EP0805938B1 - Heat shield for a gas turbine combustion chamber - Google Patents

Heat shield for a gas turbine combustion chamber Download PDF

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Publication number
EP0805938B1
EP0805938B1 EP96902920A EP96902920A EP0805938B1 EP 0805938 B1 EP0805938 B1 EP 0805938B1 EP 96902920 A EP96902920 A EP 96902920A EP 96902920 A EP96902920 A EP 96902920A EP 0805938 B1 EP0805938 B1 EP 0805938B1
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EP
European Patent Office
Prior art keywords
heat shield
effusion holes
central axes
sectors
combustion chamber
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EP96902920A
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German (de)
French (fr)
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EP0805938A1 (en
Inventor
William Kwan
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Rolls Royce Deutschland Ltd and Co KG
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BMW Rolls Royce GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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, especially for an annular combustion chamber of a gas turbine, with a passage opening for a burner, about fuel and combustion air under training of a vortex enters the combustion chamber, as well as a variety of effusion holes, their central axes are inclined to the heat shield surface and over the Cooling air can pass through from the back to one Place cooling air film on the hot surface.
  • a heat shield for a combustion chamber especially for an annular combustion chamber of a gas turbine, with a passage opening for a burner, about fuel and combustion air under training of a vortex enters the combustion chamber, as well as a variety of effusion holes, their central axes are inclined to the heat shield surface and over the Cooling air can pass through from the back to one Place cooling air film on the hot surface.
  • the heat shield provided in the head of a combustion chamber serves, as is known, the dome-shaped combustion chamber head area or the front panel provided therein as well as the burner itself before exposure to the Combustion chamber located hot gas and from excessive To protect heat radiation.
  • the heat shield To perform this function To be able to, the heat shield must be cooled in turn.
  • the usual heat shields have so-called effusion holes on, over the cooling air from the back can pass through a film of cooling air on the hot Lay the surface of the heat shield.
  • each corner region of the heat shield is assigned a surface sector extending into this corner region, the central axes of the effusion holes in these surface sectors being aligned parallel to one another and essentially towards the assigned corner region and the fuel combustion air -Vortices in this sector are approximately rectified in sections, and that the surface sectors are separated from each other by a transition zone with effusion holes, the central axes of which are essentially parallel to one another, the surface sectors together with the transition zones forming the total surface of the heat shield.
  • Advantageous training and further training are included in the subclaims.
  • Embodiment 1 shows the top view of the hot one Surface of a heat shield according to the invention, while using FIG. 2 the alignment of the central axis of the effusion holes in a similar representation is explained in more detail.
  • the top view of the hot surface 1a is shown in the two figures one arranged as usual in the head of a gas turbine annular combustion chamber Heat shield 1.
  • this heat shield has a central one Passage opening 2 for a burner, which is surrounded by a circumferential collar 3 is limited.
  • the burner 3 is not shown, but the one from Burner generated vortices 4, under the fuel and combustion air is introduced into the combustion chamber by the burner.
  • the heat shield 1 has a multiplicity of effusion holes 5, over the cooling air from the cold, not visible back of the Heat shield through the heat shield into the one on the side of the viewer of Figures 1, 2 lying gas turbine combustion chamber can reach.
  • These effusion holes 5 are oblique drilled, d. H.
  • the central axes 6 of the effusion holes 5 are not perpendicular to the surface la of the heat shield 1, but are inclined to the surface la.
  • This measure known per se has the effect that at least part of the over the effusion holes 5 that Heat shield 1 penetrating cooling air flow as a cooling air film on the hot surface 1a of the heat shield 1 sets, which results in intensive cooling.
  • the central axes 6 of the individual effusion holes 5 inclined differently, as from those in FIGS.
  • the surface 1a of the heat shield 1 is in divided four surface sectors 7, each one Corner area 8 of the heat shield 1 are closest and in which the central axes 6 of the effusion holes 5 essentially aligned to the corner or corner area 8 are.
  • the individual are Corner areas 8 and the respectively assigned sectors 7 with the same letters A in parentheses, B, C, D marked.
  • the four sectors 7 do not cover the whole Surface 1a of the heat shield 1. Rather there is a transition zone 10 between two sectors 7, in which also effusion holes 5 with compared to the Surface 1a inclined and substantially parallel aligned center axes 6 are provided.
  • each of the transition zones 10 forms the parallel alignment of the central effusion hole axes 6 again its own flow pattern in the cooling air film , which is represented by arrows 11.
  • the cooling air film flow patterns 11 are particularly affected by these cooling air film flow patterns 11 between the corner areas 8 of the heat shield 1 lying, unspecified heat shield edges intensely chilled.
  • the alignment of the flow patterns 11 or the effusion hole central axes 6 in the transition zones 10 is shown in particular in FIG. 2.
  • the heat shield 1 has four corners or corner areas 8 (A - D). Consequently, there are also four sectors 7 on the surface 1a, the effusion hole central axes 6 enclosing a right angle with one another in the sectors 7 assigned to the corner regions 8 which are adjacent to one another.
  • This is shown in FIG. 2 by the flow patterns 9A to 9D.
  • the flow pattern 9A includes a right angle ⁇ with the flow pattern 9B, in the same way there is a right angle between the flow patterns 9B and 9C, and 9C and 9D, and between 9D and 9A.
  • the effusion hole central axes 6 in the transition zones 10 are aligned in the direction of the bisector of the angle ⁇ formed by the effusion hole central axes 6 of the two adjacent sectors 7.
  • the flow pattern 11 for the transition zone 10 lying above in FIG. 2 thus forms the bisector of the 90 ° angle ⁇ between the flow patterns 9A and 9B. The same naturally applies to the flow patterns 11 in the further transition zones 10.
  • a part of the flow pattern 9A to 9D serves as can be seen also for cooling the between the heat shield corner areas 8 lying, unspecified Heat shield edge areas. For this reason too possible, as shown in sectors 7, a larger number of effusion holes 5 than to provide in the Transition zones 10. Of course, the number of the respective effusion holes 5 in the respective sectors 7 or transition zones 10 the present Geometric conditions are adjusted accordingly. You can always with the training or arrangement shown of the effusion holes 5 through optimal cooling achieve a cooling air film on the heat shield surface 1a. The formation of the cooling air film not hampered by the burner vortex 4, albeit deviates from the known state of the art the US 5,129-231 - no cooling air film vortex on the Heat shield surface 1a sets.
  • a heat shield according to the invention is also advantageous insofar as being particularly close to the surrounding collar 3 of the passage opening 2, the effusion holes 5 simple can be introduced mechanically into the heat shield 1, since these effusion holes 5 essentially in this area are aligned tangentially to the collar 3.

