EP1207350A2 - Combustor and method for operating the same - Google Patents

Combustor and method for operating the same Download PDF

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Publication number
EP1207350A2
EP1207350A2 EP01126841A EP01126841A EP1207350A2 EP 1207350 A2 EP1207350 A2 EP 1207350A2 EP 01126841 A EP01126841 A EP 01126841A EP 01126841 A EP01126841 A EP 01126841A EP 1207350 A2 EP1207350 A2 EP 1207350A2
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EP
European Patent Office
Prior art keywords
combustion chamber
fuel
mixing zone
supporting air
lance
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.)
Granted
Application number
EP01126841A
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German (de)
French (fr)
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EP1207350B1 (en
EP1207350A3 (en
Inventor
Marcel Stalder
Daniel Burri
Urs Benz
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General Electric Technology GmbH
Original Assignee
Alstom Schweiz AG
Alstom Power NV
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Application filed by Alstom Schweiz AG, Alstom Power NV filed Critical Alstom Schweiz AG
Publication of EP1207350A2 publication Critical patent/EP1207350A2/en
Publication of EP1207350A3 publication Critical patent/EP1207350A3/en
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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
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/62—Mixing devices; Mixing tubes
    • F23D14/64—Mixing devices; Mixing tubes with injectors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Definitions

  • the invention is a combustion chamber according to the Preamble of claim 4 or a method for operating the Combustion chamber according to the preamble of claim 1.
  • combustion chamber Ignition there is a combustion chamber Ignition known.
  • a Fuel lance fuel and supporting air introduced into a hot gas stream, mixed there and the mixture in a downstream Combustion zone burned.
  • the fuel lance is in one Mixing zone and is centrally located there. It is for about 10% of the Total volume flow through the channel dimensioned, the fuel can be injected transversely or in the direction of the flow.
  • the injected fuel is combined with a portion of supporting air several radial openings entrained by the vertebrae injected upstream and mixed with the main flow.
  • the injected fuel follows helical course of the vertebrae and is downstream in the chamber equally distributed. This reduces the risk of impact rays on the opposite channel wall as well as the formation of "hot spots", such as this is the case with an undisturbed flow.
  • the aim of this invention is to avoid the disadvantages mentioned.
  • the Invention solves the problem of a combustion chamber and a method of operation to create this combustion chamber with which it is possible to disrupt the To minimize hot gas flow in the mixing zone of the combustion chamber. This should happen with less cooling of the fuel lance and it should improve the behavior of the combustion chamber in all load ranges will achieve.
  • this is the case with a method according to the preamble of claim 1 achieved in that the fuel of at least one Side wall of the mixing zone of the combustion chamber is injected and it is at the combustion chamber according to the preamble of claim 4 thereby achieved that the at least one fuel lance in a side wall of the Mixing zone of the combustion chamber is embedded.
  • support air is also injected through this fuel lance.
  • An advantage of such a lateral, asymmetrical injection of the Fuel is in particular that only one through the fuel lance little flow disturbance is caused, which is this disturbance only on the side wall of the mixing zone and no longer centrally in the Main flow is located. It is also advantageous if at least a fuel lance in the form of a ball or one in Main flow direction extending ellipsoids in the side wall of the Combustion chamber is inserted and in the interior of the mixing zone Combustion chamber protrudes.
  • the mixing zone as a venturi channel or any additional internals (radial or circumferential) can increase the speed and thus improve it Mixing of hot gas and fuel / supporting air can be achieved. Trail areas behind the fuel lance, in which fuel can accumulate are practical due to this type of arrangement locked out.
  • the area of the seal between the sidewall of the Mixing zone and fuel lance is also advantageously small and in held advantageous shape.
  • An advantageous embodiment of the method according to the invention lies in that the fuel and any supporting air present in various fuel / supporting air mixture jets in the mixing zone of the Combustion chamber to be injected, the different Fuel / supporting air mixture jets in different directions or in different sectors directed within the mixing zone of the combustion chamber are.
  • This embodiment is particularly advantageous because depending on Utilization of the combustion chamber beams can be switched on or off.
  • This is also in combination with the internals mentioned above advantageous because with the targeted feeding of different sectors through the jets, the fuel at different pressures in different Areas within the mixing zone can be transported.
  • FIG. 1 shows a combustion chamber 1 according to the invention, which as one annular combustion chamber arranged around a shaft axis 9.
  • the Combustion chamber 1 consists of a vortex generator 14, a mixing zone 11 and from a combustion zone 12.
  • Such ring burner chambers are suitable very well in order to be operated as a self-igniting combustion chamber 1, the combustion chamber 1 then not between two, in the single figure shown turbines is placed.
  • the mixing zone 11, as shown in FIG. 1, is a venturi channel designed.
  • Another form of Cross section changes can be chosen as long as this is the improved Acceleration and mixing of fuel 4 and hot gases 5 is used.
  • the fuel lance 2 is in a side wall 6 of the Mixing zone 11 let in. The distribution of the fuel 3 and the supporting air 2 thus takes place asymmetrically with respect to the cross section of the mixing zone 11.
  • An advantage of such a lateral, asymmetrical injection of the Fuel 3 is in particular that the fuel lance 2 only one represents little disturbance of the flow, this disturbance merely being the side wall 6 of the mixing zone 11 and no longer centrally in the Main flow is located.
  • the Fuel lance 2 in the form of a ball or one in Main flow direction of the hot gas 5 extending ellipsoids in the Side wall 6 of the combustion chamber 1 embedded and protrudes into the interior of the Mixing zone 11 of the combustion chamber 1.
  • An advantageous embodiment of the method according to the invention lies in that the fuel 3 and any supporting air 4 in various fuel / supporting air mixture jets 7 into the mixing zone 11 the combustion chamber 1 are injected, the various Fuel / supporting air mixture jets 7 in different sectors or in different target spaces within the mixing zone 11 of the combustion chamber 1 are directed.
  • Figure 2 shows a section along the line II-II of the figure 1. There is the alignment of the rays 7 in different areas of the Mixing zone 11 clearly visible.
  • FIG. 3 also shows section III of FIG Figure 2 closer.
  • the supporting air 4 surrounds the fuel 3 in a jacket shape, the fuel jets as a plain jet be injected into the mixing zone. By choosing different Channels can use different types of fuel (gaseous / liquid) become.
  • Such an injection principle is in principle from the Publication EP-A1-1,030,109 known.
  • the use of different nozzle geometries is suitable for this purpose.
  • the embodiment of the beams 7 is therefore particularly advantageous since, depending on the load on the combustion chamber, beams 7 can be switched on or off. This means that the beams 7 are fed individually. Overall, the entire operating range can be increased from minimum to maximum fuel quantity. An improved part-load behavior is thus achieved, which has a positive effect with regard to pollutant behavior, i.e. formation of CO, NO x , UHC, etc.
  • the arrangement of the fuel lances 2 according to the invention is therefore also advantageous because trailing areas behind the fuel lance 2, in which Fuel 3 can accumulate, are practically completely excluded.
  • the cross section of the mixing zone 11 for example as Venturi channel or any additional internals (radial or in Circumferential direction) within the mixing zone 11 can increase the Speed and thus an improved mixing of hot gas 5 and fuel 3 / supporting air 4 can be reached.
  • This is also in combination with the built-in components mentioned are therefore advantageous because with the targeted feed of different sectors through the rays 7, the fuel 3 at same pressure can be transported in different sectors.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

