EP0774100B1 - Thermal shield for a gas turbine combustion chamber - Google Patents

Thermal shield for a gas turbine combustion chamber Download PDF

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Publication number
EP0774100B1
EP0774100B1 EP95926909A EP95926909A EP0774100B1 EP 0774100 B1 EP0774100 B1 EP 0774100B1 EP 95926909 A EP95926909 A EP 95926909A EP 95926909 A EP95926909 A EP 95926909A EP 0774100 B1 EP0774100 B1 EP 0774100B1
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EP
European Patent Office
Prior art keywords
heat shield
combustion chamber
burner
air
hole
Prior art date
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Expired - Lifetime
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EP95926909A
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German (de)
French (fr)
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EP0774100A1 (en
Inventor
Achim Schmid
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Rolls Royce Deutschland Ltd and Co KG
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BMW Rolls Royce GmbH
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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • 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
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling
    • 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

  • the invention relates to a heat shield for a combustion chamber, in particular for an annular combustion chamber of a gas turbine, with a passage opening for a burner, the back of the combustion chamber facing away from the Heat shield is acted upon by cooling air and one at the edge of the passage opening has surrounding web.
  • the known state of the art is referred to US 5,307,637, the web for receiving or Storage of the burner is used.
  • the heat shield provided in the head of a combustion chamber serves as is known for this, the dome-shaped combustion chamber head area or the inside provided front panel before the action of that in the combustion chamber To protect hot gas and excessive heat radiation.
  • the heat shield must itself be cooled will.
  • conventional heat shields have so-called effusion holes in the the surface facing the combustion chamber, via the cooling air from the rear forth can pass a film of cooling air on the hot surface of the heat shield. This is detailed in the above font explained.
  • Another heat shield arrangement is shown in EP-A-0 521 687, air passage openings being provided in a web-like section are, through which cooling air can get into the combustion chamber.
  • the object of the invention is to demonstrate further measures, with the help of which an improved heat shield cooling can be achieved can.
  • the web is a Has a plurality of air transfer openings, which are at an angle the direction pointing towards the center of the passage opening are that one through the air transfer openings in an annular channel between the heat shield and the burner entering and from there into the Airflow entering the combustion chamber forms a vortex that is in the same direction with the vortex formed by the combustion air supplied through the burner, and the one vertebral axis perpendicular to the surface of the heat shield having.
  • Advantageous training and further education are included in the Subclaims.
  • the ring combustion chamber is one Designated gas turbine, the head side a dome-like end wall 2 and then one also as a retaining wall has functioning front panel 3.
  • this ring combustor corresponds this ring combustor the known prior art.
  • several burners 4 arranged in a circle over which Fuel and combustion air swirl into the Combustion chamber 1 is introduced.
  • the direction of the vortex is the combustion air introduced via the burner 4 3, 4 represented by arrows 5.
  • a heat shield 6 is provided, the so-called. Combustion chamber cathedral, d. H. the front panel 3 and the end wall 2 in front of the hot burner gases and inadmissible protects against high levels of radiation.
  • This The heat shield is via bolt 7 (see FIG. 2) on the front panel 3 fastened and has a passage opening 8 for the burner 4.
  • the burner 4 is one Surround sealing part 9, which in particular ensures that much of the breakthrough 10 in the end wall 2 supplied combustion air over the Burner 4 flows into the combustion chamber 1.
  • the heat shield points at the edge of the passage opening 8 one from the rear 6a to the rear, d. H. opposed cantilevering to the combustion chamber 1, rotating Bridge 14 on.
  • the individual dimensions are included chosen so that between the web 14 and the sealing part 9 results in an annular channel 15.
  • this ring channel 15 can cool air from the rear 6a of the heat shield 6th forth through air transfer openings 16, several of which are provided in the web 14, flow. Because the free end of the circumferential web 14 on a clamped ring 23, which fixes the sealing part 9, can also only through these air transfer openings 16 cooling air in the Ring channel 15 arrive.
  • the air stream flowing into the annular duct 15 arrives finally into the combustion chamber 1, but should on the way there the particularly highly stressed areas of the Cool heat shield 6 intensively. To do this, this should the air duct exiting the annular duct 15 into the combustion chamber 1 also as a cooling air film on the combustion chamber 1 facing hot surface 6b of the heat shield 6 place, especially in the edge region of the passage opening 8.
  • the Air flow in the ring channel impressed a vortex that is in the same direction is with the vortex which is fed via the burner 8 Combustion air.
  • the emerging from the ring channel 15 Cooling air is said to describe a vortex, which has the same direction as the arrows 5 with which the vortex of the combustion air supplied via the burner 4 is shown.
  • the swirl axes of these two Air vortices are essentially vertical to the plane or surface 6b of the heat shield 6.
  • the transition area between the web 14 and the hot surface 6b of the heat shield 6 is as a chamfer 18 trained, but can also be rounded be. This measure enables this via the ring channel 15 incoming cooling air flow, maintaining itself its flow direction as a cooling air film on the surface 6b to apply the heat shield 6. Particularly promoted this application of the cooling air flow as a cooling air film however, in that the swirl directions of the air flow guided over the annular duct 15 and that entering the combustion chamber 1 via the burner 4 Combustion air flow match.
  • the heat shield 6 is still with effusion holes 19 provided, which are called from the rear 6a Guide surface 6b and thus the passage of cooling air enable by the heat shield 6.
  • effusion holes 19 are deposited as a cooling air film on the surface 6b.
  • the central axes are of the effusion holes 19 inclined twice.
  • the first angle of inclination lies between the central axis of the effusion holes and a perpendicular to the surface 6b of the Heat shield 6, which means that the central axes of the Effusion holes 19 inclined to the surface 6b are so that the emerging from an effusion hole 19 Air flow at least partially sweeps across surface 6b.
  • Another angle of inclination ⁇ occurs in one perpendicular projection onto the surface 6b, whereby in this projection the central axis 20 of each effusion hole inclined to the tangent 21 to one around the center 17 the passage opening 8 through the respective effusion hole 19 placed circle 22 is.
  • 4 apparent design of the Effusion holes 19 form through these effusion holes 19 generated cooling air film a vortex that both a radially outward with respect to the center 17 Velocity component VR, as well as a tangential speed component extending to the pitch circle 22 VT has.
  • the angle of inclination ⁇ is chosen such that that the tangential component VT rectified is with the vortex that supplied via the burner 4 Combustion air, which is represented by the arrows 5. This rectification of the vertebrae ensures that a cooling air film lying optimally on the surface 6b can form.