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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 heat shield for a gas turbine annular combustion chamber having a plurality of effusion holes, the central axes of which are inclined towards the heat shield surface and over which cooling air can penetrate from the rear to apply a film of cooling air to the hot surface. The surface is subdivided into sectors and transition areas between the sectors, the central axes of the effusion holes essentially being arranged in parallel to each other in a given sector or transition area. In addition, the central axes of the effusion holes in the sectors are oriented towards the assigned corner area in each case.

Description

Die Erfindung betrifft ein Hitzeschild für eine Brennkammer, insbesondere für eine Ring-Brennkammer einer Gasturbine, mit einer Durchtrittsöffnung für einen Brenner, über den Brennstoff sowie Verbrennungsluft unter Ausbildung eines Wirbels in die Brennkammer gelangt, sowie mit einer Vielzahl von Effusionslöchern, deren Mittelachsen zur Hitzeschild-Oberfläche geneigt sind und über die Kühlluft von der Rückseite her durchtreten kann, um einen Kühlluftfilm auf die heiße Oberfläche zu legen. Zum bekannten Stand der Technik wird auf die DE 28 51 666 C2 oder auf die US 5,129,231 verwiesen.The invention relates to a heat shield for a combustion chamber, especially for an annular combustion chamber of a gas turbine, with a passage opening for a burner, about fuel and combustion air under training of a vortex enters the combustion chamber, as well as a variety of effusion holes, their central axes are inclined to the heat shield surface and over the Cooling air can pass through from the back to one Place cooling air film on the hot surface. To the well-known The prior art is based on DE 28 51 666 C2 or refer to US 5,129,231.