The fuel (3) and air (4) are injected into the mixer zone (11) into a hot gas stream (5) through a fuel lance (2) from at least one side wall (6) of the mixer zone (11). The fuel and air are injected in different mixture streams (7) which can be sent in different directions. Independent claim describes burner chamber where fuel lance is let into side wall of mixer zone in the form of a ball.

Description

TECHNISCHES GEBIETTECHNICAL AREA

Bei der Erfindung handelt es sich um eine Brennkammer gemäss dem Oberbegriff des Anspruchs 4 bzw. um ein Verfahren zum Betrieb der Brennkammer gemäss dem Oberbegriff des Anspruchs 1.The invention is a combustion chamber according to the Preamble of claim 4 or a method for operating the Combustion chamber according to the preamble of claim 1.

STAND DER TECHNIKSTATE OF THE ART

Aus der Offenlegungsschrift DE-A1-44 17 538 ist eine Brennkammer mit Selbstzündung bekannt. In dieser Brennkammer werden durch eine Brennstofflanze Brennstoff und Stützluft in einen Heissgasstrom eingeführt, dort vermischt und die Mischung in einer nachgeschalteten Verbrennungszone verbrannt. Die Brennstofflanze befindet sich in einer Mischzone und ist dort zentral angeordnet. Sie ist für etwa 10% des Gesamtvolumenstroms durch den Kanal dimensioniert, wobei der Brennstoff quer oder auch in Richtung zur Strömung eingedüst werden kann. Der eingedüste Brennstoff wird in Verbindung mit einem Anteil Stützluft über mehrere, radiale Öffnungen von den stromauf injizierten Wirbeln mitgerissen und mit der Hauptströmung vermischt. Der eingedüste Brennstoff folgt dem schraubenförmigen Verlauf der Wirbel und wird stromab in der Kammer gleichmässig verteilt. Hierdurch reduziert sich die Gefahr von Aufprallstrahlen an der gegenüberliegenden Kanalwand sowie die Bildung von "hot spots", wie dies bei einer unverwirbelten Strömung der Fall ist.From the published patent application DE-A1-44 17 538 there is a combustion chamber Ignition known. In this combustion chamber by a Fuel lance fuel and supporting air introduced into a hot gas stream, mixed there and the mixture in a downstream Combustion zone burned. The fuel lance is in one Mixing zone and is centrally located there. It is for about 10% of the Total volume flow through the channel dimensioned, the fuel can be injected transversely or in the direction of the flow. The injected fuel is combined with a portion of supporting air several radial openings entrained by the vertebrae injected upstream and mixed with the main flow. The injected fuel follows helical course of the vertebrae and is downstream in the chamber equally distributed. This reduces the risk of impact rays on the opposite channel wall as well as the formation of "hot spots", such as this is the case with an undisturbed flow.

