EP0602384A1 - Gasturbine combustor - Google Patents

Gasturbine combustor Download PDF

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Publication number
EP0602384A1
EP0602384A1 EP93118190A EP93118190A EP0602384A1 EP 0602384 A1 EP0602384 A1 EP 0602384A1 EP 93118190 A EP93118190 A EP 93118190A EP 93118190 A EP93118190 A EP 93118190A EP 0602384 A1 EP0602384 A1 EP 0602384A1
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EP
European Patent Office
Prior art keywords
combustion chamber
cooling
flow
wall
gas turbine
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.)
Withdrawn
Application number
EP93118190A
Other languages
German (de)
French (fr)
Inventor
Rolf Dr. Althaus
Burkhard Dr. Schulte-Werning
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0602384A1 publication Critical patent/EP0602384A1/en
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F23R3/54—Reverse-flow 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
    • 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
    • F05B2240/00—Components
    • F05B2240/20—Rotors
    • F05B2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05B2240/32—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor with roughened surface
    • 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
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/222—Improvement of heat transfer by creating turbulence
    • 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
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/224—Improvement of heat transfer by increasing the heat transfer surface
    • F05B2260/2241—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the invention relates to a gas turbine combustion chamber with environmentally friendly burners, which consist of at least two hollow conical partial bodies positioned one on top of the other in the direction of flow, the longitudinal axes of symmetry of which run radially offset from one another, the walls of the combustion chamber being protected from excessive material temperatures by cooling, and a method for operating the Combustion chamber.
  • Such gas turbine combustors are known.
  • a hood is arranged in front of the burners, through which the main mass flow flows directly to the burners and which generates the pressure drop necessary to maintain the required cooling mass flow.
  • this throttling worsens the efficiency, while at the same time the mass flow supplied to the combustion chamber via film cooling indirectly contributes to a deterioration in the NO x values.
  • the invention tries to avoid all these disadvantages. It is based on the object of designing the cooling duct in a gas turbine combustion chamber in such a way that pure convective cooling of the combustion chamber walls is made possible and that the efficiency of the gas turbine combustion chamber is increased by a method for operating the combustion chamber.
  • the gas turbine combustion chamber has a cooling channel which has a continuously decreasing height and / or increasing surface roughness in the flow direction of the cooling air, and in that the gas turbine combustion chamber is operated such that the entire mass flow coming from the compressor flows through the cooling channel for pure convective cooling of the combustion chamber walls is used and the entire mass flow then takes part in the combustion.
  • the height of the cooling duct decreases linearly in the direction of flow of the cooling air in order to adapt the cooling effect to a locally different heat load.
  • the height of the cooling channel in the flow direction can also decrease exponentially, for example.
  • the combustion chamber 1 shows an embodiment of the gas turbine combustor 1 according to the invention. It is an annular combustion chamber with a combustion chamber inner wall 2 and a combustion chamber outer wall 3. The two walls 2, 3 delimit the cooling channel 4 of the combustion chamber 1.
  • the combustion chamber 1 is equipped with environmentally friendly burners 5, of which only one burner 5 in FIG. 1 is shown. These burners 5 consist of at least two hollow conical ones positioned one on top of the other in the flow direction Partial bodies whose axes of longitudinal symmetry are radially offset from one another, resulting in flow-wise tangential air inlet slots for a combustion air flow, wherein at least one nozzle for injecting the fuel is placed in the conical cavity formed by the conical partial cone bodies.
  • a hood 6 is arranged in front of the environmentally friendly burners 5.
  • the essence of the invention is that the entire mass flow coming from the compressor 7 is used for pure convective cooling of the combustion chamber 1. This is done by adapting the cooling effect to the locally different thermal load, in that the cooling duct 4 has a continuously decreasing height in the flow direction of the cooling air. In the exemplary embodiment, the height of the cooling channel 4 decreases linearly. But this can, for. B. may also be exponentially decreasing. It is known that the use of longitudinal and transverse ribs 8 can improve the convective cooling effect, which is why 4 longitudinal and transverse ribs 8 can additionally be arranged in the cooling channel. In addition, the local surface roughness can optionally be varied.
  • the cooling air velocity u or the heat transfer coefficient ⁇ increases with decreasing height of the cooling channel 4 in the flow direction of the cooling air. This means that the highest cooling effect is achieved where the highest temperatures arise in the combustion chamber 1, i. H. it is cooled the most exactly where the greatest cooling effect is necessary.
  • the entire mass flow coming from the compressor 7 is passed through the cooling channel 4 and cools the combustion chamber inner wall 2 as a result of pure convective cooling. It is preheated by the cooling and then flows directly to the burners 5 within the hood 6. So the whole takes Mass flow inside the combustion chamber 1 participates in the combustion and has a positive influence on the NO x formation.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A gas-turbine combustion chamber (1) has environmentally-friendly burners (5) which consist of at least two hollow conical component bodies placed one on top of another in the flow direction and whose axes of longitudinal symmetry extend offset radially with respect to one another, resulting in tangential air inlet slots, opposing one another in terms of flow, for a stream of combustion air. At least one nozzle for injecting the fuel is placed in the conical cavity formed by the conical component bodies. The combustion chamber also has a cooling duct (4) which is bounded by the inner wall (2) of the combustion chamber and by the outer wall (3) of the combustion chamber and in which the cooling air flows along and in which it is possible to arrange longitudinal and transverse ribs (fins) (8). In the combustion chamber, the height of the cooling duct (4) decreases continuously in the direction of flow of the cooling air, and/or the surface roughness of the duct increases. The entire mass flow arriving from the compressor (7) is used for pure convective cooling of the inner wall (2) of the combustion chamber and participates in the combustion. <IMAGE>