Das im Kopf einer Brennkammer vorgesehene Hitzeschild dient wie bekannt dazu, den domartig ausgebildeten Brennkammer-Kopfbereich bzw. die darin vorgesehene Frontplatte sowie den Brenner selbst 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 die üblichen Hitzeschilder sog. Effusionslöcher auf, über die Kühlluft von der Rückseite her durchtreten kann, um einen Kühlluftfilm auf die heiße Oberfläche des Hitzeschildes zu legen. The heat shield provided in the head of a combustion chamber serves, as is known, the dome-shaped combustion chamber head area or the front panel provided therein as well as the burner itself before exposure to the Combustion chamber located hot gas and from excessive To protect heat radiation. To perform this function To be able to, the heat shield must be cooled in turn. For this purpose, the usual heat shields have so-called effusion holes on, over the cooling air from the back can pass through a film of cooling air on the hot Lay the surface of the heat shield.

Da es jedoch nicht immer möglich ist, sämtliche gefährdeten Zonen des Hitzeschildes nach dem bekannten Stand der Technik ausreichend zu kühlen, hat sich die Erfindung zur Aufgabe gestellt, Maßnahmen aufzuzeigen, mit Hilfe derer eine verbesserte Hitzeschildkühlung erzielt werden kann.
Zur Lösung dieser Aufgabe ist vorgesehen, daß jedem Eckbereich des Hitzeschildes ein sich bis in diesen Eckbereich erstreckender Oberflächen-Sektor zugeordnet ist, wobei die Mittelachsen der Effusionslöcher in diesen Oberflächen-Sektoren zueinander parallel und im wesentlichen zum zugeordneten Eckbereich hin ausgerichtet sowie dem Brennstoff-Verbrennungsluft-Wirbel in diesem Sektor abschnittsweise annähernd gleichgerichtet sind, und daß die Oberflächen-Sektoren durch jeweils eine Übergangszone mit Effusionslöchern, deren Mittelachsen im wesentlichen zueinander parallel verlaufen, voneinander getrennt sind, wobei die Oberflächen-Sektoren zusammen mit den Übergangszonen die Gesamtoberfläche des Hitzeschildes bilden. Vorteilhafte Aus- und Weiterbildungen sind Inhalt der Unteransprüche.However, since it is not always possible to adequately cool all of the endangered zones of the heat shield according to the known prior art, the object of the invention is to demonstrate measures by means of which improved heat shield cooling can be achieved.
To solve this problem, it is provided that each corner region of the heat shield is assigned a surface sector extending into this corner region, the central axes of the effusion holes in these surface sectors being aligned parallel to one another and essentially towards the assigned corner region and the fuel combustion air -Vortices in this sector are approximately rectified in sections, and that the surface sectors are separated from each other by a transition zone with effusion holes, the central axes of which are essentially parallel to one another, the surface sectors together with the transition zones forming the total surface of the heat shield. Advantageous training and further training are included in the subclaims.

Näher erläutert wird die Erfindung anhand eines bevorzugten Ausführungsbeispieles. Dabei zeigt Fig. 1 die Aufsicht auf die heiße Oberfläche eines erfindungsgemäßen Hitzeschildes, während anhand Fig. 2 in einer gleichartigen Darstellung die Ausrichtung der Effusionslöcher-Mittelachsen näher erläutert wird.The invention is explained in more detail with reference to a preferred one Embodiment. 1 shows the top view of the hot one Surface of a heat shield according to the invention, while using FIG. 2 the alignment of the central axis of the effusion holes in a similar representation is explained in more detail.

