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WO2009007356A1 - Use of inert materials for protecting components of a combustion chamber and burner components - Google Patents

Use of inert materials for protecting components of a combustion chamber and burner components Download PDF

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Publication number
WO2009007356A1
WO2009007356A1 PCT/EP2008/058817 EP2008058817W WO2009007356A1 WO 2009007356 A1 WO2009007356 A1 WO 2009007356A1 EP 2008058817 W EP2008058817 W EP 2008058817W WO 2009007356 A1 WO2009007356 A1 WO 2009007356A1
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WO
WIPO (PCT)
Prior art keywords
combustion chamber
components
inert gas
burner
protected
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.)
Ceased
Application number
PCT/EP2008/058817
Other languages
German (de)
French (fr)
Inventor
Malte Blomeyer
Olga Deiss
Andre Kluge
Thomas Kunadt
Berthold Köstlin
Martin Lenze
Paul Pixner
Uwe Sieber
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of WO2009007356A1 publication Critical patent/WO2009007356A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M5/00—Casings; Linings; Walls
    • F23M5/08—Cooling thereof; Tube walls
    • F23M5/085—Cooling thereof; Tube walls using air or other gas as the cooling medium
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M2900/00—Special features of, or arrangements for combustion chambers
    • F23M2900/05001—Preventing corrosion by using special lining materials or other techniques
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • components are exposed to direct contact with a flame. This applies in particular to burner and combustion chamber components of a gas turbine. Although the direct contact of the burner or combustion chamber components with the flame should ideally not occur, it can not be avoided, for example, when a flashback occurs. In direct contact of the flame with burner components or combustion chamber surfaces, the materials of the burner are exposed to such high thermal loads that the material can be damaged.
  • hitherto high-temperature resistant materials such as Hastelloy X
  • Hastelloy X are used.
  • these materials provide a longer shelf life of the burner components, but provide no protection against temperatures of up to 1,400 0 C.
  • ceramic coatings and air film cooling are used. In the latter case, a boundary layer is created by air inflow, in which the fuel-air mixture is diluted so much that the fuel content is below the ignition limit and thus the risk of spreading of the flame is reduced to the burner or combustion chamber components.
  • the inventive method for protecting a surface from contact with a flame is characterized in that the surface to be protected is coated with an inert gas.
  • the surface to be protected may be the surface of a burner component or of a combustion chamber component of a gas turbine. Above all, the combustion chamber wall of a gas turbine can be effectively protected with the present method.
  • An interte gas is a gas which is very inert, meaning that it only takes part in a few chemical reactions.
  • the inert gas used in the present process may be, for example, water vapor, nitrogen, carbon dioxide or a noble gas such as helium, argon, neon, krypton, radon or xenon.
  • the inert gas used in the context of the present invention may also be a mixture of the gases mentioned.
  • the use of nitrogen or carbon dioxide is advantageous since their use is associated with the least cost.
  • the surface to be protected may be coated with the inert gas such that the inert gas is directed onto the surface through openings located in the surface to be protected.
  • the openings may be bores which extend at right angles to the surface to be protected or, in particular, at an angle thereto, at an angle to the latter.
  • the inert gas in the direction of flow of this fluid along the surface to be protected. This can be done in particular by openings in the form of obliquely arranged to the surface holes.
  • the fluid may be, for example, fuel or a Act fuel-air mixture.
  • the fuel can be hydrogen.
  • Fuel-air mixture a flow direction predetermined. It is therefore useful to protect the surface of the combustion chamber wall against direct contact with the burner flame in such a way that the inert gas is injected into the combustion chamber along the surface of the combustion chamber wall in the direction of this flow direction.
  • possibly existing film cooling holes can be used as injection openings.
  • the coating according to the invention of the endangered components or the endangered surfaces with a boundary layer of an inert gas means that oxygen is not present as oxidizer.
  • oxygen is not present as oxidizer.
  • An air film cooling is due to the large ignition range of hydrogen not suitable for this purpose.
  • Another advantage of the present invention is that it reduces the thermal stress on the components and thus extends their life.
  • FIG. 1 shows schematically a section through a part of a combustion chamber wall or a burner wall of a gas turbine.
  • FIG. 1 shows schematically a Section through a part of a combustion chamber wall or burner wall 1 of a gas turbine.
  • a fuel-air mixture 2 Inside the combustion chamber is a fuel-air mixture 2.
  • the flow direction of this fuel-air mixture 2 is indicated by an arrow 3.
  • the directed to the inside of the combustion chamber surface 7 of the combustion chamber wall 1 has an opening 6 which extends obliquely to the surface 7.
  • an inert gas 4 is passed into the interior of the combustion chamber.
  • the flow direction of the inert gas 4 is indicated by arrows 5.
  • an interface 8 is formed between the inert gas 4 introduced into the combustion chamber and the fuel-air mixture 2 located in the combustion chamber.
  • the fuel-air mixture 2 is burned via one or more flames.
  • a direct contact of the flame with the surface 7 of the combustion chamber wall 1 should be avoided.
  • an inert gas 4 is introduced into the combustion chamber via the opening 6, which is located in the combustion chamber wall 1.
  • the direction of flow 3 of the fuel-air mixture 2 causes the inert gas 4 to flow parallel to the flow direction 3 along the surface 7, thereby covering the surface 7 with a protective layer. Since the inert gas 4 is very inert and in particular contains no oxidizer such as oxygen, the flame in the combustion chamber can not reach the surface 7.
  • the opening 6 may be, for example, a film cooling hole. Moreover, as shown in FIG. 1, the opening can run obliquely to the surface 7, but also perpendicularly or at any other angle.
  • the inert gas 4 introduced into the combustion chamber through the opening 6 may be, for example, water vapor, nitrogen, carbon dioxide or a noble gas. As noble gases helium, argon, neon, krypton, radon or xenon are considered.
  • the presented in the present invention method provides effective protection of the surfaces of particular burner or combustion chamber components of a gas turbine against direct contact with a flame The thus caused protection against high temperatures reduces the thermal load on the components and thus extends their life.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The invention relates to making available a method for protecting a surface (7) from contact with a flame and is characterized in that the surface (7) which is to be protected is covered with an inert gas (4).