Description

Technisches GebietTechnical field

Die Erfindung betrifft eine Gasturbinenbrennkammer mit umweltfreundlichen Brennern, welche aus mindestens zwei in Strömungsrichtung aufeinander positionierten, hohlen kegelförmigen Teilkörpern bestehen, deren Längssymmetrieachsen Zueinander radial versetzt verlaufen, wobei die Wände der Brennkammer durch Kühlung vor zu hohen Materialtemperaturen geschützt werden, und ein Verfahren zum Betrieb der Brennkammer.The invention relates to a gas turbine combustion chamber with environmentally friendly burners, which consist of at least two hollow conical partial bodies positioned one on top of the other in the direction of flow, the longitudinal axes of symmetry of which run radially offset from one another, the walls of the combustion chamber being protected from excessive material temperatures by cooling, and a method for operating the Combustion chamber.

Stand der TechnikState of the art

Derartige Gasturbinenbrennkammern sind bekannt. So werden z. B. Ringbrennkammerwände von Gasturbinen, die mit umweltfreundlichen Brennern ausgerüstet sind, welche aus mindestens zwei in Strömungsrichtung aufeinander positionierten, hohlen kegelförmigen Teilkörpern bestehen, deren Längssymmetrieachsen zueinander radial versetzt verlaufen, wodurch strömungsmässig entgegengesetzte tangentiale Lufteintrittsschlitze für einen Verbrennungsluftstrom entstehen, wobei im von den kegelförmigen Teilkegelkörpern gebildeten Kegelhohlraum mindestens eine Düse zur Eindüsung des Brennstoffes plaziert ist, durch eine Kombination von Konvektions- und Filmkühlung mit Hilfe eines Kühlmassenstromes vor zu hohen Materialtemperaturen geschützt.Such gas turbine combustors are known. So z. B. annular combustion chamber walls of gas turbines which are equipped with environmentally friendly burners, which consist of at least two hollow conical partial bodies positioned one on top of the other in the flow direction, the longitudinal axes of symmetry of which run radially offset from one another, as a result of which flow-wise opposite tangential air inlet slots for a combustion air flow arise, in which of the conical partial cone bodies formed cone cavity is placed at least one nozzle for injecting the fuel, protected by a combination of convection and film cooling with the aid of a cooling mass flow against excessive material temperatures.

Konstruktiv wird vor den Brennern eine Haube angeordnet, über die der Hauptmassenstrom direkt den Brennern zuströmt und die das zur Aufrechterhaltung des erforderlichen Kühlmassenstromes notwendige Druckgefälle erzeugt. Diese Drosselung verschlechtert aber den Wirkungsgrad, während gleichzeitig der über die Filmkühlung der Brennkammer zugeführte Massenstrom indirekt zu einer Verschlechterung der NOX-Werte beiträgt.In terms of design, a hood is arranged in front of the burners, through which the main mass flow flows directly to the burners and which generates the pressure drop necessary to maintain the required cooling mass flow. However, this throttling worsens the efficiency, while at the same time the mass flow supplied to the combustion chamber via film cooling indirectly contributes to a deterioration in the NO x values.