In den beiden Figuren dargestellt ist die Aufsicht auf die heiße Oberfläche 1a eines wie üblich im Kopf einer Gasturbinen-Ringbrennkammer angeordneten Hitzeschildes 1. Dieses Hitzeschild besitzt wie üblich eine zentrale Durchtrittsöffnung 2 für einen Brenner, die von einem umlaufenden Kragen 3 begrenzt wird. Nicht dargestellt ist der Brenner 3, gezeigt ist jedoch der vom Brenner erzeugte Wirbel 4, unter dem Brennstoff sowie Verbrennungsluft vom Brenner in die Brennkammer eingeleitet wird.The top view of the hot surface 1a is shown in the two figures one arranged as usual in the head of a gas turbine annular combustion chamber Heat shield 1. As usual, this heat shield has a central one Passage opening 2 for a burner, which is surrounded by a circumferential collar 3 is limited. The burner 3 is not shown, but the one from Burner generated vortices 4, under the fuel and combustion air is introduced into the combustion chamber by the burner.

Weiterhin weist das Hitzeschild 1 eine Vielzahl von Effusionslöchern 5 auf, über die Kühlluft von der kalten, hier nicht sichtbaren Rückseite des Hitzeschildes durch das Hitzeschild hindurch in die auf der Seite des Betrachters der Figuren 1, 2 liegende Gasturbinen-Brennkammer gelangen kann. Diese Effusionslöcher 5 sind schräg gebohrt, d. h. die Mittelachsen 6 der Effusionslöcher 5 stehen nicht senkrecht auf der Oberfläche la des Hitzeschildes 1, sondern sind gegenüber der Oberfläche la geneigt. Diese an sich bekannte Maßnahme bewirkt, daß sich zumindest ein Teil des über die Effusionslöcher 5 das Hitzeschild 1 durchdringenden Kühlluftstromes als Kühlluftfilm auf die heiße Oberfläche 1a des Hitzeschildes 1 legt, was eine intensive Kühlung zur Folge hat. Dabei sind die Mittelachsen 6 der einzelnen Effusionslöcher 5 verschiedenartig geneigt, wie aus den in den Fig. 1, 2 dargestellten senkrechten Projektionen der Mittelachsen 6 auf die Oberfläche 1a ersichtlich wird, was sich insbesondere jedoch auch aus der Ellipsenform der an sich kreisförmigen Effusionslöcher 5 ergibt. Die größere Hauptachse jeder Ellipse fällt dabei mit der Projektion der Mittelachse 6 zusammen. Wie ersichtlich sind in verschiedenen Bereichen der Oberfläche 1a die Ellipsen der Effusionslöcher unterschiedlich ausgerichtet.Furthermore, the heat shield 1 has a multiplicity of effusion holes 5, over the cooling air from the cold, not visible back of the Heat shield through the heat shield into the one on the side of the viewer of Figures 1, 2 lying gas turbine combustion chamber can reach. These effusion holes 5 are oblique drilled, d. H. the central axes 6 of the effusion holes 5 are not perpendicular to the surface la of the heat shield 1, but are inclined to the surface la. This measure known per se has the effect that at least part of the over the effusion holes 5 that Heat shield 1 penetrating cooling air flow as a cooling air film on the hot surface 1a of the heat shield 1 sets, which results in intensive cooling. Here are the central axes 6 of the individual effusion holes 5 inclined differently, as from those in FIGS. 1, 2 shown vertical projections of the central axes 6 on the surface 1a, what is particularly apparent but also from the ellipse shape of the itself circular effusion holes 5 results. The bigger one The main axis of each ellipse coincides with the projection the central axis 6 together. As can be seen in different Areas of the surface 1a the ellipses of the Effusion holes aligned differently.

