtung die Wärme aus dem Verbrennungsprozess weitgehend freigesetzt ist. Der CO-Ausbrand muss dagegen nicht abgeschlossen sein. Die Reaktionsprodukte aus der Verbrennung innerhalb der ersten Stufe durchströmen dann deren Ausgang, welcher erfindungsgemäss nach den nachfolgenden geschilderten Kriterien ausgelegt ist, und gelangen dann in die zweite Stufe, welche als Ausbrandzone operiert. Diese muss ihrerseits so dimensioniert sein, dass der CO-Gehalt auf den Wunschwert abfällt, bevor die Arbeitsgase dann die Leit- und Laufschaufeln einer nachgeschalteten Turbine beaufschlagen.The implementation of the basic idea results for acoustic reasons the invention a combustion chamber with two in the flow direction downstream stages. At the top of the first stage Arranged burner, which can be of any design can. In the wake of the fact that combustion chambers are newer Generation to minimize pollutant emissions preferred are operated with a premix combustion here for further consideration premix burners based on. Fuel and combustion air react within the first stage with each other. The size of this first Step must be dimensioned so that before reaching it Output in the direction of flow the heat from the combustion process is largely released. The CO burnout must on the other hand, not be completed. The reaction products from then flow through the combustion within the first stage their output, which according to the invention according to the following described criteria is designed, and then arrive to the second stage, which operates as a burnout zone. This for its part must be dimensioned so that the CO content on the desired value drops before the working gases then and impeller blades of a downstream turbine.

Erfindungsgemäss wird der Uebergang, bei einer aus zwei Stufen bestehenden Brennkammer, zwischen der ersten und zweiten Stufe mit einer Querschnittsverengung gebildet, bei welcher die niederfrequenten Schwingungen absorbiert werden, indem diese durch die genannte Verengung, die als Düsenkontraktion ausgebildet ist, mit anschliessendem Freistrahl transmittiert werden. Somit wird die akustische Energie in die Energie der fluktuierenden Wirbelstärke am Düsenaustritt überführt. Diese Energie wird schliesslich in Wärme dissipiert.According to the invention, the transition is one of two stages existing combustion chamber, between the first and second Step formed with a cross-sectional constriction, at which the low frequency vibrations are absorbed by this due to the narrowing called the contraction of the nozzle is trained, then transmitted with a free jet will. Thus the acoustic energy is transformed into the energy of the fluctuating vortex strength transferred at the nozzle outlet. This Eventually energy is dissipated into heat.

Wird die Brennkammer durch mehr als zwei sequentiell geschaltete Stufen gebildet, so sind die jeweiligen Uebergänge der einzelnen Stufen hinsichtlich der Querschnittsverengung resp. Düsenkontraktion nach den hier für zwei Stufen festgelegten Grundsätzen auszulegen.The combustion chamber is switched by more than two sequentially Steps are formed, so are the respective transitions of the individual stages in terms of cross-sectional narrowing or Nozzle contraction according to the two levels specified here To interpret principles.

Ein weiterer wesentlicher Vorteil bei der Umsetzung der Erfindung ist darin zu sehen, dass die Konfiguration der Querschnittsverengung resp. Düsenkontraktion entsprechend den vorgegebenen Brennkammerverhältnissen immer zu einer minimalen Reflektion angepasst werden kann, ohne damit die Auslegung der Brennkammer zu verändern. Diese endseitige Kontraktion der ersten Stufe werden vorzugsweise als Düse mit minimalen Druckverlustbeiwert oder als Blende mit einer oder mehreren Offnungen ausgelegt. Der Querschnittsverlauf der Kontraktion in Strömungsrichtung ist hingegen erfindungsgemäss recht gut eingegrenzt: das Flächenverhältnis zwischen Austritt und Eintritt der Kontraktion entspricht der Machzahl am Düsenaustritt. Um welches Flächenverhältnis es sich hier handelt, wird weiter unten näher dargelegt.Another significant advantage in implementing the invention can be seen in the fact that the configuration of the cross-sectional constriction resp. Nozzle contraction according to the given combustion chamber conditions always to a minimum Reflection can be adjusted without changing the Change the design of the combustion chamber. This contraction at the end the first stage are preferably used as a nozzle minimal pressure loss coefficient or as an orifice with one or designed several openings. The cross section of the Contraction in the direction of flow, however, is according to the invention quite well defined: the area ratio between The exit and entry of the contraction correspond to the Mach number at the nozzle outlet. What is the area ratio here is discussed in more detail below.

