EP0813669A1 - Thermal shield arrangement for gas turbine combustion chambers - Google Patents

Thermal shield arrangement for gas turbine combustion chambers

Info

Publication number
EP0813669A1
EP0813669A1 EP96906722A EP96906722A EP0813669A1 EP 0813669 A1 EP0813669 A1 EP 0813669A1 EP 96906722 A EP96906722 A EP 96906722A EP 96906722 A EP96906722 A EP 96906722A EP 0813669 A1 EP0813669 A1 EP 0813669A1
Authority
EP
European Patent Office
Prior art keywords
heat shield
web
guide rib
combustion chamber
air
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
EP96906722A
Other languages
German (de)
French (fr)
Other versions
EP0813669B1 (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 EP0813669A1 publication Critical patent/EP0813669A1/en
Application granted granted Critical
Publication of EP0813669B1 publication Critical patent/EP0813669B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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

Definitions

  • the invention relates to a heat shield arrangement for a gas turbine combustion chamber with a heat shield with a central passage opening for a burner and with a web running around the edge of the passage opening and having a plurality of air passage openings for the cold rear side of the heat shield facing away from the combustion chamber has introduced cooling air.
  • a heat shield arrangement for a gas turbine combustion chamber with a heat shield with a central passage opening for a burner and with a web running around the edge of the passage opening and having a plurality of air passage openings for the cold rear side of the heat shield facing away from the combustion chamber has introduced cooling air.
  • the present heat shield is preferably provided for an annular combustion chamber.
  • the hot surface must be cooled intensively, for which purpose the usual heat shields have a multiplicity of cooling air passage openings, via which the cooling air flow brought up to the cold rear side of the heat shield can pass through the heat shield and then place a cooling air film on the hot surface of the heat shield.
  • the cooling air flow portion exiting in the area of the passage opening via the gap between a sealing part receiving the burner and the heat shield is also not sufficient for this.
  • the object of the invention is therefore to identify measures by means of which the cooling of the heat shield, in particular in the area of the burner passage opening, can be further improved.
  • the solution to this problem is characterized by a guide rib provided inside the passage opening and oriented essentially parallel to the web, the combustion chamber end of which is angled around the cooling air flow flowing into the gap between the web and guide rib via the air transfer openings in the direction of the hot surface of the heat shield redirect.
  • FIG. 5a shows a further variant
  • FIG. 5b shows the partial section A from FIG. 5a.
  • the cold rear of the heat shield 1 is provided with the reference number 2a, while the hot surface of the heat shield facing the combustion chamber bears the reference number 2b.
  • this heat shield surrounds a burner, not shown, via which a fuel-air stream is introduced into the combustion chamber of the gas turbine.
  • the heat shield has a passage opening 3 for the burner.
  • the burner is surrounded by a sealing part 4.
  • a bolt 5 which protrudes from the heat shield 1 behind the passage opening 3 and serves to fasten the heat shield 1 to the combustion chamber head of the gas turbine.
  • the hot surface 2b of the heat shield must be cooled intensively.