Darstellung der ErfindungPresentation of the invention

Die Erfindung versucht, all diese Nachteile zu vermeiden. Ihr liegt die Aufgabe zugrunde, bei einer Gasturbinenbrennkammer gemäss Oberbegriff des Anspruches 1 den Kühlkanal so zu gestalten, dass eine reine Konvektivkühlung der Brennkammerwände ermöglicht wird, und dass durch ein Verfahren zum Betrieb der Brennkammer der Wirkungsgrad der Gasturbinenbrennkammer erhöht wird.The invention tries to avoid all these disadvantages. It is based on the object of designing the cooling duct in a gas turbine combustion chamber in such a way that pure convective cooling of the combustion chamber walls is made possible and that the efficiency of the gas turbine combustion chamber is increased by a method for operating the combustion chamber.

Erfindungsgemäss wird dies dadurch erreicht, dass die Gasturbinenbrennkammer einen Kühlkanal besitzt, der eine in Strömungrichtung der Kühlluft stetig abnehmende Höhe und/oder zunehmende Oberflächenrauigkeit aufweist, und dass die Gasturbinenbrennkammer so betrieben wird, dass der gesamte vom Verdichter kommende Massenstrom durch den Kühlkanal fliesst, für eine reine Konvektivkühlung der Brennkammerwände eingesetzt wird und anschliessend der gesamte Massenstrom an der Verbrennung teilnimmt.According to the invention, this is achieved in that the gas turbine combustion chamber has a cooling channel which has a continuously decreasing height and / or increasing surface roughness in the flow direction of the cooling air, and in that the gas turbine combustion chamber is operated such that the entire mass flow coming from the compressor flows through the cooling channel for pure convective cooling of the combustion chamber walls is used and the entire mass flow then takes part in the combustion.

Die Vorteile der Erfindung sind unter anderem darin zu sehen, dass durch eine Verringerung der Drosselverluste der Wirkungsgrad der Gasturbinenbrennkammer erhöht wird und dass gleichzeitig die NOX-Emissionen minimiert werden.The advantages of the invention can be seen, inter alia, in that the efficiency of the gas turbine combustion chamber is increased by reducing the throttle losses and that at the same time the NO x emissions are minimized.

Es ist besonders zweckmässig, wenn die Höhe des Kühlkanals in Strömungsrichtung der Kühlluft linear abnehmend ist, um eine Anpassung der Kühlwirkung an eine lokal unterschiedliche Wärmebelastung zu erreichen. Die Höhe des Kühlkanals in Strömungsrichtung kann aber auch beispielsweise exponentiell abnehmend sein.It is particularly expedient if the height of the cooling duct decreases linearly in the direction of flow of the cooling air in order to adapt the cooling effect to a locally different heat load. However, the height of the cooling channel in the flow direction can also decrease exponentially, for example.

Kurze Beschreibung der ZeichnungBrief description of the drawing

In der Zeichnung ist ein Ausführungsbeispiel der Erfindung dargestellt.
Es zeigen:

Fig. 1
einen Teillängsschnitt der Gasturbinenbrennkammer;
Fig. 2
die Abhängigkeit der Kühlluftgeschwindigkeit und der Wärmeübergangszahl von der Höhe des Kühlluftkanals über die Brennkammerlänge gesehen.
In the drawing, an embodiment of the invention is shown.
Show it:
Fig. 1
a partial longitudinal section of the gas turbine combustor;
Fig. 2
the dependence of the cooling air speed and the heat transfer coefficient on the height of the cooling air duct over the length of the combustion chamber.

Es sind nur die für das Verständnis der Erfindung wesentlichen Elemente gezeigt. Die Strömungsrichtung der Arbeitsmittel ist mit Pfeilen bezeichnet.Only the elements essential for understanding the invention are shown. The direction of flow of the work equipment is indicated by arrows.