Description

Beschreibungdescription

Verwendung von inerten Stoffen zum Schutz von Bauteilen einer Brennkammer und von BrennerkomponentenUse of inert materials to protect components of a combustion chamber and burner components

In zahlreichen technischen Anwendungen sind Bauteile dem direkten Kontakt mit einer Flamme ausgesetzt. Dies gilt insbesondere für Brenner- und Brennkammerbauteile einer Gasturbine. Der direkte Kontakt der Brenner- bzw. Brennkammerbauteile mit der Flamme sollte zwar idealerweise nicht auftreten, er ist aber beispielsweise beim Auftreten eines Flammenrückschlages nicht zu vermeiden. Beim direkten Kontakt der Flamme mit Brennerbauteilen oder Brennkammeroberflächen werden die Materialien des Brenners so hohen thermischen Belastungen ausgesetzt, dass der Werkstoff beschädigt werden kann.In many technical applications, components are exposed to direct contact with a flame. This applies in particular to burner and combustion chamber components of a gas turbine. Although the direct contact of the burner or combustion chamber components with the flame should ideally not occur, it can not be avoided, for example, when a flashback occurs. In direct contact of the flame with burner components or combustion chamber surfaces, the materials of the burner are exposed to such high thermal loads that the material can be damaged.

Um eine Beschädigung der Bauteile zu vermeiden, werden bisher hochtemperaturfeste Materialien, beispielsweise Hastelloy X, eingesetzt. Diese Materialien bewirken zwar eine längere Haltbarkeit der Brennerbauteile, bieten jedoch keinen Schutz gegen Temperaturen von bis zu 1.4000C. Weiterhin kommen keramische Beschichtungen und Luftfilmkühlungen zum Einsatz. Bei letzterem wird durch Lufteinströmung eine Grenzschicht erzeugt, in der das Brennstoff-Luft-Gemisch so stark verdünnt wird, dass der Brennstoffgehalt unterhalb der Zündgrenze liegt und somit das Risiko eines Ausbreitens der Flamme bis zu den Brenner- bzw. Brennkammerbauteilen verringert wird.In order to avoid damage to the components, hitherto high-temperature resistant materials, such as Hastelloy X, are used. Although these materials provide a longer shelf life of the burner components, but provide no protection against temperatures of up to 1,400 0 C. Furthermore, ceramic coatings and air film cooling are used. In the latter case, a boundary layer is created by air inflow, in which the fuel-air mixture is diluted so much that the fuel content is below the ignition limit and thus the risk of spreading of the flame is reduced to the burner or combustion chamber components.

