EP0805938A1 - Heat shield for a gas turbine combustion chamber - Google Patents

Heat shield for a gas turbine combustion chamber

Info

Publication number
EP0805938A1
EP0805938A1 EP96902920A EP96902920A EP0805938A1 EP 0805938 A1 EP0805938 A1 EP 0805938A1 EP 96902920 A EP96902920 A EP 96902920A EP 96902920 A EP96902920 A EP 96902920A EP 0805938 A1 EP0805938 A1 EP 0805938A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
effusion
sectors
central axes
combustion chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP96902920A
Other languages
German (de)
French (fr)
Other versions
EP0805938B1 (en
Inventor
William Kwan
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0805938A1 publication Critical patent/EP0805938A1/en
Application granted granted Critical
Publication of EP0805938B1 publication Critical patent/EP0805938B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

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
    • F23R3/50—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, in particular for an annular combustion chamber of a gas turbine, with a passage opening for a burner through which fuel and combustion air enter the combustion chamber with the formation of a swirl, and with a multiplicity of Effusion holes, the central axes of which are inclined to the heat shield surface and can pass through the cooling air from the rear in order to place a film of cooling air on the hot surface.
  • 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 through which fuel and combustion air enter the combustion chamber with the formation of a swirl, and with a multiplicity of Effusion holes, the central axes of which are inclined to the heat shield surface and can pass through the cooling air from the rear in order to place a film of cooling air on the hot surface.
  • the heat shield provided in the head of a combustion chamber serves to protect the dome-shaped combustion chamber head region or the front plate provided therein and the burner itself against the action of the hot gas located in the combustion chamber and against excessive heat radiation.
  • the heat shield itself must be cooled.
  • the usual heat shields have so-called effusion holes, through which cooling air can pass from the rear in order to place a film of cooling air on the hot surface of the heat shield.
  • the object of the invention is to show measures by means of which improved heat shield cooling can be achieved.
  • each corner area of the heat shield is assigned a neighboring surface sector, in which the central axes of the effusion holes are aligned essentially parallel to one another and towards the corner area and the fuel combustion air vortex therein Sector are aligned approximately in sections.
  • FIG. 1 shows the top view of the hot surface of a heat shield according to the invention, while the orientation of the effusion punch center axes is explained in more detail with reference to FIG. 2 in a similar representation.
  • the two figures show the top view of the hot surface 1 a of a heat shield 1 arranged in the head of a gas turbine annular combustion chamber as usual.
  • This heat shield has, as usual, a central passage opening 2 for a burner, which is delimited by a circumferential collar 3.
  • the burner 3 is not shown, but the vortex 4 generated by the burner is shown, under which fuel and combustion air are introduced from the burner into the combustion chamber.
  • the heat shield 1 has a multiplicity of effusion holes 5 through which the cooling air passes through from the cold, not visible rear side of the heat shield the heat shield can get into the gas turbine combustion chamber lying on the side of the viewer of FIGS. 1, 2.
  • These effusion punches 5 are drilled obliquely, ie the central axes 6 of the effusion punches 5 are not perpendicular to the surface la of the heat shield 1, but are inclined towards the surface la.
  • This measure which is known per se, has the effect that at least part of the cooling air flow penetrating the heat shield 1 via the effusion holes 5 lies as a cooling air film on the hot surface 1 a of the heat shield 1, which results in intensive cooling.
  • the central axes 6 of the individual effusion punches 5 are inclined in different ways, as can be seen from the vertical projections of the central axes 6 onto the surface 1 a shown in FIGS. 1, 2, but this is also particularly evident from the elliptical shape of the circular effusion punches 5 results.
  • the major axis of each ellipse coincides with the projection of the central axis 6.
  • the ellipses of the effusion punches are oriented differently in different areas of the surface la.
  • the surface la of the heat shield 1 is divided into four surface sectors 7, each of which is closest to a corner region 8 of the heat shield 1 and in which the central axes 6 of the effusion punches 5 are oriented essentially towards the corner or corner region 8.
  • the individual corner areas 8 and the respectively assigned sectors 7 are identified with the same letters A, B, C, D in parentheses.
  • the four sectors 7 do not cover the entire surface la of the heat shield 1. Rather, there is a transition zone 10 between each two sectors 7, in which effusion perforators 5 are also provided with central axes 6 which are inclined with respect to the surface la and are oriented essentially parallel to one another. Because of the parallel alignment of the effusion hole center axes 6, a separate flow pattern is again formed in each of the transition zones 10 in the cooling air film, which is represented by arrows 11. As can be seen, these cooling air film flow patterns 11 in particular in particular, the heat shield edges lying between the corner regions 8 of the heat shield 1, not specified, are intensively cooled.
  • the alignment of the flow pattern 11 or the effusion hole center axis 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 1 a, the effusion hole central axes 6 enclosing a right angle with one another in the sectors 7 assigned to the adjacent corner regions 8.
  • 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 individual sector edge regions 7 ' are also repeated, as represented by the angle y, in steps of 90 °.
  • 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.
  • a part of the flow patterns 9A to 9D likewise serves to cool the heat shield edge regions, which are located between the heat shield corner regions 8 and are not described in any more detail.
  • the number of the respective effusion holes 5 in the respective sectors 7 or transition zones 10 can be adapted accordingly to the prevailing geometric conditions.
  • optimum cooling can always be achieved by a film of cooling air on the surface of the heat shield. The formation of the cooling air film is not hindered by the burner vortex 4, although - in contrast to the known prior art according to US Pat. No.
  • a heat shield according to the invention is also particularly advantageous in that the effusion punches 5 can be easily mechanically inserted into the heat shield 1 particularly close to the circumferential collar 3 of the passage opening 2, since in this area these effusion punches 5 are essentially tangential to the collar 3 are aligned.