Weg zur Ausführung der ErfindungWay of carrying out the invention

In Fig. 1 ist ein Ausführungsbeispiel der erfindungsgemässen Gasturbinenbrennkammer 1 dargestellt. Es ist eine Ringbrennkammer mit einer Brennkammerinnenwand 2 und einer Brennkammeraussenwand 3. Die beiden Wände 2,3 begrenzen den Kühlkanal 4 der Brennkammer 1. Die Brennkammer 1 ist mit umweltfreundlichen Brennern 5 ausgerüstet, von denen zwecks Vereinfachung der Darstellung nur ein Brenner 5 in Fig. 1 abgebildet ist. Diese Brenner 5 bestehen aus mindestens zwei in Strömungsrichtung aufeinander positionierten, hohlen kegelförmigen Teilkörpern, deren Längssymmetrieachsen zueinander radial versetzt verlaufen, wodurch strömungsmässig entgegengesetzte tangentiale Lufteintrittsschlitze für einen Verbrennungsluftstrom entstehen, wobei im von den kegelförmigen Teilkegelkörpern gebildeten Kegelhohlraum mindestens eine Düse zur Eindüsung des Brennstoffes plaziert ist. Vor den umweltfreundlichen Brennern 5 ist eine Haube 6 angeordnet.1 shows an embodiment of the gas turbine combustor 1 according to the invention. It is an annular combustion chamber with a combustion chamber inner wall 2 and a combustion chamber outer wall 3. The two walls 2, 3 delimit the cooling channel 4 of the combustion chamber 1. The combustion chamber 1 is equipped with environmentally friendly burners 5, of which only one burner 5 in FIG. 1 is shown. These burners 5 consist of at least two hollow conical ones positioned one on top of the other in the flow direction Partial bodies whose axes of longitudinal symmetry are radially offset from one another, resulting in flow-wise tangential air inlet slots for a combustion air flow, wherein at least one nozzle for injecting the fuel is placed in the conical cavity formed by the conical partial cone bodies. A hood 6 is arranged in front of the environmentally friendly burners 5.

Das Wesentliche der Erfindung besteht nun darin, dass der gesamte vom Verdichter 7 kommende Massenstrom für eine reine Konvektivkühlung der Brennkammer 1 eingesetzt wird. Das geschieht durch eine Anpassung der Kühlwirkung an die lokal unterschiedliche thermische Belastung, indem der Kühlkanal 4 eine in Strömungsrichtung der Kühlluft stetig abnehmende Höhe aufweist. Im Ausführungsbeispiel ist die Höhe des Kühlkanals 4 linear abnehmend. Diese kann aber z. B. auch exponentiell abnehmend sein. Bekannt ist, dass durch den Einsatz von Längs- und Querrippen 8 die Konvektivkühlwirkung verbessert werden kann, deshalb können zusätzlich im Kühlkanal 4 Längs- und Querrrippen 8 angeordnet sein. Desweitern kann auch wahlweise die örtliche Oberflächenrauhigkeit variiert werden.The essence of the invention is that the entire mass flow coming from the compressor 7 is used for pure convective cooling of the combustion chamber 1. This is done by adapting the cooling effect to the locally different thermal load, in that the cooling duct 4 has a continuously decreasing height in the flow direction of the cooling air. In the exemplary embodiment, the height of the cooling channel 4 decreases linearly. But this can, for. B. may also be exponentially decreasing. It is known that the use of longitudinal and transverse ribs 8 can improve the convective cooling effect, which is why 4 longitudinal and transverse ribs 8 can additionally be arranged in the cooling channel. In addition, the local surface roughness can optionally be varied.

Wie aus Fig. 2 hervorgeht, erhöhen sich die Kühlluftgeschwindigkeit u bzw. die wärmeübergangszahl α mit abnehmender Höhe des Kühlkanals 4 in Strömungsrichtung der Kühlluft. Das bedeutet, dass die höchste Kühlwirkung dort erzielt wird, wo in der Brennkammer 1 die höchsten Temperaturen entstehen, d. h. es wird genau dort am meisten gekühlt, wo die grösste Kühlwirkung notwendig ist.As can be seen from FIG. 2, the cooling air velocity u or the heat transfer coefficient α increases with decreasing height of the cooling channel 4 in the flow direction of the cooling air. This means that the highest cooling effect is achieved where the highest temperatures arise in the combustion chamber 1, i. H. it is cooled the most exactly where the greatest cooling effect is necessary.

Der gesamte vom Verdichter 7 kommende Massenstrom wird durch den Kühlkanal 4 geleitet und kühlt infolge reiner Konvektivkühlung die Brennkammerinnenwand 2. Er wird dabei durch die Kühlung vorgewärmt und strömt anschliessend innerhalb der Haube 6 direkt den Brennern 5 zu. Somit nimmt der gesamte Massenstrom im Inneren der Brennkammer 1 an der Verbrennung teil und beeinflusst positiv die NOX-Bildung.The entire mass flow coming from the compressor 7 is passed through the cooling channel 4 and cools the combustion chamber inner wall 2 as a result of pure convective cooling. It is preheated by the cooling and then flows directly to the burners 5 within the hood 6. So the whole takes Mass flow inside the combustion chamber 1 participates in the combustion and has a positive influence on the NO x formation.

In Abhängigkeit von der Brennkammerauslegung verringern sich die Drosselverluste und es kommt zu einer Verbesserung des Wirkungsgrades gegenüber dem bekannten Stand der Technik.Depending on the design of the combustion chamber, the throttle losses decrease and there is an improvement in efficiency compared to the known prior art.