Abstract

A thermal shield (6) for the head area of a combustion chamber has as usual a through-hole (5) for the burner. A continuous collar (14) with air passage holes (16) projects from the back side of the thermal shield at the edge of said through-hole. Cooling air can flow through said holes into a ring-shaped channel (15) arranged between the thermal shield and the burner, then into the combustion chamber. This cool air flow lies as a cool air film on the surface of the thermal shield. For that purpose, the cool air flow or cool air film whirls in the same direction as the combustion air supplied through the burner. To generate this whirling motion, the air passage holes in the collar are inclined in the radial direction. The thermal shield is further provided with appropriate inclined effusion holes (19).

Description

Die Erfindung betrifft ein Hitzeschild für eine Brennkammer, insbesondere für eine Ring-Brennkammer einer Gasturbine, mit einer Durchtrittsöffnung für einen Brenner, wobei die der Brennkammer abgewandte Rückseite des Hitzeschildes mit Kühlluft beaufschlagt ist und einen am Rand der Durchtrittsöffnung umlaufenden Steg aufweist. Zum bekannten Stand der Technik wird auf die US 5,307,637 verwiesen, wobei der Steg zur Aufnahme bzw. Lagerung des Brenners dient.The invention relates to a heat shield for a combustion chamber, in particular for an annular combustion chamber of a gas turbine, with a passage opening for a burner, the back of the combustion chamber facing away from the Heat shield is acted upon by cooling air and one at the edge of the passage opening has surrounding web. The known state of the art is referred to US 5,307,637, the web for receiving or Storage of the burner is used.