Landscapes

  • 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

Hitzeschild für eine Gasturbinen-Brennkammer Heat shield for a gas turbine combustor
Die Erfindung betrifft ein Hitzeschild für eine Brennkam- mer, insbesondere für eine Ring-Brennkammer einer Gastur¬ bine, mit einer Durchtrittsöffnung für einen Brenner, über den Brennstoff sowie Verbrennungsluft unter Ausbil¬ dung 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 be¬ kannten 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, in particular for an annular combustion chamber of a gas turbine, with a passage opening for a burner through which fuel and combustion air enter the combustion chamber with the formation of a swirl, and with a multiplicity of Effusion holes, the central axes of which are inclined to the heat shield surface and can pass through the cooling air from the rear in order to place a film of cooling air on the hot surface. Regarding the known prior art, reference is made to DE 28 51 666 C2 or to US Pat. No. 5,129,231.
Das im Kopf einer Brennkammer vorgesehene Hitzeschild dient wie bekannt dazu, den domartig ausgebildeten Brenn¬ kammer-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 wer¬ den. Hierzu weisen die üblichen Hitzeschilder sog. Effu- sionslöcher auf, über die Kühlluft von der Rückseite her durchtreten kann, um einen Kühlluftfilm auf die heiße Oberfläche des Hitzeschildes zu legen. Da es jedoch nicht immer möglich ist, sämtliche gefähr¬ deten 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.As is known, the heat shield provided in the head of a combustion chamber serves to protect the dome-shaped combustion chamber head region or the front plate provided therein and the burner itself against the action of the hot gas located in the combustion chamber and against excessive heat radiation. In order to be able to perform this function, the heat shield itself must be cooled. For this purpose, the usual heat shields have so-called effusion holes, through which cooling air can pass from the rear in order to place a film of cooling air on the hot surface of the heat shield. However, since it is not always possible to adequately cool all of the endangered zones of the heat shield according to the known state of the art, the object of the invention is to show measures by means of which improved heat shield cooling can be achieved.
Zur Lösung dieser Aufgabe ist vorgesehen, daß jedem Eck¬ bereich des Hitzeschildes ein nachstliegender Oberflä- chen-Sektor zugeordnet ist, in dem die Mittelachsen der Effusionslöcher im wesentlichen zueinander parallel und zum Eckbereich hin ausgerichtet und dem Brennstoff-Ver¬ brennungsluft-Wirbel in diesem Sektor abschnittsweise an¬ nähernd gleichgerichtet sind. Vorteilhafte Aus- und Wei- terbildungen sind Inhalt der Unteransprüche.To solve this problem, it is provided that each corner area of the heat shield is assigned a neighboring surface sector, in which the central axes of the effusion holes are aligned essentially parallel to one another and towards the corner area and the fuel combustion air vortex therein Sector are aligned approximately in sections. Advantageous training and further education are the content of the subclaims.
Näher erläutert wird die Erfindung anhand eines bevorzug¬ ten Ausführungsbeispieles. Dabei zeigt Fig. 1 die Auf¬ sicht auf die heiße Oberfläche eines erfindungsgemaßen Hitzeschildes, während anhand Fig. 2 in einer gleicharti¬ gen Darstellung die Ausrichtung der Effusionslocher-Mit- telachsen näher erläutert wird.The invention is explained in more detail with reference to a preferred exemplary embodiment. 1 shows the top view of the hot surface of a heat shield according to the invention, while the orientation of the effusion punch center axes is explained in more detail with reference to FIG. 2 in a similar representation.