  • a cooling air flow is brought to the cold rear side 2a of the heat shield 1, which (as FIG. 1 shows) can at least partially penetrate through a plurality of bores 6 in the heat shield 1 and - since these bores 6 are inclined with respect to the surface 2b - Lies as a cooling air film on the hot surface 2b of the heat shield 1.
  • a plurality of air transfer openings 7 are likewise provided in a web 8, which is provided at the edge of the passage opening 3, in particular in the area of the rear side 2a. Cooling air can thus get from the rear side 2a into the area of the passage opening 3 via these air transfer openings 7.
  • the web 8 is part of the heat shield 1, and in the other exemplary embodiments the web 8 is part of a separate ring element 11.
  • a guide rib 9 is provided which is oriented essentially parallel to the web 8 and whose end 9a on the combustion side is such it is angled that the cooling air flow is deflected in the direction of the hot surface 2b of the heat shield 1 as shown by the arrow 10.
  • the free end 9a of the guide rib 9 is substantially parallel to the chamfered edge la of the heat shield 1 in the corner region of through opening 3 and hot surface 2b aligned (see. Fig. 1).
  • the guide rib 9 is molded onto a so-called ring element 11, which is arranged between a collar 4 'of the sealing part 4 and the web 8 molded onto the heat shield 1.
  • This ring element 11 can thus be manufactured simply on the one hand and on the other hand simply plugged onto the heat shield 1, which is also easy to manufacture.
  • a ring element 11 is also provided between the collar 4 and the heat shield 1, which in this case forms the web 8 and has the air transfer openings 7.
  • the guide rib 9, which also represents a separate annular component, is also supported on this ring element 11.
  • the air transfer openings 7 in the ring element 11 are provided with swirling devices so that a desired vortex can be impressed on the cooling air flow passing through the air transfer openings 7.
  • 3 shows a similar embodiment with air transfer openings 7 without swirling measures.
  • the guide rib 9 is thus molded onto the heat shield 1.
  • the heat shield 1 with the integrally formed guide rib 9 constitutes a cast part for this purpose.
  • the free end 9a of the guide rib 9 is so far into the Combustion chamber of the gas turbine pulled in that this free end 9a itself is aligned parallel to the hot surface 2b of the heat shield 1. In this way, the one in the annular gap 12 is urgent flow of cooling air is guided particularly safely and reliably onto the heat shield surface 2b.
  • the air transfer bores 7 are again provided with swirling devices, which is represented by the cross grating.
  • FIG. 5a, 5b show a further exemplary embodiment in which the guide rib 9 is molded onto the ring element 11 in a manner similar to the exemplary embodiment according to FIG. 1.
  • the air transfer openings 7 are located in the ring element 11, so that further measures are necessary in order to allow air access to these air transfer openings 7. Therefore, between the ring element 11 and the collar 4 'of the sealing part 4, there is a ring 13 slotted like a gear wheel, the tooth slots 13' of which allow this air access to the air transfer openings 7.
  • a spacer 14 provided with air passage openings 14 ' is shown, by means of which the sealing part 4 with its collar' is supported on the top wall 15 of the combustion chamber.
  • the cooling air flow brought to the side of the web 8 facing away from the combustion chamber ie. H. the cooling air flow must first penetrate the air passage openings 14 'in order to then be able to flow through the air passage openings 7 into the annular gap 12 between the web 8 and the guide rib 9, in order ultimately to lead from this guide rib 9 in the direction of the hot surface 2b of the heat shield 1 to be redirected.