Das im Kopf einer Brennkammer vorgesehene Hitzeschild dient wie bekannt dazu, den domartig ausgebildeten Brennkammer-Kopfbereich bzw. die darin vorgesehene Frontplatte vor der Einwirkung des in der Brennkammer befindlichen Heißgases sowie vor übermäßiger Hitzestrahlung zu schützen. Um diese Funktion wahrnehmen zu können, muß das Hitzeschild seinerseits gekühlt werden. Hierzu weisen übliche Hitzeschilder sog. Effusionslöcher in der der Brennkammer zugewandten Fläche auf, über die Kühlluft von der Rückseite her durchtreten kann, um einen Kühlluftfilm auf die heiße Oberfläche des Hitzeschildes zu legen. Dies ist in der oben genannten Schrift ausführlich erläutert. Eine weitere Hitzeschild-Anordnung zeigt die EP-A-0 521 687, wobei in einem stegähnlichen Abschnitt Luftübertrittsöffnungen vorgesehen sind, über die Kühlluft in die Brennkammer gelangen kann. The heat shield provided in the head of a combustion chamber serves as is known for this, the dome-shaped combustion chamber head area or the inside provided front panel before the action of that in the combustion chamber To protect hot gas and excessive heat radiation. Around To be able to perform this function, the heat shield must itself be cooled will. For this purpose, conventional heat shields have so-called effusion holes in the the surface facing the combustion chamber, via the cooling air from the rear forth can pass a film of cooling air on the hot surface of the heat shield. This is detailed in the above font explained. Another heat shield arrangement is shown in EP-A-0 521 687, air passage openings being provided in a web-like section are, through which cooling air can get into the combustion chamber.

Da es jedoch nicht immer möglich ist, sämtliche gefährdete Zonen des Hitzeschildes nach diesem bekannten Stand der Technik ausreichend zu kühlen, hat sich die Erfindung zur Aufgabe gestellt, weitere Maßnahmen aufzuzeigen, mit Hilfe derer eine verbesserte Hitzeschildkühlung erzielt werden kann.However, since it is not always possible to cover all areas at risk Heat shield according to this known state of the art cool, the object of the invention is to demonstrate further measures, with the help of which an improved heat shield cooling can be achieved can.

Die Lösung dieser Aufgabe ist dadurch gekennzeichnet, daß der Steg eine Vielzahl von Luftübertrittsöffnungen aufweist, die unter einem Winkel gegenüber der ins Zentrum der Durchtrittsöffnung weisenden Richtung derart geneigt sind, daß ein durch die Luftübertrittsöffnungen in einen Ringkanal zwischen dem Hitzeschild und dem Brenner eintretender und von da aus in die Brennkammer gelangender Luftstrom einen Wirbel bildet, der gleichsinnig ist mit dem Wirbel, den die über den Brenner zugeführte Verbrennungsluft bildet, und der eine senkrecht zur Oberfläche des Hitzeschildes stehende Wirbelachse aufweist. Vorteilhafte Aus- und Weiterbildungen sind Inhalt der Unteransprüche.The solution to this problem is characterized in that the web is a Has a plurality of air transfer openings, which are at an angle the direction pointing towards the center of the passage opening are that one through the air transfer openings in an annular channel between the heat shield and the burner entering and from there into the Airflow entering the combustion chamber forms a vortex that is in the same direction with the vortex formed by the combustion air supplied through the burner, and the one vertebral axis perpendicular to the surface of the heat shield having. Advantageous training and further education are included in the Subclaims.

Näher erläutert wird die Erfindung anhand eines bevorzugten Ausführungsbeispiels. Dabei zeigt

Fig. 1
einen Teilschnitt durch den Kopf einer erfindungsgemäßen Gasturbinen-Ringbrennkammer,
Fig. 2
die obere Hälfte eines Hitzeschildes im Schnitt,
Fig. 3
die Aufsicht auf die kalte Rückseite des Hitzeschildes , sowie
Fig. 4
die Aufsicht auf die der Brennkammer zugewandte heiße Oberfläche.
The invention is explained in more detail with reference to a preferred exemplary embodiment. It shows
Fig. 1
a partial section through the head of a gas turbine annular combustion chamber according to the invention,
Fig. 2
the top half of a heat shield in section,
Fig. 3
supervision of the cold back of the heat shield, as well
Fig. 4
the supervision of the hot surface facing the combustion chamber.