Die Vorteile der zentralen Brennstoffeindüsung werden mit einer relativ schwierig zu kühlenden Brennstofflanzenoberfläche im Heissgasstrom erkauft. Zudem beeinflusst dieser Einbau die Strömung der Heissgase nicht unerheblich. Aus strömungstechnischen Gründen ist eine minimale Lanzenlänge erforderlich. Diese Lanzenlänge bedingt zudem, dass die Brennstofflanze zu Montagezwecken durch ein entsprechendes Langloch in den Brenner eingeführt wird. Dabei entsteht zwischen der Brennerwand und der Brennstofflanze ein relativ grosser Spalt, der relativ schwierig abzudichten ist. Entsprechend unregelmässige Luftleckagen beeinflussen das gesamte Verhalten des Brenners negativ.The advantages of central fuel injection are relative difficult to cool fuel lance surface in the hot gas stream he buys. In addition, this installation does not affect the flow of hot gases irrelevant. For fluidic reasons, this is a minimal one Lance length required. This lance length also means that the Fuel lance for assembly purposes through a corresponding elongated hole in the burner is inserted. This creates between the burner wall and the fuel lance a relatively large gap that is relatively difficult to seal is. Correspondingly irregular air leaks affect the whole Burner behavior negative.

DARSTELLUNG DER ERFINDUNGPRESENTATION OF THE INVENTION

Es ist Ziel dieser Erfindung, die genannten Nachteile zu vermeiden. Die Erfindung löst die Aufgabe, eine Brennkammer und ein Verfahren zum Betrieb dieser Brennkammer zu schaffen, mit welchem es möglich ist, die Störung der Heissgasströmung in der Mischzone der Brennkammer zu minimieren. Dies soll bei gleichzeitig geringerer Kühlung der Brennstofflanze geschehen und es soll ein verbessertes Verhalten der Brennkammer in allen Lastbereichen erreichen werden.The aim of this invention is to avoid the disadvantages mentioned. The Invention solves the problem of a combustion chamber and a method of operation to create this combustion chamber with which it is possible to disrupt the To minimize hot gas flow in the mixing zone of the combustion chamber. This should happen with less cooling of the fuel lance and it should improve the behavior of the combustion chamber in all load ranges will achieve.

Erfindungsgemäss wird dies bei einem Verfahren gemäss dem Oberbegriff des Anspruchs 1 dadurch erreicht, dass der Brennstoff von mindestens einer Seitenwand der Mischzone der Brennkammer eingedüst wird und es wird bei der Brennkammer gemäss dem Oberbegriff des Anspruchs 4 dadurch erreicht, dass die mindestens eine Brennstofflanze in eine Seitenwand der Mischzone der Brennkammer eingelassen ist. Selbstverständlich ist es denkbar, dass ebenfalls Stützluft durch diese Brennstofflanze eingedüst wird. According to the invention, this is the case with a method according to the preamble of claim 1 achieved in that the fuel of at least one Side wall of the mixing zone of the combustion chamber is injected and it is at the combustion chamber according to the preamble of claim 4 thereby achieved that the at least one fuel lance in a side wall of the Mixing zone of the combustion chamber is embedded. Of course it is conceivable that support air is also injected through this fuel lance.