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)
  • Supercharger (AREA)
  • Spray-Type Burners (AREA)

Abstract

In order to cool down as efficiently as possible the hot surface of the thermal shield (1) that surrounds the burner of a gas turbine ring-shaped combustion chamber, in particular in the area of the burner outlet (3), a cooling air flow (10) ejected in the direction of the outlet over a continuous web (8) at the edge of the outlet is guided by a guiding rib (9). The guiding rib (9) is substantially parallel to the web (8) and has at the side of the combustion chamber a bent end, so that the cooling air flow that enters the gap between the web and the guiding rib is deflected there towards the hot surface (2b) of the thermal shield (1).

Description

Hitzeschild-Anordnung für eine Gasturbinen-BrennkammerHeat shield arrangement for a gas turbine combustor
Die Erfindung betrifft eine Hitzeschild-Anordnung für eine Gasturbinen-Brennkammer mit einem Hitzeschild mit einer zentralen Durchtrittsöffnung für einen Brenner so- wie mit einem am Rand der Durchtrittsöffnung umlaufenden Steg, der eine Vielzahl von Luftübertrittsöffnungen für die an die der Brennkammer abgewandte kalte Rückseite des Hitzeschildes herangeführte Kühlluft aufweist. Zum Stand der Technik wird beispielshalber auf die EP 0 471 437 AI verwiesen, dabei ist analog diesem bekannten Stand der Technik auch das vorliegende Hitzeschild bevorzugt für eine Ringbrennkammer vorgesehen.The invention relates to a heat shield arrangement for a gas turbine combustion chamber with a heat shield with a central passage opening for a burner and with a web running around the edge of the passage opening and having a plurality of air passage openings for the cold rear side of the heat shield facing away from the combustion chamber has introduced cooling air. With regard to the prior art, reference is made, for example, to EP 0 471 437 A1, in which case, analogously to this known prior art, the present heat shield is preferably provided for an annular combustion chamber.
Die heiße Oberfläche muß intensiv gekühlt werden, wozu die üblichen Hitzeschilder eine Vielzahl von Kühlluft- Durchtrittsöffnungen aufweisen, über die der an die kalte Rückseite des Hitzeschildes herangeführte Kühlluftstrom durch das Hitzeschild hindurchtreten kann und sodann auf die heiße Oberfläche des Hitzeschildes einen Kühlluftfilm legt. Damit ist es jedoch nicht möglich, den einer beson¬ ders hohen Temperaturbelastung ausgesetzten Ringbereich rund um die Brenner-Durchtrittsöffnung ausreichend zu kühlen. Auch der im Bereich der Durchtrittsöffnung über den Spalt zwischen einem den Brenner aufnehmenden Dich- tungsteil sowie dem Hitzeschild austretende Kühlluft¬ stromanteil reicht hierfür nicht aus. Aufgabe der Erfindung ist es daher, Maßnahmen aufzuzei¬ gen, mit Hilfe derer die Kühlung des Hitzeschildes insbe¬ sondere im Bereich der Brenner-Durchtrittsöffnung weiter verbessert werden kann.The hot surface must be cooled intensively, for which purpose the usual heat shields have a multiplicity of cooling air passage openings, via which the cooling air flow brought up to the cold rear side of the heat shield can pass through the heat shield and then place a cooling air film on the hot surface of the heat shield. However, this means that it is not possible to sufficiently cool the ring area around the burner passage opening which is exposed to a particularly high temperature load. The cooling air flow portion exiting in the area of the passage opening via the gap between a sealing part receiving the burner and the heat shield is also not sufficient for this. The object of the invention is therefore to identify measures by means of which the cooling of the heat shield, in particular in the area of the burner passage opening, can be further improved.