Mit der Bezugsziffer 1 ist die Ring-Brennkammer einer Gasturbine bezeichnet, die kopfseitig eine domartige Abschlußwand 2 und darauffolgend eine auch als Stützwand fungierende Frontplatte 3 aufweist. Insofern entspricht diese Ring-Brennkammer dem bekannten Stand der Technik. Ebenfalls wie bekannt ragen in die Ring-Brennkammer 1 kreisförmig angeordnet mehrere Brenner 4 hinein, über die Brennstoff sowie Verbrennungsluft verwirbelt in die Brennkammer 1 eingebracht wird. Die Richtung des Wirbels der über den Brenner 4 eingebrachten Verbrennungsluft ist in den Fig. 3, 4 durch Pfeile 5 dargestellt.With the reference number 1, the ring combustion chamber is one Designated gas turbine, the head side a dome-like end wall 2 and then one also as a retaining wall has functioning front panel 3. In this respect corresponds this ring combustor the known prior art. Also protrude into the ring combustion chamber 1, as is known several burners 4 arranged in a circle over which Fuel and combustion air swirl into the Combustion chamber 1 is introduced. The direction of the vortex is the combustion air introduced via the burner 4 3, 4 represented by arrows 5.

Zwischen der Frontplatte 3 sowie der eigentlichen Brennkammer 1 ist ein Hitzeschild 6 vorgesehen, das den sog. Brennkammer-Dom, d. h. die Frontplatte 3 sowie die Abschlußwand 2 vor den heißen Brennergasen und vor unzulässig hoher Strahlungseinwirkung schützt. Dieses Hitzeschild ist über Bolzen 7 (vgl. Fig. 2) an der Frontplatte 3 befestigt und weist eine Durchtrittsöffnung 8 für den Brenner 4 auf. Dabei ist der Brenner 4 von einem Dichtungsteil 9 umgeben, welches insbesondere sicherstellt, daß ein Großteil der über den Durchbruch 10 in der Abschlußwand 2 zugeführten Verbrennungsluft über den Brenner 4 in die Brennkammer 1 einströmt.Between the front plate 3 and the actual combustion chamber 1 is a heat shield 6 is provided, the so-called. Combustion chamber cathedral, d. H. the front panel 3 and the end wall 2 in front of the hot burner gases and inadmissible protects against high levels of radiation. This The heat shield is via bolt 7 (see FIG. 2) on the front panel 3 fastened and has a passage opening 8 for the burner 4. The burner 4 is one Surround sealing part 9, which in particular ensures that much of the breakthrough 10 in the end wall 2 supplied combustion air over the Burner 4 flows into the combustion chamber 1.

Ein Teil des über den Durchbruch 10 zugeführten Luftstromes kann am Dichtungsteil 9 vorbei über eine Bohrungsreihe 11 in der Frontplatte 3 zur Rückseite 6a des Hitzeschildes 6 gelangen und hierdurch dieses Hitzeschild 6 kühlen. über Spalte 12 zwischen den Rändern des Hitzeschildes 6 sowie der inneren Brennkammerwand 13a bzw. der äußeren Brennkammerwand 13b kann ein Teil des die Rückseite 6a des Hitzeschildes 6 beaufschlagenden Luftstromes in die Brennkammer 1 gelangen. Part of the air flow supplied through the opening 10 can past the sealing part 9 over a row of holes 11 in the front panel 3 to the rear 6a of the Heat shield 6 and thereby this heat shield 6 cool. over column 12 between the edges of the Heat shield 6 and the inner combustion chamber wall 13a or the outer combustion chamber wall 13b, part of the the rear 6a of the heat shield 6 acting Air flow get into the combustion chamber 1.

Am Rand der Durchtrittsöffnung 8 weist das Hitzeschild einen von dessen Rückseite 6a nach hinten, d. h. entgegengerichtet zur Brennkammer 1 abkragenden, umlaufenden Steg 14 auf. Die einzelnen Dimensionierungen sind dabei so gewählt, daß sich zwischen dem Steg 14 sowie dem Dichtungsteil 9 ein Ringkanal 15 ergibt. In diesen Ringkanal 15 kann Kühlluft von der Rückseite 6a des Hitzeschildes 6 her durch Luftübertrittsöffnungen 16, von denen mehrere im Steg 14 vorgesehen sind, einströmen. Da das freie Ende des umlaufenden Steges 14 an einem eingeklemmten Ring 23, der das Dichtungsteil 9 fixiert, anliegt, kann auch nur durch diese Luftübertrittsöffnungen 16 Kühlluft in den Ringkanal 15 gelangen.The heat shield points at the edge of the passage opening 8 one from the rear 6a to the rear, d. H. opposed cantilevering to the combustion chamber 1, rotating Bridge 14 on. The individual dimensions are included chosen so that between the web 14 and the sealing part 9 results in an annular channel 15. In this ring channel 15 can cool air from the rear 6a of the heat shield 6th forth through air transfer openings 16, several of which are provided in the web 14, flow. Because the free end of the circumferential web 14 on a clamped ring 23, which fixes the sealing part 9, can also only through these air transfer openings 16 cooling air in the Ring channel 15 arrive.