Ein Vorteil einer solchen seitlichen, asymmetrischen Eindüsung des Brennstoffs liegt insbesondere darin, dass durch die Brennstofflanze nur eine geringe Störung der Strömung verursacht wird, wobei sich diese Störung lediglich an der Seitenwand der Mischzone und nicht mehr zentral in der Hauptströmung befindet. Vorteilhaft ist es dabei auch, wenn die mindestens eine Brennstofflanze in Form einer Kugel oder eines sich in Hauptströmungsrichtung erstreckenden Ellipsoiden in die Seitenwand der Brennkammer eingelassen ist und in den Innenraum der Mischzone der Brennkammer ragt. Durch die Ausgestaltung der Mischzone als Venturikanal bzw. evtl. zusätzlich vorhandene Einbauten (radial oder in Umfangsrichtung) kann eine Erhöhung der Geschwindigkeit und damit eine verbesserte Vermischung von Heissgas und Brennstoff/Stützluft erreicht werden. Nachlaufgebiete hinter der Brennstofflanze, in welchen sich Brennstoff ansammeln kann, sind durch diese Art der Anordnung praktisch ausgeschlossen.An advantage of such a lateral, asymmetrical injection of the Fuel is in particular that only one through the fuel lance little flow disturbance is caused, which is this disturbance only on the side wall of the mixing zone and no longer centrally in the Main flow is located. It is also advantageous if at least a fuel lance in the form of a ball or one in Main flow direction extending ellipsoids in the side wall of the Combustion chamber is inserted and in the interior of the mixing zone Combustion chamber protrudes. By designing the mixing zone as a venturi channel or any additional internals (radial or circumferential) can increase the speed and thus improve it Mixing of hot gas and fuel / supporting air can be achieved. Trail areas behind the fuel lance, in which fuel can accumulate are practical due to this type of arrangement locked out.

Durch eine verkleinerte Fläche der Kontaktstelle zwischen der Brennstofflanze und der Heissgasströmung kann die Kühlung der Brennstofflanze vorteilhaft minimiert werden. Der Bereich der Abdichtung zwischen Seitenwand der Mischzone und Brennstofflanze wird ebenfalls vorteilhaft klein und in vorteilhafter Form gehalten.Due to a reduced area of the contact point between the fuel lance and the hot gas flow can advantageously cool the fuel lance be minimized. The area of the seal between the sidewall of the Mixing zone and fuel lance is also advantageously small and in held advantageous shape.

Eine vorteilhafte Ausführungsform des erfindungsgemässen Verfahrens liegt darin, dass der Brennstoff und die eventuell vorhandene Stützluft in verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen in die Mischzone der Brennkammer eingedüst werden, wobei die verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen in verschiedene Richtungen bzw. in verschiedene Sektoren innerhalb der Mischzone der Brennkammer gerichtet sind. Diese Ausführungsform ist deshalb besonders vorteilhaft, da je nach Auslastung der Brennkammer Strahlen zu- oder abgeschaltet werden können. Dies ist auch in Kombination mit den oben erwähnten Einbauten deshalb vorteilhaft, da mit der gezielten Anspeisung von verschiedenen Sektoren durch die Strahlen, der Brennstoff bei gleichem Druck in verschiedene Bereiche innerhalb der Mischzone transportiert werden kann.An advantageous embodiment of the method according to the invention lies in that the fuel and any supporting air present in various fuel / supporting air mixture jets in the mixing zone of the Combustion chamber to be injected, the different Fuel / supporting air mixture jets in different directions or in different sectors directed within the mixing zone of the combustion chamber are. This embodiment is particularly advantageous because depending on Utilization of the combustion chamber beams can be switched on or off. This is also in combination with the internals mentioned above advantageous because with the targeted feeding of different sectors through the jets, the fuel at different pressures in different Areas within the mixing zone can be transported.

KURZE BESCHREIBUNG DER ZEICHNUNGENBRIEF DESCRIPTION OF THE DRAWINGS

Die Erfindung wird anhand den beigefügten Figuren näher bezeichnet, wobei

Fig. 1
schematisch einen Schnitt durch eine Ringbrennkammer gemäss der Erfindung darstellt,
Fig. 2
einen Schnitt gemäss der Linie II-II in der Figur 1 und
Fig. 3
den Ausschnitt III der Figur 2.
The invention is described in more detail with reference to the accompanying figures, wherein
Fig. 1
schematically represents a section through an annular combustion chamber according to the invention,
Fig. 2
a section along the line II-II in Figure 1 and
Fig. 3
section III of FIG. 2.

Es werden nur die für die Erfindung wesentlichen Elemente dargestellt. Gleiche Elemente werden in unterschiedlichen Figuren gleich bezeichnet.Only the elements essential to the invention are shown. The same elements are given the same names in different figures.