Vorteilhafte und zweckmässige Weiterbildungen der erfindungsgemässen Aufgabenlösung sind in den weiteren abhängigen Ansprüchen gekennzeichnet.Advantageous and expedient developments of the inventive Task solution are in the further dependent claims featured.

Im folgenden wird anhand der Zeichnung ein Ausführungsbeispiel der Erfindung näher erläutert. Alle für das unmittelbare Verständnis der Erfindung nicht erforderlichen Elemente sind fortgelassen. Die Strömungsrichtung der Medien ist mit Pfeilen angegeben.In the following, an embodiment is shown with reference to the drawing the invention explained in more detail. All for the immediate Understanding the invention does not require elements are omitted. The direction of flow of the media is with Arrows indicated.

Kurze Beschreibung der ZeichnungBrief description of the drawing

Die einzige Figur zeigt eine als Ringbrennkammer konzipierte Brennkammer, die aus zwei Stufen besteht, wobei intermediär zwischen den beiden eine Düsenkontraktion wirkt.The only figure shows one designed as an annular combustion chamber Combustion chamber, which consists of two stages, being intermediate a nozzle contraction acts between the two.

Wege zur Ausführung der Erfindung, gewerbliche VerwendbarkeitWAYS OF CARRYING OUT THE INVENTION, INDUSTRIAL APPLICABILITY

Die Figur zeigt, wie dies aus der Wellenachse 60 und Drehbewegung 61 des nicht näher gezeigten Rotors hervorgeht, dass es sich vorliegend um eine Ringbrennkammer handelt, welche im wesentlichen die Form eines zusammenhängenden annularen oder quasi-annularen Zylinders aufweist. Darüber hinaus kann eine solche Brennkammer auch aus einer Anzahl axial, quasi-axial oder schraubenförmig angeordneter und einzeln in sich abgeschlossener Brennräume bestehen. An sich kann die Brennkammer auch aus einem einzigen Rohr bestehen. Die in der Figur gezeigte Ringbrennkammer besteht aus einer ersten Stufe 20 und einer zweiten nachgeschalteten Stufe 40. Intermediär zwischen den beiden Stufen 20, 40 wirkt eine Querschnittsverengung 30, auf welche weiter unten noch näher eingegangen wird. Die erste Stufe 20 weist zunächst kopfseitig eine Anzahl in Umfangsrichtung nebeneinander angeordneter Vormischbrenner 10 auf, deren Ausgestaltung und Funktion aus EP-0 321 809 B1 hervorgeht, wobei diese Druckschrift integrierender Bestandteil vorliegender Beschreibung ist. Ein weiterer Vormischbrenner, der ebenfalls prädestiniert ist, hier zum Einsatz zu gelangen, geht aus EP-0 704 657 A2 hervor, wobei auch diese Druckschrift integrierender Bestandteil vorliegender Beschreibung ist. Die stattfindende Gemischbildung im Brenner 10 zwischen einem Luftstrom 12 und einem Brennstoff 10 bildet jenes Verbrennungsgemisch, das in der ersten Stufe 20 zu Heissgasen 21 verbrannt wird. Nach Durchströmung der bereits genannten Querschnittsverengung 30 strömen die Heissgase 21 dann in die zweite Stufe 40, in welcher der endgültige Ausbrand stattfindet, bevor die dort gebildete Arbeitsgase 41 schliesslich eine nachgeschaltete Turbine 50 beaufschlagen.The figure shows how this results from the shaft axis 60 and rotary motion 61 of the rotor, not shown, shows that it is an annular combustion chamber in the present case essentially the shape of a coherent annular or has quasi-annular cylinder. In addition, a such combustion chamber also from a number axially, quasi-axially or helically arranged and individually self-contained Combustion chambers exist. In itself, the combustion chamber also consist of a single tube. The one shown in the figure Annular combustion chamber consists of a first stage 20 and a second downstream stage 40. intermediate between a cross-sectional constriction 30 acts on the two stages 20, 40, which will be discussed in more detail below. The first Stage 20 initially has a number on the head side in the circumferential direction side-by-side premix burner 10 whose design and function from EP-0 321 809 B1 emerges, this document integrating component present description is. Another premix burner, which is also predestined to be used here arrive, emerges from EP-0 704 657 A2, whereby this too Document integral part of this description is. The mixture formation taking place in the burner 10 forms between an air stream 12 and a fuel 10 that combustion mixture that in the first stage 20 to Hot gases 21 is burned. After flowing through the already cross-sectional constriction 30 mentioned flow the hot gases 21st then to the second stage 40, in which the final burnout takes place before the working gases 41 formed there finally act on a downstream turbine 50.