Im einzelnen ist die Oberfläche 1a des Hitzeschildes 1 in vier Oberflächen-Sektoren 7 unterteilt, die jeweils einem Eckbereich 8 des Hitzeschildes 1 nächstliegend sind und in denen die Mittelachsen 6 der Effusionslöcher 5 im wesentlichen zum Eck bzw. Eckbereich 8 hin ausgerichtet sind. Der besseren Erläuterung wegen sind dabei die einzelnen Eckbereiche 8 sowie die jeweils zugeordneten Sektoren 7 mit gleichen in Klammern gesetzten Buchstaben A, B, C, D gekennzeichnet.In detail, the surface 1a of the heat shield 1 is in divided four surface sectors 7, each one Corner area 8 of the heat shield 1 are closest and in which the central axes 6 of the effusion holes 5 essentially aligned to the corner or corner area 8 are. For the sake of better explanation, the individual are Corner areas 8 and the respectively assigned sectors 7 with the same letters A in parentheses, B, C, D marked.

In jedem Sektor 7 sind somit die Effusionslöcher-Mittelachsen 6 im wesentlichen parallel zueinander ausgerichtet und zum jeweiligen Eckbereich 8 hin orientiert. Hierdurch werden die thermisch hochbelasteten und beim bekannten Stand der Technik - insbesondere bei der US 5,129,231 - nicht ausreichend gekühlten Eckbereiche äußerst wirkungsvoll gekühlt. Da sich in jedem Sektor 7 aufgrund der im wesentlichen parallelen Ausrichtung der Mittelachsen 6 aller Effusionslöcher 5 ein intensives sog. Strömungsmuster - dargestellt durch die Pfeile 9A, 9B, 9C, 9D - im Kühlluftfilm ausbildet, gelangt ein ausreichend intensiver Kühlluftstrom in die jeweiligen Eckbereiche 8 (A - D).
Um die Ausbildung der jeweiligen Strömungsmuster 9A, 9B, 9C, 9D nicht durch den vom Brenner in der Durchtrittsöffnung 2 hervorgerufenen Wirbel 4 zu behindern, ist weiterhin bezüglich der Ausbildung der Effusionslöcher 5 bzw. der Lage der Mittelachsen 6 darauf zu achten, daß die Mittelachsen 6 in jedem Sektor dem Brennstoff-Verbrennungsluft-Wirbel 4 in diesem jeweiligen Sektor 7 abschnittsweise annähernd gleichgerichtet sind. Insbesondere sind die Mittelachsen 6 in demjenigen Abschnitt eines Sektors 7 dem Wirbel in diesem Sektor 7 gleichgerichtet, in dem die Effusionslöcher-Mittelachsen 6 im wesentlichen tangential zur Brenner-Durchtrittsöffnung 2 ausgerichtet sind. Wie ersichtlich handelt es sich dabei um einen Sektoren-Randbereich 7', der dem zugeordneten Eckbereich 8 abgewandt ist.In each sector 7, the effusion hole central axes 6 are thus aligned essentially parallel to one another and oriented towards the respective corner area 8. As a result, the thermally highly stressed corner areas, which are not sufficiently cooled in the known prior art - in particular in US Pat. No. 5,129,231 - are cooled extremely effectively. Since an intensive so-called flow pattern - represented by the arrows 9A, 9B, 9C, 9D - is formed in the cooling air film in each sector 7 due to the substantially parallel alignment of the center axes 6 of all effusion holes 5, a sufficiently intensive cooling air flow reaches the respective corner regions 8 (A - D).
In order not to impede the formation of the respective flow patterns 9A, 9B, 9C, 9D by the vortex 4 caused by the burner in the passage opening 2, care must also be taken with regard to the formation of the effusion holes 5 or the position of the central axes 6 that the central axes 6 in each sector the fuel-combustion air vortex 4 in this respective sector 7 are approximately rectified in sections. In particular, the central axes 6 in that section of a sector 7 are aligned with the vortex in this sector 7 in which the effusion hole central axes 6 are oriented essentially tangentially to the burner passage opening 2. As can be seen, this is a sector edge area 7 ′ which faces away from the assigned corner area 8.