WEG ZUR AUSFÜHRUNG DER ERFINDUNGWAY OF CARRYING OUT THE INVENTION

Die Figur 1 zeigt eine erfindungsgemässe Brennkammer 1, welche als eine um eine Wellenachse 9 angeordnete Ringbrennkammer ausgeführt ist. Die Brennkammer 1 besteht aus einem Wirbelerzeuger 14, einer Mischzone 11 und aus einer Verbrennungszone 12. Solche Ringbrennerkammern eignen sich sehr gut, um als selbstzündende Brennkammer 1 betrieben zu werden, wobei die Brennkammer 1 dann zwischen zwei, in der einzigen Figur nicht dargestellten Turbinen plaziert ist. Ein Heissgasstrom 5, welcher aus einer ersten, nicht dargestellten Turbine kommt, strömt durch den Wirbelerzeuger 14 in die Mischzone 11, wird dort mit einem Brennstoff 3 vermischt, entzündet sich von selbst in der Verbrennungszone 12 und wird daraufhin in einer zweiten, ebenfalls nicht dargestellten Turbine entspannt. Wird eine solche Brennkammer 1 aufgrund von Selbstzündung betrieben, so ist die stromauf wirkende Turbine nur auf eine Teilentspannung der Heissgase 5 ausgelegt, wobei die Heissgase 5 dann noch mit einer recht hohen Temperatur in den Wirbelerzeuger 14 und die Mischzone 11 der Brennkammer 1 strömen. Die Temperatur der Selbstzündung ist selbstverständlich brennstoffabhängig. Zwischen der Mischzone 11 und der Verbrennungszone 12 befindet sich eine sprunghafte Querschnittserweiterung 13. In der Ebene der Querschnittserweiterung 13 stellt sich die Flammenfront ein.FIG. 1 shows a combustion chamber 1 according to the invention, which as one annular combustion chamber arranged around a shaft axis 9. The Combustion chamber 1 consists of a vortex generator 14, a mixing zone 11 and from a combustion zone 12. Such ring burner chambers are suitable very well in order to be operated as a self-igniting combustion chamber 1, the combustion chamber 1 then not between two, in the single figure shown turbines is placed. A hot gas stream 5, which consists of a first turbine, not shown, comes flows through the vortex generator 14 into the mixing zone 11, is mixed there with a fuel 3, ignited itself in the combustion zone 12 and is then in a second, also not shown turbine relaxed. Will be one Combustion chamber 1 operated due to self-ignition, so it is upstream acting turbine designed only for a partial relaxation of the hot gases 5, the hot gases 5 are then still at a very high temperature in the Vortex generator 14 and the mixing zone 11 of the combustion chamber 1 flow. The The temperature of the auto-ignition is of course dependent on the fuel. There is one between the mixing zone 11 and the combustion zone 12 abrupt cross-sectional expansion 13. In the level of Cross-sectional expansion 13 sets the flame front.

Die Mischzone 11, wie sie in der Figur 1 dargestellt ist, ist als Venturikanal ausgestaltet. Selbstverständlich kann eine andere Form von Querschnittsänderungen gewählt werden, solange dies der verbesserten Beschleunigung und Vermischung von Brennstoff 4 und Heissgasen 5 dient. Im Bereich der engsten Stelle befindet sich eine Brennstofflanze 2, mit welcher Brennstoff 3 und zusätzliche Stützluft 4 in die Heissgase 5 eingedüst werden. Erfindungsgemäss ist die Brennstofflanze 2 in eine Seitenwand 6 der Mischzone 11 eingelassen. Die Verteilung des Brennstoffs 3 und der Stützluft 2 erfolgt somit asymmetrisch in bezug auf den Querschnitt der Mischzone 11.The mixing zone 11, as shown in FIG. 1, is a venturi channel designed. Of course, another form of Cross section changes can be chosen as long as this is the improved Acceleration and mixing of fuel 4 and hot gases 5 is used. In the area of the narrowest point there is a fuel lance 2 with which fuel 3 and additional supporting air 4 are injected into the hot gases 5 become. According to the invention, the fuel lance 2 is in a side wall 6 of the Mixing zone 11 let in. The distribution of the fuel 3 and the supporting air 2 thus takes place asymmetrically with respect to the cross section of the mixing zone 11.