Die Lösung dieser Aufgabe ist gekennzeichnet durch eine innerhalb der Durchtrittsöffnung vorgesehene, im wesentlichen parallel zum Steg ausgerichtete Leitrippe, deren brennkammerseitiges Ende abgewinkelt ist, um den über die Luftübertrittsöffnungen in den Spalt zwischen Steg und Leitrippe einströmenden Kühlluftstrom in Rich¬ tung der heißen Oberfläche des Hitzeschildes umzulenken. Vorteilhafte Aus- und Weiterbildungen sind Inhalt der Unteransprüche.The solution to this problem is characterized by a guide rib provided inside the passage opening and oriented essentially parallel to the web, the combustion chamber end of which is angled around the cooling air flow flowing into the gap between the web and guide rib via the air transfer openings in the direction of the hot surface of the heat shield redirect. Advantageous training and further education are included in the subclaims.
Näher erläutert wird die Erfindung anhand bevorzugter Ausführungsbeispiele. Die Figurendarstellungen 1 bis 4 zeigen Prinzip-Halbschnitte durch jeweils eine erfindungsgemäße Hitzeschild-Anordnung, Fig. 5a zeigt eine weitere Variante und Fig. 5b den Teilschnitt A aus Fig. 5a.The invention is explained in more detail with reference to preferred exemplary embodiments. The figures 1 to 4 show principle half-sections through a heat shield arrangement according to the invention, FIG. 5a shows a further variant and FIG. 5b shows the partial section A from FIG. 5a.
Die kalte Rückseite des Hitzeschildes 1 ist mit der Be¬ zugsziffer 2a versehen, während die der Brennkammer zuge- wandte heiße Oberfläche des Hitzeschildes die Bezugszif¬ fer 2b trägt. Dieses Hitzeschild umgibt wie üblich einen nicht gezeigten Brenner, über den ein Brennstoff-Luft- Strom in die Brennkammer der Gasturbine eingeführt wird. Hierzu weist das Hitzeschild eine Durchtrittsöffnung 3 für den Brenner auf. Ebenfalls wie üblich ist dabei der Brenner von einem Dichtungsteil 4 umgeben. Ferner erkennt man in Figur 1 einen hinter der Durchtrittsöffnung 3 vom Hitzeschild 1 wegragenden Bolzen 5, der der Befestigung des Hitzschildes 1 am Brennkammerkopf der Gasturbine dient. Die heiße Oberfläche 2b des Hitzeschildes muß intensiv gekühlt werden. Hierzu wird an die kalte Rückseite 2a des Hitzeschildes 1 ein Kühlluftstrom herangeführt, der (wie Fig. 1 zeigt) zumindest teilweise über eine Vielzahl von Bohrungen 6 im Hitzeschild 1 dieses durchdringen kann und - da diese Bohrungen 6 gegenüber der Oberfläche 2b ge¬ neigt verlaufen - sich als Kühlluftfilm auf die heiße Oberfläche 2b des Hitzeschildes 1 legt. Ebenfalls mehrere Luftübertrittsöffnungen 7 sind in einem Steg 8 vorgese- hen, der am Rand der Durchtrittsöffnung 3 insbesondere im Bereich der Rückseite 2a vorgesehen ist. über diese Luft¬ übertrittsöffnungen 7 kann somit Kühlluft von der Rück¬ seite 2a in den Bereich der Durchtrittsöffnung 3 gelan¬ gen. Bei den Ausführungsbeispielen nach den Fig. 1, 4 ist der Steg 8 Bestandteil des Hitzeschildes 1, bei den ande¬ ren Ausführungsbeispielen ist der Steg 8 Bestandteil ei¬ nes separaten Ringelementes 11.The cold rear of the heat shield 1 is provided with the reference number 2a, while the hot surface of the heat shield facing the combustion chamber bears the reference number 2b. As usual, this heat shield surrounds a burner, not shown, via which a fuel-air stream is introduced into the combustion chamber of the gas turbine. For this purpose, the heat shield has a passage opening 3 for the burner. As usual, the burner is surrounded by a sealing part 4. Furthermore, one can see in FIG. 1 a bolt 5 which protrudes from the heat shield 1 behind the passage opening 3 and serves to fasten the heat shield 1 to the combustion chamber head of the gas turbine. The hot surface 2b of the heat shield must be cooled intensively. For this purpose, a cooling air flow is brought to the cold rear side 2a of the heat shield 1, which (as FIG. 1 shows) can at least partially penetrate through a plurality of bores 6 in the heat shield 1 and - since these bores 6 are inclined with respect to the surface 2b - Lies as a cooling air film on the hot surface 2b of the heat shield 1. A plurality of air transfer openings 7 are likewise provided in a web 8, which is provided at the edge of the passage opening 3, in particular in the area of the rear side 2a. Cooling air can thus get from the rear side 2a into the area of the passage opening 3 via these air transfer openings 7. In the exemplary embodiments according to FIGS. 1, 4, the web 8 is part of the heat shield 1, and in the other exemplary embodiments the web 8 is part of a separate ring element 11.