Der in den Ringkanal 15 einströmende Luftstrom gelangt schließlich in die Brennkammer 1, soll jedoch auf dem Weg dorthin die besonders hoch beanspruchten Bereiche des Hitzeschildes 6 intensiv kühlen. Hierzu soll dieser aus dem Ringkanal 15 in die Brennkammer 1 austretende Luftstrom sich ebenfalls als Kühlluftfilm auf die der Brennkammer 1 zugewandte heiße Oberfläche 6b des Hitzeschildes 6 legen, und zwar insbesondere im Randbereich der Durchtrittsöffnung 8. Um diesen Effekt zu erzielen, wird dem Luftstrom im Ringkanal ein Wirbel aufgeprägt, der gleichsinnig ist mit dem Wirbel der über den Brenner 8 zugeführten Verbrennungsluft. Die aus dem Ringkanal 15 austretende Kühlluft soll somit einen Wirbel beschreiben, der die gleiche Richtung hat wie die Pfeile 5, mit denen der Wirbel der über den Brenner 4 zugeführten Verbrennungsluft dargestellt ist. Die Wirbelachsen dieser beiden Luftwirbel stehen im übrigen im wesentlichen senkrecht zur Ebene bzw. Oberfläche 6b des Hitzeschildes 6.The air stream flowing into the annular duct 15 arrives finally into the combustion chamber 1, but should on the way there the particularly highly stressed areas of the Cool heat shield 6 intensively. To do this, this should the air duct exiting the annular duct 15 into the combustion chamber 1 also as a cooling air film on the combustion chamber 1 facing hot surface 6b of the heat shield 6 place, especially in the edge region of the passage opening 8. To achieve this effect, the Air flow in the ring channel impressed a vortex that is in the same direction is with the vortex which is fed via the burner 8 Combustion air. The emerging from the ring channel 15 Cooling air is said to describe a vortex, which has the same direction as the arrows 5 with which the vortex of the combustion air supplied via the burner 4 is shown. The swirl axes of these two Air vortices are essentially vertical to the plane or surface 6b of the heat shield 6.

Um dem aus dem Ringkanal 15 in die Brennkammer 1 austretenden Kühlluftstrom den gewünschten Wirbel aufzuprägen, sind die Luftübertrittsöffnungen 16 nicht zum Zentrum der Durchtrittsöffnung 8 hin gerichtet, sondern sind - wie Fig. 3 zeigt - unter einem Winkel α gegenüber der ins Zentrum 17 der Durchtrittsöffnung 8 weisenden Richtung geneigt.In order from the annular duct 15 into the combustion chamber 1 exiting cooling air flow to impress the desired vortex, are the air transfer openings 16 not to the center of the Passage opening 8 directed, but are - like Fig. 3 shows - at an angle α compared to the ins Center 17 of the passage opening 8 pointing direction inclined.

Der Übergangsbereich zwischen dem Steg 14 sowie der heißen Oberfläche 6b des Hitzeschildes 6 ist als Fase 18 ausgebildet, kann jedoch ebenso abgerundet gestaltet sein. Diese Maßnahme ermöglicht es dem über den Ringkanal 15 zuströmenden Kühlluftstrom, sich unter Beibehaltung seiner Strömungsrichtung als Kühlluftfilm an der Oberfläche 6b des Hitzeschildes 6 anzulegen. Besonders gefördert wird dieses Anlegen des Kühlluftstromes als Kühlluftfilm jedoch dadurch, daß die Drallrichtungen bzw. Wirbelrichtungen des über den Ringkanal 15 geführten Luftstromes sowie des über den Brenner 4 in die Brennkammer 1 eintretenden Verbrennungs-Luftstromes übereinstimmen.The transition area between the web 14 and the hot surface 6b of the heat shield 6 is as a chamfer 18 trained, but can also be rounded be. This measure enables this via the ring channel 15 incoming cooling air flow, maintaining itself its flow direction as a cooling air film on the surface 6b to apply the heat shield 6. Particularly promoted this application of the cooling air flow as a cooling air film however, in that the swirl directions of the air flow guided over the annular duct 15 and that entering the combustion chamber 1 via the burner 4 Combustion air flow match.