Ein Vorteil einer solchen seitlichen, asymmetrischen Eindüsung des Brennstoffs 3 liegt insbesondere darin, dass die Brennstofflanze 2 nur eine geringe Störung der Strömung darstellt, wobei sich diese Störung lediglich an der Seitenwand 6 der Mischzone 11 und nicht mehr wie bisher zentral in der Hauptströmung befindet. In einer vorteilhaften Ausführungsform ist die Brennstofflanze 2 in Form einer Kugel oder eines sich in Hauptströmungsrichtung des Heissgases 5 erstreckenden Ellipsoiden in die Seitenwand 6 der Brennkammer 1 eingelassen und ragt in den Innenraum der Mischzone 11 der Brennkammer 1. Durch eine verkleinerte Fläche der Kontaktstelle zwischen der Brennstofflanze 2 und der Heissgasströmung kann sowohl die Kühlung der Brennstofflanze 2 vorteilhaft minimiert als auch die Festigkeit der Brennkammer 1 insgesamt erhöht werden. In der Praxis bedeutet dies, dass die verkleinerte Oberfläche der Brennstofflanze 2 einfach zu kühlen ist. Eine verbesserte Abdichtung zur Vermeidung von Leckagen wird dadurch erreicht, dass der Durchbruch anstelle eines bisher bekannten Langlochs entsprechend kleiner, d.h. kreisrund oder ellipsenförmig, ausgeführt werden kann, was insgesamt eine Reduktion der Leckagemenge bedeutet.An advantage of such a lateral, asymmetrical injection of the Fuel 3 is in particular that the fuel lance 2 only one represents little disturbance of the flow, this disturbance merely being the side wall 6 of the mixing zone 11 and no longer centrally in the Main flow is located. In an advantageous embodiment, the Fuel lance 2 in the form of a ball or one in Main flow direction of the hot gas 5 extending ellipsoids in the Side wall 6 of the combustion chamber 1 embedded and protrudes into the interior of the Mixing zone 11 of the combustion chamber 1. Through a reduced area of the Contact point between the fuel lance 2 and the hot gas flow can both the cooling of the fuel lance 2 advantageously minimized as well Strength of the combustion chamber 1 can be increased overall. In practice this means that the reduced surface area of the fuel lance 2 is simple is to be cooled. An improved seal to prevent leakage is achieved in that the breakthrough instead of a previously known Elongated holes correspondingly smaller, i.e. circular or elliptical, can be performed, resulting in a total reduction in the amount of leakage means.

Eine vorteilhafte Ausführungsform des erfindungsgemässen Verfahrens liegt darin, dass der Brennstoff 3 und die eventuell vorhandene Stützluft 4 in verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen 7 in die Mischzone 11 der Brennkammer 1 eingedüst werden, wobei die verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen 7 in verschiedene Sektoren bzw. in verschiedene Zielräume innerhalb der Mischzone 11 der Brennkammer 1 gerichtet sind. Die Figur 2 zeigt einen Schnitt gemäss der Linie II-II der Figur 1. Dort ist die Ausrichtung der Strahlen 7 in verschiedene Bereiche der Mischzone 11 gut sichtbar. Die Figur 3 zeigt weiter den Ausschnitt III der Figur 2 näher. Durch eine Anordnung von mehreren Kanälen nebeneinander ist die Eindüsung von Brennstoff 3 und Stützluft 4 möglich. Die Stützluft 4 umgibt den Brennstoff 3 mantelförmig, wobei die Brennstoffstrahlen als Plain-Jet in die Mischzone eingedüst werden. Durch die Wahl von verschiedenen Kanälen können verschiedene Brennstoffarten (gasförmig / flüssig) verwendet werden. Ein derartiges Eindüsungprinzip ist im Prinzip aus der Offenlegungsschrift EP-A1-1,030,109 bekannt.An advantageous embodiment of the method according to the invention lies in that the fuel 3 and any supporting air 4 in various fuel / supporting air mixture jets 7 into the mixing zone 11 the combustion chamber 1 are injected, the various Fuel / supporting air mixture jets 7 in different sectors or in different target spaces within the mixing zone 11 of the combustion chamber 1 are directed. Figure 2 shows a section along the line II-II of the figure 1. There is the alignment of the rays 7 in different areas of the Mixing zone 11 clearly visible. FIG. 3 also shows section III of FIG Figure 2 closer. By arranging several channels next to each other injection of fuel 3 and supporting air 4 is possible. The supporting air 4 surrounds the fuel 3 in a jacket shape, the fuel jets as a plain jet be injected into the mixing zone. By choosing different Channels can use different types of fuel (gaseous / liquid) become. Such an injection principle is in principle from the Publication EP-A1-1,030,109 known.