Gegenüber diesem Stand der Technik ist es die Aufgabe der vorliegenden Erfindung, ein vorteilhaftes Verfahren zumCompared to this prior art, it is the object of the present invention, an advantageous method for

Schutz einer Oberfläche vor dem Kontakt mit einer Flamme zur Verfügung zu stellen.To provide protection of a surface from contact with a flame.

Diese Aufgabe wird durch das Verfahren nach Anspruch 1 ge- löst. Die abhängigen Ansprüche enthalten weitere, vorteilhafte Ausgestaltungen der Erfindung. Das erfindungsgemäße Verfahren zum Schutz einer Oberfläche vor dem Kontakt mit einer Flamme zeichnet sich dadurch aus, dass die zu schützende Oberfläche mit einem inerten Gas überzogen wird. Insbesondere kann es sich bei der zu schützenden Oberfläche um die Oberfläche eines Brennerbauteils oder eines Brennkammerbauteils einer Gasturbine handeln. Mit dem vorliegenden Verfahren lässt sich vor allem die Brennkammerwand einer Gasturbine wirksam schützen.This object is achieved by the method according to claim 1. The dependent claims contain further, advantageous embodiments of the invention. The inventive method for protecting a surface from contact with a flame is characterized in that the surface to be protected is coated with an inert gas. In particular, the surface to be protected may be the surface of a burner component or of a combustion chamber component of a gas turbine. Above all, the combustion chamber wall of a gas turbine can be effectively protected with the present method.

Als intertes Gas bezeichnet man ein Gas, welches sehr reaktionsträge ist, sich also an nur wenigen chemischen Reaktionen beteiligt. Bei dem im Rahmen des vorliegenden Verfahrens verwendeten inerten Gas kann es sich beispielsweise um Wasserdampf, Stickstoff, Kohlendioxid oder ein Edelgas, wie Helium, Argon, Neon, Krypton, Radon oder Xenon, handeln. Es kann sich bei dem im Rahmen der vorliegenden Erfindung verwendeten i- nerten Gas auch um ein Gemisch aus den genannten Gasen handeln. Vorteilhaft ist die Verwendung von Stickstoff oder Kohlendioxid, da ihre Verwendung mit den geringsten Kosten ver- bunden ist.An interte gas is a gas which is very inert, meaning that it only takes part in a few chemical reactions. The inert gas used in the present process may be, for example, water vapor, nitrogen, carbon dioxide or a noble gas such as helium, argon, neon, krypton, radon or xenon. The inert gas used in the context of the present invention may also be a mixture of the gases mentioned. The use of nitrogen or carbon dioxide is advantageous since their use is associated with the least cost.

Im Zusammenhang mit der vorliegenden Erfindung kann die zu schützende Oberfläche mit dem inerten Gas derart überzogen werden, dass das inerte Gas durch Öffnungen, welche sich in der zu schützenden Oberfläche befinden, auf die Oberfläche geleitet wird. Bei den Öffnungen kann es sich beispielsweise um Bohrungen handeln, die senkrecht zur zu schützenden Oberfläche oder aber insbesondere schräg zu dieser in einem beliebigen Winkel verlaufen.In the context of the present invention, the surface to be protected may be coated with the inert gas such that the inert gas is directed onto the surface through openings located in the surface to be protected. By way of example, the openings may be bores which extend at right angles to the surface to be protected or, in particular, at an angle thereto, at an angle to the latter.

In dem Fall, dass die zu schützende Oberfläche einem Fluid ausgesetzt ist, welches eine Strömungsrichtung aufweist, ist es vorteilhaft das inerte Gas in Richtung der Strömungsrichtung dieses Fluids an der zu schützenden Oberfläche entlang zu leiten. Dies kann insbesondere durch Öffnungen in Form von schräg zur Oberfläche angeordneten Bohrungen erfolgen. Bei dem Fluid kann es sich zum Beispiel um Brennstoff oder ein Brennstoff-Luft-Gemisch handeln. Der Brennstoff kann unter anderem auch Wasserstoff sein.In the event that the surface to be protected is exposed to a fluid having a flow direction, it is advantageous to guide the inert gas in the direction of flow of this fluid along the surface to be protected. This can be done in particular by openings in the form of obliquely arranged to the surface holes. The fluid may be, for example, fuel or a Act fuel-air mixture. Among other things, the fuel can be hydrogen.