In den beiden Figuren dargestellt ist die Aufsicht auf die heiße Oberfläche la 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 um¬ laufenden Kragen 3 begrenzt wird. Nicht dargestellt ist der Brenner 3, gezeigt ist jedoch der vom Brenner er¬ zeugte Wirbel 4, unter dem Brennstoff sowie Verbrennungs¬ luft vom Brenner in die Brennkammer eingeleitet wird.The two figures show the top view of the hot surface 1 a of a heat shield 1 arranged in the head of a gas turbine annular combustion chamber as usual. This heat shield has, as usual, a central passage opening 2 for a burner, which is delimited by a circumferential collar 3. The burner 3 is not shown, but the vortex 4 generated by the burner is shown, under which fuel and combustion air are introduced from the burner into the combustion chamber.
Weiterhin weist das Hitzeschild 1 eine Vielzahl von Effu- sionslöchern 5 auf, über die Kuhlluft von der kalten, hier nicht sichtbaren Rückseite des Hitzeschildes durch das Hitzeschild hindurch in die auf der Seite des Be¬ trachters der Figuren 1, 2 liegende Gasturbinen-Brennkam¬ mer gelangen kann. Diese Effusionslocher 5 sind schräg gebohrt, d. h. die Mittelachsen 6 der Effusionslocher 5 stehen nicht senkrecht auf der Oberfläche la des Hitze¬ schildes 1, sondern sind gegenüber der Oberfläche la ge¬ neigt. Diese an sich bekannte Maßnahme bewirkt, daß sich zumindest ein Teil des über die Effusionslocher 5 das Hitzeschild 1 durchdringenden Kühlluftstromes als Kühl- luftfilm auf die heiße Oberfläche la des Hitzeschildes 1 legt, was eine intensive Kühlung zur Folge hat. Dabei sind die Mittelachsen 6 der einzelnen Effusionslocher 5 verschiedenartig geneigt, wie aus den in den Fig. 1, 2 dargestellten senkrechten Projektionen der Mittelachsen 6 auf die Oberfläche la ersichtlich wird, was sich insbe¬ sondere jedoch auch aus der Ellipsenform der an sich kreisförmigen Effusionslocher 5 ergibt. Die größere Hauptachse jeder Ellipse fällt dabei mit der Projektion der Mittelachse 6 zusammen. Wie ersichtlich sind in ver- schiedenen Bereichen der Oberfläche la die Ellipsen der Effusionslocher unterschiedlich ausgerichtet.Furthermore, the heat shield 1 has a multiplicity of effusion holes 5 through which the cooling air passes through from the cold, not visible rear side of the heat shield the heat shield can get into the gas turbine combustion chamber lying on the side of the viewer of FIGS. 1, 2. These effusion punches 5 are drilled obliquely, ie the central axes 6 of the effusion punches 5 are not perpendicular to the surface la of the heat shield 1, but are inclined towards the surface la. This measure, which is known per se, has the effect that at least part of the cooling air flow penetrating the heat shield 1 via the effusion holes 5 lies as a cooling air film on the hot surface 1 a of the heat shield 1, which results in intensive cooling. The central axes 6 of the individual effusion punches 5 are inclined in different ways, as can be seen from the vertical projections of the central axes 6 onto the surface 1 a shown in FIGS. 1, 2, but this is also particularly evident from the elliptical shape of the circular effusion punches 5 results. The major axis of each ellipse coincides with the projection of the central axis 6. As can be seen, the ellipses of the effusion punches are oriented differently in different areas of the surface la.
Im einzelnen ist die Oberfläche la 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 Effusionslocher 5 im we¬ sentlichen zum Eck bzw. Eckbereich 8 hin ausgerichtet sind. Der besseren Erläuterung wegen sind dabei die ein¬ zelnen Eckbereiche 8 sowie die jeweils zugeordneten Sek- toren 7 mit gleichen in Klammern gesetzten Buchstaben A, B, C, D gekennzeichnet.In detail, the surface la of the heat shield 1 is divided into four surface sectors 7, each of which is closest to a corner region 8 of the heat shield 1 and in which the central axes 6 of the effusion punches 5 are oriented essentially towards the corner or corner region 8. For the sake of better explanation, the individual corner areas 8 and the respectively assigned sectors 7 are identified with the same letters A, B, C, D in parentheses.