Der Einsatz von unterschiedlichen Düsengeometrien ist für diesen Zweck geeignet. Die Ausführungsform der Strahlen 7 ist deshalb besonders vorteilhaft, da je nach Auslastung der Brennkammer Strahlen 7 zu- oder abgeschaltet werden können. Dies bedeutet, dass die Strahlen 7 einzeln angespiesen werden. Insgesamt kann der gesamte Betriebsbereich von minimaler zu maximaler Brennstoffmenge vergrössert werden. Somit wird ein verbessertes Teillastverhalten erreicht, was sich in bezug auf Schadstoffverhalten, also Bildung von CO, NOx, UHC u.s.w. positiv auswirkt. Daneben ist es ebenso möglich, alle Brennstoff/Stützluft-Gemisch-Strahlen 7 einer Brennstofflanze 2 gemeinsam zu- oder abzuschalten.The use of different nozzle geometries is suitable for this purpose. The embodiment of the beams 7 is therefore particularly advantageous since, depending on the load on the combustion chamber, beams 7 can be switched on or off. This means that the beams 7 are fed individually. Overall, the entire operating range can be increased from minimum to maximum fuel quantity. An improved part-load behavior is thus achieved, which has a positive effect with regard to pollutant behavior, i.e. formation of CO, NO x , UHC, etc. In addition, it is also possible to switch on or off all fuel / supporting air mixture jets 7 of a fuel lance 2 together.

Die erfindungsgemässe Anordnung der Brennstofflanzen 2 ist auch deshalb vorteilhaft, da Nachlaufgebiete hinter der Brennstofflanze 2, in welchen sich Brennstoff 3 ansammeln kann, praktisch vollständig ausgeschlossen sind.The arrangement of the fuel lances 2 according to the invention is therefore also advantageous because trailing areas behind the fuel lance 2, in which Fuel 3 can accumulate, are practically completely excluded.

Durch eine Querschnittsänderung der Mischzone 11 beispielsweise als Venturikanal bzw. evtl. zusätzlich vorhandene Einbauten (radial oder in Umfangsrichtung) innerhalb der Mischzone 11 kann eine Erhöhung der Geschwindigkeit und damit eine verbesserte Vermischung von Heissgas 5 und Brennstoff 3 / Stützluft 4 erreicht werden. Dies ist auch in Kombination mit den erwähnten Einbauten deshalb vorteilhaft, da mit der gezielten Anspeisung von verschiedenen Sektoren durch die Strahlen 7, der Brennstoff 3 bei gleichem Druck in verschiedene Sektoren transportiert werden kann.By changing the cross section of the mixing zone 11, for example as Venturi channel or any additional internals (radial or in Circumferential direction) within the mixing zone 11 can increase the Speed and thus an improved mixing of hot gas 5 and fuel 3 / supporting air 4 can be reached. This is also in combination with the built-in components mentioned are therefore advantageous because with the targeted feed of different sectors through the rays 7, the fuel 3 at same pressure can be transported in different sectors.

BEZUGSZEICHENLISTELIST OF REFERENCE NUMBERS

11
Brennkammercombustion chamber
22
Brennstofflanzefuel lance
33
Brennstofffuel
44
Stützluftsupport air
55
HeissgasstromHot gas flow
66
Seitenwand des Brenners 1Side wall of the burner 1
77
Brennstoff/Luft-Gemisch-StrahlFuel / air mixture jet
88th
Abdichtungseal
99
Wellenachseshaft axis
1010
Abgaseexhaust
1111
Mischzonemixing zone
1212
Verbrennungszonecombustion zone
1313
QuerschnittserweiterungCross-sectional widening
1414
Wirbelerzeugervortex generators

Claims (9)