In der Brennkammer einer Gasturbine ist durch den in diese eingedüsten Brennstoff oder durch ein in diese eingedüstesIn the combustion chamber of a gas turbine is injected by the injected into this fuel or by a in this injected

Brennstoff-Luft-Gemisch eine Strömungsrichtung vorgegeben. Es ist daher sinnvoll die Oberfläche der Brennkammerwand gegen einen direkten Kontakt mit der Brennerflamme derart zu schützen, dass das inerte Gas in Richtung dieser Strömungsrichtung entlang der Oberfläche der Brennkammerwand in die Brennkammer eingedüst wird. Hierzu lassen sich insbesondere möglicherweise vorhandene Filmkühllöcher als Eindüsöffnungen verwenden.Fuel-air mixture a flow direction predetermined. It is therefore useful to protect the surface of the combustion chamber wall against direct contact with the burner flame in such a way that the inert gas is injected into the combustion chamber along the surface of the combustion chamber wall in the direction of this flow direction. In particular, possibly existing film cooling holes can be used as injection openings.

In Gegensatz zu der oben beschriebenen Luftfilmkühlung führt das erfindungsgemäße Überziehen der gefährdeten Bauteile bzw. der gefährdeten Oberflächen mit einer Grenzschicht aus einem inerten Gas dazu, dass Sauerstoff als Oxidator nicht vorhanden ist. Es besteht so die Möglichkeit auch Wasserstoff zu verbrennen ohne das hohe Risiko einer Schädigung der Bautei- Ie, insbesondere durch mögliche Flammenrückschläge. Dies wird dadurch bewirkt, dass die Flamme bedingt durch die inerte Gasgrenzschicht die Bauteile, insbesondere die Brennkammerwand, nicht erreicht. Eine Luftfilmkühlung ist bedingt durch den großen Zündbereich von Wasserstoff hierzu nicht geeignet. Ein weiterer Vorteil der vorliegenden Erfindung besteht darin, dass die thermische Belastung der Bauteile reduziert und somit ihre Lebensdauer verlängert wird.In contrast to the air-film cooling described above, the coating according to the invention of the endangered components or the endangered surfaces with a boundary layer of an inert gas means that oxygen is not present as oxidizer. There is also the possibility of burning hydrogen without the high risk of damage to the components, in particular due to possible flashbacks. This is caused by the fact that the flame does not reach the components, in particular the combustion chamber wall, due to the inert gas boundary layer. An air film cooling is due to the large ignition range of hydrogen not suitable for this purpose. Another advantage of the present invention is that it reduces the thermal stress on the components and thus extends their life.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung werden nachfolgend anhand eines Ausführungsbeispiels unter Bezugnahme auf die beiliegende Figur beschrieben .Further features, properties and advantages of the present invention will be described below by means of an embodiment with reference to the accompanying figure.

FIG 1 zeigt schematisch einen Schnitt durch einen Teil einer Brennkammerwand bzw. einer Brennerwand einer Gasturbine.1 shows schematically a section through a part of a combustion chamber wall or a burner wall of a gas turbine.

Im Folgenden wird das erfindungsgemäße Verfahren anhand von FIG 1 näher beschrieben. Die Figur 1 zeigt schematisch einen Schnitt durch einen Teil einer Brennkammerwand bzw. Brennerwand 1 einer Gasturbine. Im Inneren der Brennkammer befindet sich ein Brennstoff-Luft-Gemisch 2. Die Strömungsrichtung dieses Brennstoff-Luft-Gemisches 2 ist durch einen Pfeil 3 gekennzeichnet. Die zur Innenseite der Brennkammer gerichtete Oberfläche 7 der Brennkammerwand 1 weist eine Öffnung 6 auf, die schräg zur Oberfläche 7 verläuft. Durch die Öffnung 6 wird ein Inertgas 4 in das Innere der Brennkammer geleitet. Die Strömungsrichtung des Inertgases 4 ist durch Pfeile 5 ge- kennzeichnet. Zwischen dem in die Brennkammer eingeleiteten Inertgas 4 und dem sich in der Brennkammer befindlichen Brennstoff-Luft-Gemisches 2 bildet sich eine Grenzschicht 8 aus .The method according to the invention is described in more detail below with reference to FIG. 1 shows schematically a Section through a part of a combustion chamber wall or burner wall 1 of a gas turbine. Inside the combustion chamber is a fuel-air mixture 2. The flow direction of this fuel-air mixture 2 is indicated by an arrow 3. The directed to the inside of the combustion chamber surface 7 of the combustion chamber wall 1 has an opening 6 which extends obliquely to the surface 7. Through the opening 6, an inert gas 4 is passed into the interior of the combustion chamber. The flow direction of the inert gas 4 is indicated by arrows 5. Between the inert gas 4 introduced into the combustion chamber and the fuel-air mixture 2 located in the combustion chamber, an interface 8 is formed.