Die Gestaltung der Querschnittsverengung 30 ist durch den erlaubten Druckverlustbeiwert und die Anforderungen an das Strömungsfeld definiert. Möglich sind eine Düsenform mit minimiertem Druckverlustbeiwert oder eine Blende mit einem oder mehreren Löchern. Entscheidend für die Ausgestaltung der Querschnittsverengung 30 ist indessen das Flächenverhältnis der Kontraktion in Strömungsrichtung. Eine minimale Reflexion wird erreicht, wenn die Machzahl am Austritt 31 der Querschnittsverengung 30 gleich dem Flächenverhältnis der Querschnittsverengung 30 ist, wobei dieses Flächenverhältnis aus dem Quotient zwischen Austrittsfläche A2 dividiert durch die Eintrittsfläche A1 der Querschnittsverengung 30 ermittelt wird. Durch diese Vorgabe wird bei einem ausreichenden Verlauf der Düsenkontraktion eine minimale Reflexion erreicht, d.h., die dort auftretende akustische Energie wird in die Energie der fluktuierenden Wirbelstärke am Austritt 31 der Querschnittsverengung 30 überführt, wobei diese Energie schliesslich in Wärme dissipiert. Allein durch diese geometrische Ausgestaltung der Querschnittsverengung 30 ergibt eine Impedanz Z / ρc = 1, welche ein typisches reflexionsfreies Ende am Austritt 31 der Querschnittsverengung 30 induziert. Typische Werte für die Aufenthaltszeiten der Heissgase 21, 41 betragen für die erste Stufe 5-20 ms, für die zweite Stufe 10-50 ms.The design of the cross-sectional constriction 30 is permitted by the Pressure loss coefficient and the requirements for that Flow field defined. A nozzle shape is also possible minimized pressure loss coefficient or an orifice with a or more holes. Crucial for the design of the Cross-sectional constriction 30 is, however, the area ratio contraction in the direction of flow. A minimal reflection is reached when the Mach number at outlet 31 of the cross-sectional constriction 30 equal to the area ratio of the cross-sectional constriction 30, this area ratio being made up of the quotient between exit area A2 divided by the Entry area A1 of the cross-sectional constriction 30 is determined becomes. This specification ensures that there is sufficient progress the nozzle contraction reaches a minimal reflection, i.e. the acoustic energy occurring there is converted into energy the fluctuating vortex strength at the outlet 31 of the Cross-sectional constriction 30 transferred, this energy finally dissipated in heat. This geometric alone Design of the cross-sectional constriction 30 results an impedance Z / ρc = 1, which is a typical reflection-free End induced at the exit 31 of the cross-sectional constriction 30. Typical values for the residence times of the hot gases 21, 41 are 5-20 ms for the first stage and for the second stage 10-50 ms.

BezugszeichenlisteReference list

1010th
VormischbrennerPremix burner
1111
Brennstofffuel
1212th
LuftstromAirflow
2020th
Erste StufeFirst stage
2121
HeissgaseHot gases
3030th
QuerschnittsverengungCross-sectional narrowing
3131
Austritt der QuerschnittsverengungExit of the cross-sectional constriction
4040
Zweite StufeSecond step
4141
ArbeitsgaseWorking gases
5050
Turbineturbine
6060
Wellenachse des RotorsShaft axis of the rotor
6161
DrehbewegungRotary motion
A1A1
Eintrittsfläche der DüsenkontraktionEntry area of the nozzle contraction
A2A2
Austrittsfläche der DüsenkontraktionExit area of the nozzle contraction
LL
Axiale Länge der DüsenkontraktionAxial length of the nozzle contraction

Claims (8)