Die vier Sektoren 7 bedecken jedoch nicht die gesamte Oberfläche 1a des Hitzeschildes 1. Vielmehr befindet sich jeweils zwischen zwei Sektoren 7 eine Übergangszone 10, in der ebenfalls Effusionslöcher 5 mit gegenüber der Oberfläche 1a geneigten sowie im wesentlichen parallel zueinander ausgerichteten Mittelachsen 6 vorgesehen sind. In jeder der Übergangszonen 10 bildet sich somit aufgrund der parallelen Ausrichtung der Effusionslöcher-Mittelachsen 6 wieder ein eigenes Strömungsmuster im Kühlluftfilm aus, das durch Pfeile 11 dargestellt ist. Wie ersichtlich werden durch diese Kühlluftfilm-Strömungsmuster 11 insbesondere die zwischen den Eckbereichen 8 des Hitzeschildes 1 liegenden, nicht näher bezeichneten Hitzeschild-Ränder intensivst gekühlt.However, the four sectors 7 do not cover the whole Surface 1a of the heat shield 1. Rather there is a transition zone 10 between two sectors 7, in which also effusion holes 5 with compared to the Surface 1a inclined and substantially parallel aligned center axes 6 are provided. Thus, in each of the transition zones 10 forms the parallel alignment of the central effusion hole axes 6 again its own flow pattern in the cooling air film , which is represented by arrows 11. As can be seen are particularly affected by these cooling air film flow patterns 11 between the corner areas 8 of the heat shield 1 lying, unspecified heat shield edges intensely chilled.

Die Ausrichtung der Strömungsmuster 11 bzw. der Effusionslöcher-Mittelachsen 6 in den Übergangszonen 10 geht insbesondere aus Fig. 2 hervor. Wie ersichtlich besitzt das Hitzeschild 1 vier Ecken bzw. Eckbereiche 8 (A - D). Folglich befinden sich auf der Oberfläche 1a auch vier Sektoren 7, wobei die Effusionslöcher-Mittelachsen 6 in den einander benachbarten Eckbereichen 8 zugeordneten Sektoren 7 miteinander einen rechten Winkel einschließen. Dargestellt ist dies in Fig. 2 durch die Strömungsmuster 9A bis 9D. So schließt das Strömungsmuster 9A mit dem Strömungsmuster 9B einen rechten Winkel α ein, in gleicher Weise findet sich ein rechter Winkel zwischen den Strömungsmustern 9B und 9C, sowie 9C und 9D sowie zwischen 9D und 9A. Auch die einzelnen Sektoren-Randbereiche 7' wiederholen sich - wie durch den Winkel γ dargestellt - in Schritten von 90°.
Was nun die Ausrichtung der Strömungsmuster 11 betrifft, so sind die Effusionslöcher-Mittelachsen 6 in den Übergangszonen 10 in Richtung der Winkelhalbierenden des von den Effusionslöcher-Mittelachsen 6 der beiden benachbarten Sektoren 7 gebildeten Winkels α ausgerichtet. Das Strömungsmuster 11 für die in Fig. 2 obenliegende Übergangszone 10 bildet somit die Winkelhalbierende des 90°-Winkels α zwischen den Strömungsmuster 9A und 9B. Analoges gilt selbstverständlich für die Strömungsmuster 11 in den weiteren Übergangszonen 10.The alignment of the flow patterns 11 or the effusion hole central axes 6 in the transition zones 10 is shown in particular in FIG. 2. As can be seen, the heat shield 1 has four corners or corner areas 8 (A - D). Consequently, there are also four sectors 7 on the surface 1a, the effusion hole central axes 6 enclosing a right angle with one another in the sectors 7 assigned to the corner regions 8 which are adjacent to one another. This is shown in FIG. 2 by the flow patterns 9A to 9D. Thus, the flow pattern 9A includes a right angle α with the flow pattern 9B, in the same way there is a right angle between the flow patterns 9B and 9C, and 9C and 9D, and between 9D and 9A. The individual sector edge regions 7 'are also repeated, as represented by the angle γ, in steps of 90 °.
With regard to the alignment of the flow patterns 11, the effusion hole central axes 6 in the transition zones 10 are aligned in the direction of the bisector of the angle α formed by the effusion hole central axes 6 of the two adjacent sectors 7. The flow pattern 11 for the transition zone 10 lying above in FIG. 2 thus forms the bisector of the 90 ° angle α between the flow patterns 9A and 9B. The same naturally applies to the flow patterns 11 in the further transition zones 10.