Um auch die in radialer Richtung betrachtet weiter außen liegenden Bereiche des Hitzeschildes 6 optimal kühlen zu können, ist das Hitzeschild 6 weiterhin mit Effusionslöchern 19 versehen, die von der Rückseite 6a zur heißen Oberfläche 6b führen und somit den Druchtritt von Kühlluft durch das Hitzeschild 6 ermöglichen. Auch diese über die Effusionslöcher 19 hindurchtretende Kühlluft soll sich als Kühlluftfilm auf der Oberfläche 6b niederschlagen. Um diesen Effekt zu erzielen, sind die Mittelachsen der Effusionslöcher 19 zweifach geneigt. Der erste Neigungswinkel liegt zwischen der Mittelachse der Effusionslöcher und einer Senkrechten auf die Oberfläche 6b des Hitzeschildes 6, was bedeutet, daß die Mittelachsen der Effusionslöcher 19 gegenüber der Oberfläche 6b geneigt sind, so daß der aus einem Effusionsloch 19 austretende Luftstrom zumindest teilweise über die Oberfläche 6b hinwegstreicht. Ein weiterer Neigungswinkel β tritt in einer senkrechten Projektion auf die Oberfläche 6b auf, wobei in dieser Projektion die Mittelachse 20 jedes Effusionsloches geneigt zur Tangente 21 an einen um das Zentrum 17 der Durchtrittsöffnung 8 durch das jeweilige Effusionsloch 19 gelegten Teilkreis 22 ist. Mit dieser beschriebenen, insbesondere aus Fig. 4 ersichtlichen Gestaltung der Effusionslöcher 19 bildet der durch diese Effusionslöcher 19 erzeugte Kühlluftfilm einen Wirbel, der sowohl eine bezüglich des Zentrums 17 radial nach außen gerichtete Geschwindigkeitskomponente VR, als auch eine tangential zum Teilkreis 22 verlaufende Geschwindigkeitskomponente VT aufweist. Dabei ist der Neigungswinkel β derart gewählt, daß die Tangential-Komponente VT gleichgerichtet ist mit dem Wirbel der über den Brenner 4 zugeführten Verbrennungsluft, der durch die Pfeile 5 dargestellt ist. Diese Gleichrichtung der Wirbel stellt sicher, daß sich ein optimal an der Oberfläche 6b anliegender Kühlluftfilm bilden kann.To also look further out in the radial direction lying areas of the heat shield 6 cool optimally can, the heat shield 6 is still with effusion holes 19 provided, which are called from the rear 6a Guide surface 6b and thus the passage of cooling air enable by the heat shield 6. These too cooling air passing through the effusion holes 19 are deposited as a cooling air film on the surface 6b. To achieve this effect, the central axes are of the effusion holes 19 inclined twice. The first angle of inclination lies between the central axis of the effusion holes and a perpendicular to the surface 6b of the Heat shield 6, which means that the central axes of the Effusion holes 19 inclined to the surface 6b are so that the emerging from an effusion hole 19 Air flow at least partially sweeps across surface 6b. Another angle of inclination β occurs in one perpendicular projection onto the surface 6b, whereby in this projection the central axis 20 of each effusion hole inclined to the tangent 21 to one around the center 17 the passage opening 8 through the respective effusion hole 19 placed circle 22 is. With this described, 4 apparent design of the Effusion holes 19 form through these effusion holes 19 generated cooling air film a vortex that both a radially outward with respect to the center 17 Velocity component VR, as well as a tangential speed component extending to the pitch circle 22 VT has. The angle of inclination β is chosen such that that the tangential component VT rectified is with the vortex that supplied via the burner 4 Combustion air, which is represented by the arrows 5. This rectification of the vertebrae ensures that a cooling air film lying optimally on the surface 6b can form.