Um mit Hilfe dieser über die Luftübertrittsöffnungen 7 den Steg 8 durchdringenden Kühlluft insbesondere den Randbereich des Hitzeschildes 1 in der Umgebung der Durchtrittsöffnung 3 intensiv zu kühlen, ist eine im we¬ sentlichen parallel zum Steg 8 ausgerichtete Leitrippe 9 vorgesehen, deren brennkam erseitiges Ende 9a derart ab- gewinkelt ist, daß der Kühlluftstrom wie durch den Pfeil 10 dargestellt in Richtung der heißen Oberfläche 2b des Hitzeschildes 1 umgelenkt wird. Dabei befindet sich zwi¬ schen dem Steg 8 sowie der Leitrippe 9 ein Ring-Spalt 12, durch den der die Luftübertrittsöffnungen 7 durchdrin- gende Kühlluftstrom geführt wird und schließlich dem ab¬ gewinkelten freien Ende 9a der Leitrippe 9 folgend in Richtung der heißen Oberfläche 2b des Hitzeschildes 1 ab¬ gelenkt wird. Bevorzugt ist das freie Ende 9a der Leitrippe 9 im wesentlichen parallel zur abgeschrägten Kante la des Hitzeschildes 1 im Eckbereich von Durch- trittsoffnung 3 und heißer Oberflache 2b ausgerichtet (vgl. Fig. 1) .In order to use this cooling air, which penetrates the web 8 through the air transfer openings 7, in particular to intensively cool the edge region of the heat shield 1 in the vicinity of the through opening 3, a guide rib 9 is provided which is oriented essentially parallel to the web 8 and whose end 9a on the combustion side is such it is angled that the cooling air flow is deflected in the direction of the hot surface 2b of the heat shield 1 as shown by the arrow 10. There is an annular gap 12 between the web 8 and the guide rib 9 through which the cooling air flow penetrating the air transfer openings 7 is guided and finally following the angled free end 9a of the guide rib 9 in the direction of the hot surface 2b of the heat shield 1 is deflected. Preferably, the free end 9a of the guide rib 9 is substantially parallel to the chamfered edge la of the heat shield 1 in the corner region of through opening 3 and hot surface 2b aligned (see. Fig. 1).
Beim Ausfuhrungsbeispiel nach Fig. 1 ist die Leitrippe 9 an ein sog. Ringelement 11 angeformt, das zwischen einem Bund 4 ' des Dichtungsteiles 4 sowie dem an das Hitzeschild 1 angeformten Steg 8 angeordnet ist. Dieses Ringelement 11 kann somit einerseits einfach gefertigt und andererseits einfach auf das ebenfalls einfach zu fertigende Hitzeschild 1 aufgesteckt werden.In the exemplary embodiment according to FIG. 1, the guide rib 9 is molded onto a so-called ring element 11, which is arranged between a collar 4 'of the sealing part 4 and the web 8 molded onto the heat shield 1. This ring element 11 can thus be manufactured simply on the one hand and on the other hand simply plugged onto the heat shield 1, which is also easy to manufacture.
Beim Ausfuhrungsbeispiel nach Fig. 2 ist ebenfalls zwi¬ schen dem Bund 4 • sowie dem Hitzeschild 1 ein Ringelement 11 vorgesehen, das in diesem Falle den Steg 8 bildet und die Luftubertrittsoffnungen 7 aufweist. An diesem Ring¬ element 11 stutzt sich weiterhin die ein separates eben¬ falls ringförmiges Bauteil darstellende Leitrippe 9 ab. Dabei sind die Luftubertrittsoffnungen 7 im Ringelement 11 mit Verwirbelungseinrichtungen versehen, so daß dem über die Luftubertrittsoffnungen 7 hindurchtretenden Kühlluftstrom ein gewünschter Wirbel aufgeprägt werden kann. Eine ahnliche Ausfuhrungsform mit Luftubertritts¬ offnungen 7 ohne Verwirbelungsmaßnahmen zeigt Fig. 3.In the exemplary embodiment according to FIG. 2, a ring element 11 is also provided between the collar 4 and the heat shield 1, which in this case forms the web 8 and has the air transfer openings 7. The guide rib 9, which also represents a separate annular component, is also supported on this ring element 11. The air transfer openings 7 in the ring element 11 are provided with swirling devices so that a desired vortex can be impressed on the cooling air flow passing through the air transfer openings 7. 3 shows a similar embodiment with air transfer openings 7 without swirling measures.