Ein Teil der Strömungsmuster 9A bis 9D dient wie ersichtlich ebenfalls zur Kühlung der zwischen den Hitzeschild-Eckbereichen 8 liegenden, nicht näher bezeichneten Hitzeschild-Randbereiche. Auch aus diesem Grunde ist es möglich, wie gezeigt in den Sektoren 7 eine großere Anzahl von Effusionslöchern 5 vorzusehen, als in den Übergangszonen 10. Dabei kann selbstverständlich die Zahl der jeweiligen Effusionslöcher 5 in den jeweiligen Sektoren 7 bzw. Übergangszonen 10 den jeweils vorliegenden geometrischen Verhältnissen entsprechend angepaßt werden. Stets läßt sich mit der gezeigten Ausbildung bzw. Anordnung der Effusionslöcher 5 eine optimale Kühlung durch einen Kühlluftfilm auf der Hitzeschild-Oberfläche 1a erzielen. Dabei wird die Ausbildung des Kühlluftfilmes nicht durch den Brenner-Wirbel 4 behindert, wenngleich sich - abweichend vom bekannten Stand der Technik nach der US 5,129-231 - kein Kühlluftfilm-Wirbel auf der Hitzeschild-Oberfläche 1a einstellt. Diese Tatsache wird besonders offensichtlich, wenn man die Strömungsverhältnisse in den Grenzbereichen zwischen den einzelnen Sektoren 7 sowie den benachbarten Übergangszonen 10 analysiert. Dort nämlich heben sich die einander entgegengerichteten Geschwindigskomponenten auf, so daß sich letztlich eine im wesentlichen radial von der Durchtrittsöffnung 2 nach außen, d. h. zum Hitzeschild-Randbereich hin orientierte Kühlluftfilm-Strömung einstellt. Besonders vorteilhaft ist ein erfindungsgemäßes Hitzeschild auch insofern, als daß besonders nahe des umlaufenden Kragens 3 der Durchtrittsöffnung 2 die Effusionslöcher 5 einfach maschinell in das Hitzeschild 1 eingebracht werden können, da diese Effusionslöcher 5 in diesem Bereich im wesentlichen tangential zum Kragen 3 ausgerichtet sind. Dabei wird trotz dieser tangentialen Ausrichtung kein - im übrigen unerwünschter - Kühlluftfilm-Wirbel erzeugt, da sich gemäß den obigen Erläuterungen eine radial von der Durchtrittsöffnung 2 nach außen orientierte Kühlluftfilm-Strömung einstellt, hervorgerufen durch die im wesentlichen parallele Ausrichtung der Effusionslöcher-Mittelachsen 6 in den jeweiligen Sektoren 7 sowie den Übergangszonen 10.A part of the flow pattern 9A to 9D serves as can be seen also for cooling the between the heat shield corner areas 8 lying, unspecified Heat shield edge areas. For this reason too possible, as shown in sectors 7, a larger number of effusion holes 5 than to provide in the Transition zones 10. Of course, the number of the respective effusion holes 5 in the respective sectors 7 or transition zones 10 the present Geometric conditions are adjusted accordingly. You can always with the training or arrangement shown of the effusion holes 5 through optimal cooling achieve a cooling air film on the heat shield surface 1a. The formation of the cooling air film not hampered by the burner vortex 4, albeit deviates from the known state of the art the US 5,129-231 - no cooling air film vortex on the Heat shield surface 1a sets. That fact will especially obvious when you look at the flow conditions in the border areas between the individual sectors 7 and the adjacent transition zones 10 are analyzed. There the opposing ones rise up Speed components on, so that ultimately one essentially radially from the passage opening 2 outwards, d. H. towards the edge of the heat shield oriented cooling air film flow. Especially A heat shield according to the invention is also advantageous insofar as being particularly close to the surrounding collar 3 of the passage opening 2, the effusion holes 5 simple can be introduced mechanically into the heat shield 1, since these effusion holes 5 essentially in this area are aligned tangentially to the collar 3. Here despite this tangential alignment, no - in other undesirable - cooling air film vortex generated because radially from the Passage opening 2 outwardly oriented cooling air film flow sets, caused by the essentially parallel alignment of the effusion hole center axes 6 in the respective sectors 7 and the transition zones 10th