In jedem Sektor 7 sind somit die Effusionslöcher-Mittel- achsen 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 wirkungs¬ voll gekühlt. Da sich in jedem Sektor 7 aufgrund der im wesentlichen parallelen Ausrichtung der Mittelachsen 6 aller Effusionslocher 5 ein intensives sog. Strömungs¬ muster - dargestellt durch die Pfeile 9A, 9B, 9C, 9D - im Kühlluftfilm ausbildet, gelangt ein ausreichend intensi¬ ver 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 Durchtrittsöff¬ nung 2 hervorgerufenen Wirbel 4 zu behindern, ist weiter¬ hin bezüglich der Ausbildung der Effusionslocher 5 bzw. der Lage der Mittelachsen 6 darauf zu achten, daß die Mittelachsen 6 in jedem Sektor dem Brennstoff-Verbren¬ nungsluft-Wirbel 4 in diesem jeweiligen Sektor 7 ab¬ schnittsweise annähernd gleichgerichtet sind. Insbeson¬ dere sind die Mittelachsen 6 in demjenigen Abschnitt eines Sektors 7 dem Wirbel in diesem Sektor 7 gleichge- richtet, in dem die Effusionslöcher-Mittelachsen 6 im we¬ sentlichen 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 central axis 6 of the effusion holes are thus aligned essentially parallel to one another and oriented towards the respective corner area 8. As a result, the thermally highly stressed and known State of the art - in particular in US Pat. No. 5,129,231 - corner areas which are not sufficiently cooled are cooled extremely effectively. Since an intensive so-called flow pattern - represented by the arrows 9A, 9B, 9C, 9D - forms in the cooling air film in each sector 7 due to the essentially parallel alignment of the center axes 6 of all effusion perforators 5, a sufficiently intensive cooling air flow enters the respective corner areas 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 punches 5 or the position of the central axes 6 that the central axes 6 in each sector are approximately rectified in sections with the fuel combustion air vortex 4 in this respective sector 7. 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 la des Hitzeschildes 1. Vielmehr befindet sich jeweils zwischen zwei Sektoren 7 eine Ubergangszone 10, in der ebenfalls Effusionslocher 5 mit gegenüber der Oberfläche la geneigten sowie im wesentlichen parallel zueinander ausgerichteten Mittelachsen 6 vorgesehen sind. In jeder der ubergangszonen 10 bildet sich somit aufgrund der parallelen Ausrichtung der Effusionslöcher-Mittelach¬ sen 6 wieder ein eigenes Strömungsmuster im Kühlluftfilm aus, das durch Pfeile 11 dargestellt ist. Wie ersichtlich werden durch diese Kühlluftfilm-Stromungsmuster 11 insbe- sondere 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 entire surface la of the heat shield 1. Rather, there is a transition zone 10 between each two sectors 7, in which effusion perforators 5 are also provided with central axes 6 which are inclined with respect to the surface la and are oriented essentially parallel to one another. Because of the parallel alignment of the effusion hole center axes 6, a separate flow pattern is again formed in each of the transition zones 10 in the cooling air film, which is represented by arrows 11. As can be seen, these cooling air film flow patterns 11 in particular in particular, the heat shield edges lying between the corner regions 8 of the heat shield 1, not specified, are intensively cooled.
Die Ausrichtung der Strömungsmuster 11 bzw. der Effu- sionslöcher-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 la 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 glei¬ cher Weise findet sich ein rechter Winkel zwischen den Strömungsmustern 9B und 9C, sowie 9C und 9D sowie zwi¬ schen 9D und 9A. Auch die einzelnen Sektoren-Randbereiche 7' wiederholen sich - wie durch den Winkel y dargestellt - in Schritten von 90°.The alignment of the flow pattern 11 or the effusion hole center axis 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 1 a, the effusion hole central axes 6 enclosing a right angle with one another in the sectors 7 assigned to the adjacent corner regions 8. 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 y, in steps of 90 °.