Beste Ergebnisse werden dann erzielt, wenn der Betrag der radialen Geschwindigkeits-Komponente VR größer ist als derjenige der Tangential-Kompontente VT. Jedoch kann dies sowie weitere Details insbesondere konstruktiver Art durchaus abweichend vom gezeigten Ausführungsbeispiel gestaltet sein, ohne den Inhalt der Patentansprüche zu verlassen.Best results are achieved when the amount of radial velocity component VR is greater than that of the tangential component VT. However, this can as well as further details, particularly of a constructive nature designed quite differently from the embodiment shown be without leaving the content of the claims.

Claims (6)

  1. A heat shield for a combustion chamber, especially for an annular combustion chamber of a gas turbine, with a through hole (8) for a burner (4), whereby the rear side (6a) of the heat shield (6) facing away from the combustion chamber (1) is impacted with cooling air and has a web (14) surrounding the edge of the through hole (8),
    characterised in that the web (14) has a multiplicity of air passage holes (16), which are inclined at an angle (α) to the direction of the through hole (8) into the centre (17) such that a vortex is formed by the flow of air through the air passage holes (16) into an annular channel (15) between the heat shield (6) and the burner (4) and thence out into the combustion chamber (1), which is of the same sense as the vortex (arrows 5), formed by the combustion air introduced via the burners (4), and which has an axis of swirling remaining perpendicular to the surface (6b) of the heat shield (6).
  2. A heat shield according to Claim 1,
    characterised in that the annular channel (15) is bordered by the web (14) of the heat shield (6) and a sealing component (9) surrounding the burner (4).
  3. A heat shield according to Claim 1 or Claim 2,
    characterised in that the transition region between the web (14) and the (hot) surface (6b) facing the combustion chamber (1) ) is formed as a bevel (18) or rounded off.
  4. A heat shield according to one of the foregoing Claims with a multiplicity of effusion holes (19), in the surface (6b) facing the combustion chamber (1) through which the cool air can pass from the rear side (6a), so as to lay a cool air film onto the hot surface (6b),
    characterised in that the central axes (20) of the effusion holes (19) are inclined towards the surface (6b) and are inclined towards the surface (6b) in such a way in each case in a perpendicular projection onto the tangent (21) to an arc of a circle (22) about the centre (17) of the through hole (8) positioned through the effusion hole (19) in question, that the cool air film forms a vortex, which has both a radial speed component (VR), directed outwards with respect to the centre (17) and also a speed component (VT) running tangentially to the arc of the circle (22), whereby the direction of the tangential component (VT) is the same as that of the vortex (arrows 5) of the combustion air introduced via the burner (4).
  5. A heat shield according to Claim 4,
    characterised in that the value of the radial speed component (VR) is greater than that of the tangential component (VT).
  6. A heat shield in accordance with one of the foregoing Claims,
    characterised by bolts (7) by means of which the heat shield (6) is screwed to a front plate (3), also carrying the sealing component (9).
EP95926909A 1994-08-01 1995-07-17 Thermal shield for a gas turbine combustion chamber Expired - Lifetime EP0774100B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE4427222 1994-08-01
DE4427222A DE4427222A1 (en) 1994-08-01 1994-08-01 Heat shield for a gas turbine combustor
PCT/EP1995/002795 WO1996004510A1 (en) 1994-08-01 1995-07-17 Thermal shield for a gas turbine combustion chamber

Publications (2)

Publication Number Publication Date
EP0774100A1 EP0774100A1 (en) 1997-05-21
EP0774100B1 true EP0774100B1 (en) 1998-09-16

Family

ID=6524660

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95926909A Expired - Lifetime EP0774100B1 (en) 1994-08-01 1995-07-17 Thermal shield for a gas turbine combustion chamber

Country Status (5)

Country Link
US (1) US5956955A (en)
EP (1) EP0774100B1 (en)
CA (1) CA2196310C (en)
DE (2) DE4427222A1 (en)
WO (1) WO1996004510A1 (en)

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Also Published As

Publication number Publication date
DE4427222A1 (en) 1996-02-08
US5956955A (en) 1999-09-28
CA2196310C (en) 2006-11-07
DE59503631D1 (en) 1998-10-22
WO1996004510A1 (en) 1996-02-15
CA2196310A1 (en) 1996-02-15
EP0774100A1 (en) 1997-05-21

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