In der Brennkammer wird das Brennstoff-Luft-Gemisch 2 über eine oder mehrere Flammen verbrannt. Zum Schutz der Brennkammerwand 1 vor den hohen Temperaturen der Flamme soll ein direkter Kontakt der Flamme mit der Oberfläche 7 der Brennkammerwand 1 vermieden werden. Zu diesem Zweck wird über die Öffnung 6, welche sich in der Brennkammerwand 1 befindet, ein Inertgas 4 in die Brennkammer eingeleitet. Die Strömungsrichtung 3 des Brennstoff-Luft-Gemisches 2 bewirkt, dass das I- nertgas 4 parallel zur Strömungsrichtung 3 entlang der Oberfläche 7 strömt und dabei die Oberfläche 7 mit einer Schutz- schicht überzieht. Da das Inertgas 4 sehr reaktionsträge ist und insbesondere keinen Oxidator, wie beispielsweise Sauerstoff, enthält, kann die Flamme in der Brennkammer die Oberfläche 7 nicht erreichen.In the combustion chamber, the fuel-air mixture 2 is burned via one or more flames. To protect the combustion chamber wall 1 from the high temperatures of the flame, a direct contact of the flame with the surface 7 of the combustion chamber wall 1 should be avoided. For this purpose, an inert gas 4 is introduced into the combustion chamber via the opening 6, which is located in the combustion chamber wall 1. The direction of flow 3 of the fuel-air mixture 2 causes the inert gas 4 to flow parallel to the flow direction 3 along the surface 7, thereby covering the surface 7 with a protective layer. Since the inert gas 4 is very inert and in particular contains no oxidizer such as oxygen, the flame in the combustion chamber can not reach the surface 7.

Bei der Öffnung 6 kann es sich beispielsweise um ein Filmkühlloch handeln. Darüber hinaus kann die Öffnung wie in Figur 1 gezeigt schräg zur Oberfläche 7 verlaufen, aber auch senkrecht oder in einem beliebigen anderen Winkel. Das durch die Öffnung 6 in die Brennkammer eingeleitete Inertgas 4 kann beispielsweise Wasserdampf, Stickstoff, Kohlendioxid oder ein Edelgas sein. Als Edelgase kommen Helium, Argon, Neon, Krypton, Radon oder Xenon in betracht. Zusammenfassend bietet das im Rahmen der vorliegenden Erfindung vorgestellte Verfahren einen wirksamen Schutz der Oberflächen von insbesondere Brenner- oder Brennkammerbauteilen einer Gasturbine gegen den direkten Kontakt mit einer Flamme Der dadurch bewirkte Schutz vor hohen Temperaturen reduziert die thermische Belastung der Bauteile und verlängert somit deren Lebensdauer. The opening 6 may be, for example, a film cooling hole. Moreover, as shown in FIG. 1, the opening can run obliquely to the surface 7, but also perpendicularly or at any other angle. The inert gas 4 introduced into the combustion chamber through the opening 6 may be, for example, water vapor, nitrogen, carbon dioxide or a noble gas. As noble gases helium, argon, neon, krypton, radon or xenon are considered. In summary, the presented in the present invention method provides effective protection of the surfaces of particular burner or combustion chamber components of a gas turbine against direct contact with a flame The thus caused protection against high temperatures reduces the thermal load on the components and thus extends their life.