Beim Ausfuhrungsbeispiel nach Fig. 4 ist nicht nur der Steg 8, sondern auch die Leitrippe 9 selbst Bestandteil des Hitzeschildes 1. Die Leitrippe 9 ist somit an das Hitzeschild 1 angeformt. Insbesondere stellt das Hitzeschild 1 mit der angeformten Leitrippe 9 hierzu ein Gußteil dar. Bei diesem Ausfuhrungsbeispiel nach Fig. 4 ist ebenso wie bei den bereits erläuterten Ausfuhrungs¬ beispielen nach den Fig. 2, 3 das freie Ende 9a der Leitrippe 9 so weit in die Brennkammer der Gasturbine hineingezogen, daß dieses- freie Ende 9a selbst parallel zur heißen Oberflache 2b des Hitzeschildes 1 ausgerichtet ist. Auf diese Weise wird die in den Ring-Spalt 12 ein- dringende Kuhlluftstromung besonders sicher und zuverläs¬ sig auf die Hitzeschild-Oberflache 2b gefuhrt. Im übrigen sind bei diesem Ausfuhrungsbeispiel nach Fig. 4 die Luft- ubertrittsbohrungen 7 abermals mit Verwirbelungseinrich- tungen versehen, was durch das Kreuz-Gitter dargestellt ist.In the exemplary embodiment according to FIG. 4, not only the web 8 but also the guide rib 9 itself is part of the heat shield 1. The guide rib 9 is thus molded onto the heat shield 1. In particular, the heat shield 1 with the integrally formed guide rib 9 constitutes a cast part for this purpose. In this exemplary embodiment according to FIG. 4, as in the already explained exemplary embodiments according to FIGS. 2, 3, the free end 9a of the guide rib 9 is so far into the Combustion chamber of the gas turbine pulled in that this free end 9a itself is aligned parallel to the hot surface 2b of the heat shield 1. In this way, the one in the annular gap 12 is urgent flow of cooling air is guided particularly safely and reliably onto the heat shield surface 2b. Moreover, in this exemplary embodiment according to FIG. 4, the air transfer bores 7 are again provided with swirling devices, which is represented by the cross grating.
Die Fig. 5a, 5b zeigen ein weiteres Ausfuhrungsbeispiel, bei dem die Leitrippe 9 ahnlich dem Ausfuhrungsbeispiel nach Fig. 1 an das Ringelement 11 angeformt ist. Bei die¬ sem Ausfuhrungsbeispiel befinden sich die Luftubertritts¬ offnungen 7 jedoch im Ringelement 11, so daß weitere Ma߬ nahmen erforderlich sind, um einen Luftzutritt zu diesen Luftubertrittsoffnungen 7 zu ermöglichen. Daher ist zwi- sehen dem Ringelement 11 sowie dem Bund 4 ' des Dichtungs¬ teiles 4 ein zahnradartig geschlitzter Ring 13 angeord¬ net, dessen Zahnschlitze 13' diesen Luftzutritt zu den Luftubertrittsoffnungen 7 ermöglichen. Nicht nur bei die¬ sem, sondern auch bei den vorangegangenen Ausfuhrungsbei- spielen ist im übrigen ein mit Luftdurchtrittsoffnungen 14' versehenes Abstandsstuck 14 dargestellt, über das sich das Dichtungsteil 4 mit seinem Bund ' an der Kopf¬ wand 15 der Brennkammer abstutzt. Über die Luftdurch¬ trittsoffnungen 14 • gelangt dabei der herangeführte Kuhl- luftstrom zu der von der Brennkammer abgewandten Seite des Steges 8, d. h. der Kühlluftstrom muß zunächst die Luftdurchtrittsoffnungen 14' durchdringen, um an¬ schließend über die Luftubertrittsoffnungen 7 in den Ring-Spalt 12 zwischen dem Steg 8 und der Leitrippe 9 einströmen zu können, um letztlich von dieser Leitrippe 9 in Richtung der heißen Oberflache 2b des Hitzeschildes 1 umgelenkt zu werden. 5a, 5b show a further exemplary embodiment in which the guide rib 9 is molded onto the ring element 11 in a manner similar to the exemplary embodiment according to FIG. 1. In this exemplary embodiment, however, the air transfer openings 7 are located in the ring element 11, so that further measures are necessary in order to allow air access to these air transfer openings 7. Therefore, between the ring element 11 and the collar 4 'of the sealing part 4, there is a ring 13 slotted like a gear wheel, the tooth slots 13' of which allow this air access to the air transfer openings 7. Not only in this, but also in the previous exemplary embodiments, a spacer 14 provided with air passage openings 14 'is shown, by means of which the sealing part 4 with its collar' is supported on the top wall 15 of the combustion chamber. Via the air passage openings 14, the cooling air flow brought to the side of the web 8 facing away from the combustion chamber, ie. H. the cooling air flow must first penetrate the air passage openings 14 'in order to then be able to flow through the air passage openings 7 into the annular gap 12 between the web 8 and the guide rib 9, in order ultimately to lead from this guide rib 9 in the direction of the hot surface 2b of the heat shield 1 to be redirected.