Claims (5)

  1. A heat shield for a combustion chamber, especially for an annular combustion chamber of a gas turbine, with a through opening (2) for a burner, via which fuel as well as combustion air reaches the combustion chamber, forming a swirl (4) in the combustion chamber, and with a multiplicity of effusion holes (5), whose central axes (6) are inclined to the surface of the heat shield (1a) and through which the cooling air from the rear side can penetrate, so as to lay a cooling air film onto the hot surface(1a),
    characterised in that each corner area (8) of the heat shield (1) is allocated a surface sector (7) extending into this corner area (8), whereby the central axes (6) of the effusion holes (5) in these surface sectors (7) are aligned parallel to each other and essentially towards the associated corner area (8) as well as approximately in the same direction as the fuel-combustion air swirl (4) in each sector (7),
    and that the surface sectors (7) are separated in each case from each other by a transition zone (10) with effusion holes (5) whose central axes (6) run essentially parallel to each other, whereby the surface sectors (7) together with the transition zones (10) form the entire surface of the heat shield.
  2. A heat shield according to Claim 1,
    characterised in that, in the border area (7') away from the corner area (8), the central axes (6) of the effusion holes are aligned essentially tangential to the burner through opening (2).
  3. A heat shield according to Claim 1 or Claim 2,
    characterised in that in the transition zones (10) the inclined central axes (6) of the effusion holes (5) are aligned essentially in the direction of the angle bisecting the angle (α) formed by the central axes (6) of the effusion holes in the two adjacent sectors (7).
  4. A heat shield according to one of the foregoing Claims,
    characterised in that the number of effusion holes (5) in the sectors (7) is larger than the number of effusion holes (8) in the transition zones (10).
  5. A heat shield with four corners in accordance with one of the foregoing Claims,
    characterised in that the central axes (6) of the effusion holes (5) in the sectors (7) allocated to adjacent corner areas (8) include a right angle between each other.
EP96902920A 1995-01-26 1996-01-25 Heat shield for a gas turbine combustion chamber Expired - Lifetime EP0805938B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19502328 1995-01-26
DE19502328A DE19502328A1 (en) 1995-01-26 1995-01-26 Heat shield for a gas turbine combustor
PCT/EP1996/000300 WO1996023175A1 (en) 1995-01-26 1996-01-25 Heat shield for a gas turbine combustion chamber

Publications (2)

Publication Number Publication Date
EP0805938A1 EP0805938A1 (en) 1997-11-12
EP0805938B1 true EP0805938B1 (en) 1998-10-21

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EP96902920A Expired - Lifetime EP0805938B1 (en) 1995-01-26 1996-01-25 Heat shield for a gas turbine combustion chamber

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US (1) US5918467A (en)
EP (1) EP0805938B1 (en)
CA (1) CA2209317C (en)
DE (2) DE19502328A1 (en)
WO (1) WO1996023175A1 (en)

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Also Published As

Publication number Publication date
CA2209317C (en) 2007-03-20
CA2209317A1 (en) 1996-08-01
US5918467A (en) 1999-07-06
DE59600704D1 (en) 1998-11-26
EP0805938A1 (en) 1997-11-12
DE19502328A1 (en) 1996-08-01
WO1996023175A1 (en) 1996-08-01

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