Brennkammer, im wesentlichen bestehend einer ersten Stufe und mindestens einer nachgeschalteten zweiten Stufe, wobei in diesen Stufen sequentiell die Aufbereitung der Heissgase zur Beaufschlagung einer der Brennkammer nachgeschalteten Turbine vonstatten geht, dadurch gekennzeichnet, dass der Uebergang der Heissgase (21) zwischen der vorangehenden Stufe (20) und der nachgeschalteten Stufe (40) durch eine in Strömungsrichtung angeordnete Querschnittsverengung (30) gebildet ist.Combustion chamber, consisting essentially of a first Stage and at least one downstream second Stage, in which stages the processing is sequential the hot gases for loading one of the combustion chambers downstream turbine takes place, thereby characterized that the transition of the hot gases (21) between the previous stage (20) and the downstream one Stage (40) through a in the direction of flow arranged cross-sectional constriction (30) is formed. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Querschnittsverengung (30) einen Aufbau aufweist, bei welchem die Machzahl am Austritt (31) der Querschnittsverengung (30) gleich dem Flächenverhältnis der Querschnittsverengung (30) entspricht, welches Flächenverhältnis ein Quotient aus Austrittsfläche (A2) über Eintrittsfläche (A1) ist.Combustion chamber according to claim 1, characterized in that the cross-sectional constriction (30) has a structure, at which the Mach number at the exit (31) of the Cross-sectional constriction (30) equal to the area ratio the cross-sectional constriction (30) corresponds to which area ratio a quotient from the exit area (A2) over entrance area (A1). Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die axiale Länge (L) der Querschnittsverengung (30) grösser 5% des Durchmessers an der Eintrittsfläche (A1) ist.Combustion chamber according to claim 1, characterized in that the axial length (L) of the cross-sectional constriction (30) greater than 5% of the diameter at the entry surface (A1) is. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Brennkammer eine Ringbrennkammer ist.Combustion chamber according to claim 1, characterized in that the combustion chamber is an annular combustion chamber. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Brennkammer mit mindestens einem Vormischbrenner (10) betreibbar ist. Combustion chamber according to claim 1, characterized in that the combustion chamber with at least one premix burner (10) is operable. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Querschnittsverengung (30) eine Düsenform aufweist.Combustion chamber according to claim 1, characterized in that the cross-sectional constriction (30) has a nozzle shape. Brennkammer nach Anspruch 6, dadurch gekennzeichnet, dass die Düsenform einen minimalen Druckverlustbeiwert aufweist.Combustion chamber according to claim 6, characterized in that the nozzle shape has a minimal pressure loss coefficient having. Brennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Querschnittsverengung (30) eine Blende mit einem oder mehreren Löchern ist.Combustion chamber according to claim 1, characterized in that the cross-sectional constriction (30) has an aperture with a or more holes.
EP97810817A 1996-11-29 1997-10-31 Combustor and method of operation Expired - Lifetime EP0845639B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19649486 1996-11-29
DE19649486A DE19649486A1 (en) 1996-11-29 1996-11-29 Combustion chamber

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EP0845639A1 true EP0845639A1 (en) 1998-06-03
EP0845639B1 EP0845639B1 (en) 2003-10-01

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EP97810817A Expired - Lifetime EP0845639B1 (en) 1996-11-29 1997-10-31 Combustor and method of operation

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US6010334A (en) * 1996-10-30 2000-01-04 Tokai Corporation Combustion appliance for liquid fuel
EP0985877A1 (en) * 1998-09-10 2000-03-15 Abb Research Ltd. Device and method for minimizing thermoacoustic oscillations in gas turbine combustion chambers
US6113385A (en) * 1996-10-24 2000-09-05 Tokai Corporation Combustion wick for liquid fuel combustion appliances

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DE59810760D1 (en) * 1998-12-15 2004-03-18 Krasnojarskij Politekhn I Kras Combustion chamber with acoustically damped fuel supply system
EP2236926B1 (en) 2009-03-17 2015-07-29 Siemens Aktiengesellschaft Temperature measuring device, gas turbine with same and method for directly determining the temperature in a combustion chamber
US8484980B1 (en) 2009-11-19 2013-07-16 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Dual-mode combustor

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US6113385A (en) * 1996-10-24 2000-09-05 Tokai Corporation Combustion wick for liquid fuel combustion appliances
US6010334A (en) * 1996-10-30 2000-01-04 Tokai Corporation Combustion appliance for liquid fuel
EP0985877A1 (en) * 1998-09-10 2000-03-15 Abb Research Ltd. Device and method for minimizing thermoacoustic oscillations in gas turbine combustion chambers

Also Published As

Publication number Publication date
US6050078A (en) 2000-04-18
DE59710802D1 (en) 2003-11-06
EP0845639B1 (en) 2003-10-01
JPH10169986A (en) 1998-06-26
DE19649486A1 (en) 1998-06-04

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