Was nun die Ausrichtung der Strömungsmuster 11 betrifft, so sind die Effusionslöcher-Mittelachsen 6 in den Uber- gangszonen 10 in Richtung der Winkelhalbierenden des von den Effusionslöcher-Mittelachsen 6 der beiden benachbar- ten Sektoren 7 gebildeten Winkels 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.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 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 ersicht¬ lich 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 größere An- zahl von Effusionslöchern 5 vorzusehen, als in den Ubergangszonen 10. Dabei kann selbstverständlich die Zahl der jeweiligen Effusionslocher 5 in den jeweiligen Sekto¬ ren 7 bzw. ubergangszonen 10 den jeweils vorliegenden geometrischen Verhältnissen entsprechend angepaßt werden. Stets läßt sich mit der gezeigten Ausbildung bzw. Anord¬ nung der Effusionslocher 5 eine optimale Kühlung durch einen Kühlluftfilm auf der Hitzeschild-Oberfläche la er¬ zielen. 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 Kuhlluftfilm-Wirbel auf der Hitzeschild-Oberfläche la einstellt. Diese Tatsache wird besonders offensichtlich, wenn man die Strömungsverhait- nisse in den Grenzbereichen zwischen den einzelnen Sekto¬ ren 7 sowie den benachbarten Ubergangszonen 10 analy¬ siert. Dort nämlich heben sich die einander entgegenge¬ richteten Geschwindigskomponenten auf, so daß sich letzt¬ lich eine im wesentlichen radial von der Durchtrittsoff- nung 2 nach außen, d. h. zum Hitzeschild-Randbereich hin orientierte Kühlluftfilm-Strömung einstellt. Besonders vorteilhaft ist ein erfindungsgemaßes Hitzeschild auch insofern, als daß besonders nahe des umlaufenden Kragens 3 der Durchtrittsöffnung 2 die Effusionslocher 5 einfach maschinell in das Hitzeschild 1 eingebracht werden kön¬ nen, da diese Effusionslocher 5 in diesem Bereich im we¬ sentlichen tangential zum Kragen 3 ausgerichtet sind. Da¬ bei wird trotz dieser tangentialen Ausrichtung kein - im übrigen unerwünschter - Kühlluftfilm-Wirbel erzeugt, da sich gemäß den obigen Erläuterungen eine radial von der Durchtrittsoffnung 2 nach außen orientierte Kuhlluftfilm- Strömung einstellt, hervorgerufen durch die im wesentli¬ chen parallele Ausrichtung der Effusionslöcher-Mittelach¬ sen 6 in den jeweiligen Sektoren 7 sowie den Ubergangszo- nen 10. As can be seen, a part of the flow patterns 9A to 9D likewise serves to cool the heat shield edge regions, which are located between the heat shield corner regions 8 and are not described in any more detail. For this reason too, it is possible, as shown in sectors 7, to number of effusion holes 5 than to be provided in the transition zones 10. Of course, the number of the respective effusion holes 5 in the respective sectors 7 or transition zones 10 can be adapted accordingly to the prevailing geometric conditions. With the design or arrangement of the effusion punches 5 shown, optimum cooling can always be achieved by a film of cooling air on the surface of the heat shield. The formation of the cooling air film is not hindered by the burner vortex 4, although - in contrast to the known prior art according to US Pat. No. 5,129-231 - no cooling air film vortex occurs on the heat shield surface 1a. This fact becomes particularly evident when one analyzes the flow conditions in the border areas between the individual sectors 7 and the adjacent transition zones 10. There, namely, the mutually opposed speed components cancel each other out, so that ultimately a cooling air film flow oriented essentially radially from the opening 2 to the outside, ie towards the edge of the heat shield, is established. A heat shield according to the invention is also particularly advantageous in that the effusion punches 5 can be easily mechanically inserted into the heat shield 1 particularly close to the circumferential collar 3 of the passage opening 2, since in this area these effusion punches 5 are essentially tangential to the collar 3 are aligned. Despite this tangential orientation, no - otherwise undesirable - cooling air film vortex is generated, since, according to the above explanations, a cooling air film flow oriented radially outward from the passage opening 2 occurs, caused by the essentially parallel orientation of the effusion holes -Middle axes 6 in the respective sectors 7 and the transition zones 10.