Verfahren zur Eindüsung von Brennstoff (3) und Stützluft (4) in eine Brennkammer (1), wobei der Brennstoff (3) in eine Mischzone (11) in einen Heissgasstrom (5) mittels mindestens einer Brennstofflanze (2) eingedüst wird und in einer der Mischzone (11) nachgeschalteten Verbrennungszone (12) zur Erzeugung eines Abgasstroms (10) verbrannt wird, wobei der Mischzone (11) ein Wirbelerzeuger (14) vorgeschaltet ist, und die Brennkammer (1) durch Selbstzündung zündet,
dadurch gekennzeichnet, dass
der Brennstoff (3) und die Stützluft (4) von mindestens einer Seitenwand (6) der Mischzone (11) der Brennkammer (1) in die Mischzone (11) eingedüst werden.Method for injecting fuel (3) and supporting air (4) into a combustion chamber (1), the fuel (3) being injected into a mixing zone (11) into a hot gas stream (5) by means of at least one fuel lance (2) and in one the combustion zone (12) downstream of the mixing zone (11) is burned to produce an exhaust gas stream (10), the mixing zone (11) being preceded by a vortex generator (14) and the combustion chamber (1) igniting by self-ignition,
characterized in that
the fuel (3) and the supporting air (4) are injected into the mixing zone (11) from at least one side wall (6) of the mixing zone (11) of the combustion chamber (1). Verfahren nach Anspruch 1,
dadurch gekennzeichnet, dass
der Brennstoff (3) und die Stützluft (4) in verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen (7) in die Mischzone (11) der Brennkammer (1) eingedüst werden, wobei die verschiedenen Brennstoff/Stützluft-Gemisch-Strahlen (7) in verschiedene Richtungen innerhalb der Mischzone (11) der Brennkammer (1) gerichtet sind.Method according to claim 1,
characterized in that
the fuel (3) and the supporting air (4) are injected in different fuel / supporting air mixture jets (7) into the mixing zone (11) of the combustion chamber (1), the different fuel / supporting air mixture jets (7) are directed in different directions within the mixing zone (11) of the combustion chamber (1). Verfahren nach Anspruch 2,
dadurch gekennzeichnet, dass
in Abhängigkeit des Lastverhaltens der Brennkammer (1) Brennstoff/Stützluft-Gemisch-Strahlen (7) zu- und abgeschaltet werden. Method according to claim 2,
characterized in that
Depending on the load behavior of the combustion chamber (1), fuel / supporting air mixture jets (7) can be switched on and off. Brennerkammer (1) zur Durchführung des Verfahrens nach einem der Ansprüche 1 bis 3, welche aus einer Mischzone (11) und einer Verbrennungszone (12) besteht, wobei zur Eindüsung von Brennstoff (3) und von Stützluft (4) in den sich in der Mischzone (11) befindenden Heissgasstrom (5) mindestens eine Brennstofflanze (2) vorhanden ist, wobei der Mischzone (11) ein Wirbelerzeuger (14) vorgeschaltet ist,
dadurch gekennzeichnet, dass
die mindestens eine Brennstofflanze (2) in eine Seitenwand (6) der Mischzone (11) der Brennkammer (1) eingelassen ist.Burner chamber (1) for carrying out the method according to one of claims 1 to 3, which consists of a mixing zone (11) and a combustion zone (12), wherein for the injection of fuel (3) and supporting air (4) into which in the Hot gas flow (5) located in the mixing zone (11), at least one fuel lance (2) is present, the mixing zone (11) being connected upstream of a vortex generator (14),
characterized in that
the at least one fuel lance (2) is let into a side wall (6) of the mixing zone (11) of the combustion chamber (1). Brennkammer (1) nach Anspruch 4,
dadurch gekennzeichnet, dass
die mindestens eine Brennstofflanze (2) in Form einer Kugel oder eines Ellipsoiden in die Seitenwand (6) des Brenners (1) eingelassen ist und in den Innenraum der Mischzone (11) der Brennkammer (1) ragt.Combustion chamber (1) according to claim 4,
characterized in that
the at least one fuel lance (2) in the form of a ball or an ellipsoid is let into the side wall (6) of the burner (1) and projects into the interior of the mixing zone (11) of the combustion chamber (1). Brennkammer (1) nach Anspruch 5,
dadurch gekennzeichnet, dass
sich zwischen der Brennstofflanze (2) und der Seitenwand (6) der Brennkammer (1) eine Abdichtung (8) befindet.Combustion chamber (1) according to claim 5,
characterized in that
there is a seal (8) between the fuel lance (2) and the side wall (6) of the combustion chamber (1). Brennkammer (1) nach einem der Ansprüche 4 bis 6,
dadurch gekennzeichnet, dass
die Brennkammer (1) als Ringbrennkammer ausgeführt ist.Combustion chamber (1) according to one of claims 4 to 6,
characterized in that
the combustion chamber (1) is designed as an annular combustion chamber. Brennkammer (1) nach einem der Ansprüche 4 bis 6,
dadurch gekennzeichnet, dass
die Mischzone (11) der Brennkammer (1) mindestens eine Querschnittänderung aufweist.Combustion chamber (1) according to one of claims 4 to 6,
characterized in that
the mixing zone (11) of the combustion chamber (1) has at least one change in cross section. Brennkammer (1) nach Anspruch 8,
dadurch gekennzeichnet, dass
die Mischzone (11) der Brennkammer (1) als Venturikanal ausgeführt ist.Combustion chamber (1) according to claim 8,
characterized in that
the mixing zone (11) of the combustion chamber (1) is designed as a venturi channel.
EP01126841A 2000-11-14 2001-11-12 Combustor and method for operating the same Expired - Lifetime EP1207350B1 (en)

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DE10056243A DE10056243A1 (en) 2000-11-14 2000-11-14 Combustion chamber and method for operating this combustion chamber
DE10056243 2000-11-14

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Also Published As

Publication number Publication date
EP1207350B1 (en) 2008-08-06
JP2002162037A (en) 2002-06-07
US20030093997A1 (en) 2003-05-22
DE50114185D1 (en) 2008-09-18
US6688111B2 (en) 2004-02-10
DE10056243A1 (en) 2002-05-23
EP1207350A3 (en) 2002-07-24

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