Claims

Patentansprüche claims 1. Verfahren zum Schutz einer Oberfläche (7) vor dem Kontakt mit einer Flamme, dadurch gekennzeichnet, dass die Oberfläche (7) mit einem inerten Gas (4) überzogen wird.A method of protecting a surface (7) from contact with a flame, characterized in that the surface (7) is coated with an inert gas (4). 2. Verfahren nach Anspruch 1, dadurch gekennzeichnet, dass es sich bei der zu schützenden Oberfläche (7) um die Oberfläche eines Brennerbauteils oder eines Brennkammerbauteiles (1) einer Gasturbine handelt.2. The method according to claim 1, characterized in that it is the surface to be protected (7) to the surface of a burner component or a combustion chamber component (1) of a gas turbine. 3. Verfahren nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass es sich bei dem inerten Gas (4) um Stickstoff, Wasserdampf, Kohlendioxid oder ein Edelgas handelt.3. The method according to claim 1 or 2, characterized in that it is the inert gas (4) is nitrogen, water vapor, carbon dioxide or a noble gas. 4. Verfahren nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das inerte Gas (4) durch Öffnungen (6) in der zu schützenden Oberfläche (7) an die Oberflä- che geleitet wird.4. The method according to any one of claims 1 to 3, characterized in that the inert gas (4) is passed through openings (6) in the surface to be protected (7) to the surface. 5. Verfahren nach Anspruch 4, dadurch gekennzeichnet, dass es sich bei den Öffnungen (6) um schräg zu der zu schützenden Oberfläche (7) angeordnete Boh- rungen handelt.5. Method according to claim 4, characterized in that the openings (6) are bores arranged obliquely to the surface (7) to be protected. 6. Verfahren nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das inerte Gas (4) in Richtung (3) der Strömung eines an der Oberfläche (7) vorbeiströmenden Fluids (2) entlang der zu schützenden Oberfläche (7) geleitet wird.6. The method according to any one of claims 1 to 5, characterized in that the inert gas (4) in the direction (3) of the flow of a on the surface (7) passing fluid (2) along the surface to be protected (7) is passed , 7. Verfahren nach Anspruch 6, dadurch gekennzeichnet, dass es sich bei dem Fluid (2) um Brennstoff oder ein Brennstoff-Luft-Gemisch handelt. 7. The method according to claim 6, characterized in that it is the fluid (2) is fuel or a fuel-air mixture. 8. Verfahren nach Anspruch 7, dadurch gekennzeichnet, dass es sich bei dem Brennstoff um Wasserstoff handelt.8. The method according to claim 7, characterized in that it is the fuel is hydrogen. 9. Verfahren nach einem der Ansprüche 4 bis 8, dadurch gekennzeichnet, dass es sich bei den Öffnungen (6) um Filmkühllöcher handelt. 9. Method according to one of claims 4 to 8, characterized in that the openings (6) are film cooling holes.
PCT/EP2008/058817 2007-07-09 2008-07-08 Use of inert materials for protecting components of a combustion chamber and burner components Ceased WO2009007356A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP07013410.1 2007-07-09
EP07013410A EP2014984A1 (en) 2007-07-09 2007-07-09 Use of inert substances for protecting components of a combustion chamber and burner components

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US8869889B2 (en) 2010-09-21 2014-10-28 Palmer Labs, Llc Method of using carbon dioxide in recovery of formation deposits
US8986002B2 (en) 2009-02-26 2015-03-24 8 Rivers Capital, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US9068743B2 (en) 2009-02-26 2015-06-30 8 Rivers Capital, LLC & Palmer Labs, LLC Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US9416728B2 (en) 2009-02-26 2016-08-16 8 Rivers Capital, Llc Apparatus and method for combusting a fuel at high pressure and high temperature, and associated system and device
US10859264B2 (en) 2017-03-07 2020-12-08 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof
US11199327B2 (en) 2017-03-07 2021-12-14 8 Rivers Capital, Llc Systems and methods for operation of a flexible fuel combustor
US11572828B2 (en) 2018-07-23 2023-02-07 8 Rivers Capital, Llc Systems and methods for power generation with flameless combustion

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US8986002B2 (en) 2009-02-26 2015-03-24 8 Rivers Capital, Llc Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US9068743B2 (en) 2009-02-26 2015-06-30 8 Rivers Capital, LLC & Palmer Labs, LLC Apparatus for combusting a fuel at high pressure and high temperature, and associated system
US9416728B2 (en) 2009-02-26 2016-08-16 8 Rivers Capital, Llc Apparatus and method for combusting a fuel at high pressure and high temperature, and associated system and device
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US10859264B2 (en) 2017-03-07 2020-12-08 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof
US11199327B2 (en) 2017-03-07 2021-12-14 8 Rivers Capital, Llc Systems and methods for operation of a flexible fuel combustor
US11435077B2 (en) 2017-03-07 2022-09-06 8 Rivers Capital, Llc System and method for combustion of non-gaseous fuels and derivatives thereof
US11828468B2 (en) 2017-03-07 2023-11-28 8 Rivers Capital, Llc Systems and methods for operation of a flexible fuel combustor
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US11572828B2 (en) 2018-07-23 2023-02-07 8 Rivers Capital, Llc Systems and methods for power generation with flameless combustion

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