Claims

Patentansprüche claims
1. Hitzeschild für eine Brennkammer, insbesondere für eine Ring-Brennkammer einer Gasturbine, mit einer Durchtrittsöffnung (2) für einen Brenner, über den Brennstoff sowie Verbrennungsluft unter Ausbildung eines Wirbels (4) in die Brennkammer gelangt, sowie mit einer Vielzahl von Effusionslöchern (5) , deren Mittelachsen (6) zur Hitzeschild-Oberfläche (la) ge¬ neigt sind und über die Kühlluft von der Rückseite her durchtreten kann, um einen Kühlluftfilm auf die heiße Oberfläche (la) zu legen, dadurch gekennzeichnet, daß jedem Eckbereich (8) des Hitzeschildes (1) ein nächstliegender Oberflächen- Sektor (7) zugeordnet ist, in dem die Mittelachsen (6) der Effusionslocher (5) im wesentlichen zueinan¬ der parallel und zum Eckbereich (8) hin ausgerichtet und dem Brennstoff-Verbrennungsluft-Wirbel (4) in diesem Sektor (7) abschnittsweise annähernd gleich¬ gerichtet sind.1.Heat shield for a combustion chamber, in particular for an annular combustion chamber of a gas turbine, with a passage opening (2) for a burner, through which fuel and combustion air get into the combustion chamber to form a swirl (4), and with a large number of effusion holes ( 5), whose central axes (6) are inclined to the heat shield surface (la) and can pass through the cooling air from the rear in order to place a film of cooling air on the hot surface (la), characterized in that each corner area ( 8) of the heat shield (1) is assigned a closest surface sector (7) in which the central axes (6) of the effusion punches (5) are aligned essentially parallel to one another and towards the corner area (8) and the fuel combustion air Vortices (4) in this sector (7) are approximately rectified in sections.
2. Hitzeschild nach Anspruch 1, dadurch gekennzeichnet, daß im dem Eckbereich (8) abgewandten Sektoren-Randbereich (7') die Effusions¬ löcher-Mittelachsen (6) im wesentlichen tangentail zur Brenner-Durchtrittsöffnung (2) ausgerichtet sind.2. Heat shield according to claim 1, characterized in that in the corner area (8) facing away from the sector edge area (7 ') the effusion holes central axes (6) substantially tangentail are aligned with the burner passage opening (2).
3. Hitzeschild nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß jeweils zwischen zwei Sektoren (7) mit zu den Eckbereichen (8) hin ausge¬ richteten Effusionslöcher-Mittelachsen (6) eine Ubergangszone (10) liegt, in der die geneigten Mit¬ telachsen (6) der Effusionslocher (5) im wesentli- chen parallel zueinander in Richtung der Winkel¬ halbierenden des von den Effusionslöcher-Mittelach¬ sen (6) der beiden benachbarten Sektoren (7) gebil¬ deten Winkels (α) ausgerichtet sind.3. Heat shield according to claim 1 or 2, characterized in that a transition zone (10) in which the inclined Mit¬ is between two sectors (7) with towards the corner regions (8) towards effusion hole central axes (6) Tel axes (6) of the effusion punches (5) are aligned essentially parallel to one another in the direction of the bisector of the angle (α) formed by the effusion hole center axes (6) of the two adjacent sectors (7).
4. Hitzeschild nach einem der vorangegangenen Ansprü¬ che, dadurch gekennzeichnet, daß die Anzahl der Effusi¬ onslocher (5) in den Sektoren (7) größer ist als die Anzahl der Effusionslocher (5) in den Ubergangszonen (10).4. Heat shield according to one of the preceding claims, characterized in that the number of effusion punches (5) in the sectors (7) is greater than the number of effusion punches (5) in the transition zones (10).
5. Hitzeschild mit vier Ecken nach einem der vorange¬ gangenen Ansprüche, dadurch gekennzeichnet, daß die Effusionslocher-Mit- telachsen (6) von einander benachbarten Eckbereichen (8) zugeordneten Sektoren (7) miteinander einen rechten Winkel einschließen. 5. Heat shield with four corners according to one of the preceding claims, characterized in that the effusion punch center axes (6) of mutually adjacent corner regions (8) associated sectors (7) enclose a right angle with one another.
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 true EP0805938A1 (en) 1997-11-12
EP0805938B1 EP0805938B1 (en) 1998-10-21

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP96902920A Expired - Lifetime EP0805938B1 (en) 1995-01-26 1996-01-25 Heat shield for a gas turbine combustion chamber

Country Status (5)

Country Link
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
EP0805938B1 (en) 1998-10-21
DE19502328A1 (en) 1996-08-01
WO1996023175A1 (en) 1996-08-01

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