BezugszeichenlisteReference list

11
BrennkammerCombustion chamber
22nd
BrennkammerinnenwandInternal combustion chamber wall
33rd
BrennkammeraussenwandCombustion chamber outer wall
44th
KühlkanalCooling channel
55
Brennerburner
66
HaubeHood
77
Verdichtercompressor
88th
RippenRibs
uu
KühlluftgeschwindigkeitCooling air speed
αα
WärmeübergangszahlHeat transfer coefficient
LL
Länge des zylindrischen Teils der BrennkammerLength of the cylindrical part of the combustion chamber

Claims (4)

Gasturbinenbrennkammer (1) mit umweltfreundlichen Brennern (5), welche aus mindestens zwei in Strömungsrichtung aufeinander positionierten, hohlen kegelförmigen Teilkörpern bestehen, deren Längssymmetrieachsen zueinander radial versetzt verlaufen, wodurch strömungsmässig entgegengesetzte tangentiale Lufteintrittsschlitze für einen Verbrennungsluftstrom entstehen, wobei im von den kegelförmigen Teilkegelkörpern gebildeten Kegelhohlraum mindestens eine Düse zur Eindüsung des Brennstoffes plaziert ist, und mit einem durch die Brennkammerinnenwand (2) und die Brennkammeraussenwand (3) begrenzten Kühlkanal (4), in welchem die Kühlluft entlangströmt und in welchem Längs- und Querrippen (8) angeordnet sein können, dadurch gekennzeichnet, dass in Strömungrichtung der Kühlluft die Höhe des Kühlkanals (4) stetig abnehmend ist und/oder die Oberflächenrauhigkeit der Innenwände des Kühlkanals zunehmend ist.Gas turbine combustion chamber (1) with environmentally friendly burners (5), which consist of at least two hollow cone-shaped partial bodies positioned one on top of the other in the direction of flow, the longitudinal axes of symmetry of which run radially offset from one another, as a result of which opposite tangential air inlet slots for a combustion air flow arise, the cone hollow body formed by the conical partial conical hollow bodies at least one nozzle for injecting the fuel is placed, and with a cooling channel (4) delimited by the combustion chamber inner wall (2) and the combustion chamber outer wall (3), in which the cooling air flows along and in which longitudinal and transverse ribs (8) can be arranged, characterized in that the height of the cooling duct (4) is continuously decreasing in the flow direction of the cooling air and / or the surface roughness of the inner walls of the cooling duct is increasing. Gasturbinenbrennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Höhe des Kühlkanals (4) in Strömungsrichtung der Kühlluft linear abnehmend ist.Gas turbine combustion chamber according to claim 1, characterized in that the height of the cooling channel (4) is linearly decreasing in the flow direction of the cooling air. Gasturbinenbrennkammer nach Anspruch 1, dadurch gekennzeichnet, dass die Höhe des Kühlkanals (4) in Strömungsrichtung der Kühlluft exponentiell abnehmend ist.Gas turbine combustion chamber according to claim 1, characterized in that the height of the cooling channel (4) decreases exponentially in the flow direction of the cooling air. Verfahren zum Betrieb der Gasturbinenbrennkammer nach einem der Ansprüch 1 bis 3, dadurch gekennzeichnet, dass der gesamte vom Verdichter (7) kommende Massenstrom durch den Kühlkanal (4) fliesst und für eine reine Konvektivkühlung der Brennkammerinnenwand (2) eingesetzt wird und der gesamte Massenstrom an der Verbrennung teilnimmt.Method for operating the gas turbine combustion chamber according to one of Claims 1 to 3, characterized in that the entire mass flow coming from the compressor (7) flows through the cooling channel (4) and is used for pure convective cooling of the combustion chamber inner wall (2) and the entire mass flow is on participates in the combustion.
EP93118190A 1992-12-17 1993-11-10 Gasturbine combustor Withdrawn EP0602384A1 (en)

Applications Claiming Priority (2)

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DE4242721A DE4242721A1 (en) 1992-12-17 1992-12-17 Gas turbine combustion chamber
DE4242721 1992-12-17

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EP0602384A1 true EP0602384A1 (en) 1994-06-22

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JP (1) JP3523309B2 (en)
DE (1) DE4242721A1 (en)

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US5426943A (en) 1995-06-27
JPH06221562A (en) 1994-08-09
DE4242721A1 (en) 1994-06-23
JP3523309B2 (en) 2004-04-26

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