Claims

Patentansprüche claims
1. Hitzeschild-Anordnung für eine Gasturbinen-Brennkam- mer mit einem Hitzeschild (1) mit einer zentralen1. Heat shield arrangement for a gas turbine combustion chamber with a heat shield (1) with a central one
Durchtrittsöffnung (3) für einen Brenner, sowie mit einem am Rand der Durchtrittsöffnung (3) umlaufenden Steg (8) , der eine Vielzahl von Luftübertrittsöff¬ nungen (7) für die an die der Brennkammer abgewandte kalte Rückseite (2b) des Hitzeschildes (1) herange¬ führte Kühlluft aufweist, gekennzeichnet durch eine innerhalb der Durchtritts¬ öffnung (3) vorgesehene, im wesentlichen parallel zum Steg (8) ausgerichtete Leitrippe (9) , deren brennkammerseitiges Ende (9a) abgewinkelt ist, um den über die Luftübertrittsöffnungen (7) in den Spalt (12) zwischen Steg (8) und Leitrippe (9) ein¬ strömenden Kühlluftstrom in Richtung der heißen Oberfläche (2b) des Hitzeschildes (1) umzulenken.Passage opening (3) for a burner, and with a web (8) running around the edge of the passage opening (3), which has a plurality of air transfer openings (7) for the cold rear side (2b) of the heat shield (1) facing away from the combustion chamber ) has cooling air, characterized by a guide rib (9) provided within the passage opening (3) and oriented essentially parallel to the web (8), the end (9a) of the combustion chamber being angled around which the air passage openings (7 ) deflecting cooling air stream flowing into the gap (12) between the web (8) and the guide rib (9) in the direction of the hot surface (2b) of the heat shield (1).
2. Hitzeschild-Anordnung nach Anspruch 1, dadurch gekennzeichnet, daß die Leitrippe (9) an ein Ringelement (11), das zwischen dem Bund (4') eines den Brenner umgebenden Dichtungsteiles (4) sowie dem Hitzeschild (1) angeordnet ist, angeformt ist oder sich an dem Ringelement (11) abstützt. 2. Heat shield arrangement according to claim 1, characterized in that the guide rib (9) on a ring element (11) which is arranged between the collar (4 ') of a sealing part surrounding the burner (4) and the heat shield (1), is integrally formed or is supported on the ring element (11).
3. Hitzeschild-Anordnung nach Anspruch 2, dadurch gekennzeichnet, daß zwischen dem Ringelement (11) und dem Bund (41) des Dichtungsteiles (4) ein zahnradartig geschlitzter Ring (13) angeordnet ist, wobei die Zahnschlitze (13') einen Luftzutritt zu den Luftübertrittsöffnungen (7) ermöglichen.3. Heat shield arrangement according to claim 2, characterized in that between the ring element (11) and the collar (4 1 ) of the sealing part (4) a gear-like slotted ring (13) is arranged, the tooth slots (13 ') having an air inlet to the air transfer openings (7).
4. Hitzeschild-Anordnung nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß die Luftübertrittsöff¬ nungen (7) mit Verwirbelungseinrichtungen versehen sind.4. Heat shield arrangement according to one of the preceding claims, characterized in that the air transfer openings (7) are provided with swirling devices.
5. Hitzeschild-Anorndung nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, daß die Leitrippe (9) an das Hitzeschild (1) angeformt ist.5. Heat shield arrangement according to one of the preceding claims, characterized in that the guide rib (9) is integrally formed on the heat shield (1).
6. Hitzeschild-Anorndung nach Anspruch 5, dadurch gekennzeichnet, daß das Hitzeschild (1) mit der Leitrippe (9) ein Gußteil ist. 6. heat shield arrangement according to claim 5, characterized in that the heat shield (1) with the guide rib (9) is a casting.
EP96906722A 1995-03-08 1996-03-01 Thermal shield arrangement for gas turbine combustion chambers Expired - Lifetime EP0813669B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19508111A DE19508111A1 (en) 1995-03-08 1995-03-08 Heat shield arrangement for a gas turbine combustor
DE19508111 1995-03-08
PCT/EP1996/000860 WO1996027765A1 (en) 1995-03-08 1996-03-01 Thermal shield arrangement for gas turbine combustion chambers

Publications (2)

Publication Number Publication Date
EP0813669A1 true EP0813669A1 (en) 1997-12-29
EP0813669B1 EP0813669B1 (en) 1999-09-22

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP96906722A Expired - Lifetime EP0813669B1 (en) 1995-03-08 1996-03-01 Thermal shield arrangement for gas turbine combustion chambers

Country Status (5)

Country Link
US (1) US5894732A (en)
EP (1) EP0813669B1 (en)
CA (1) CA2214691A1 (en)
DE (2) DE19508111A1 (en)
WO (1) WO1996027765A1 (en)

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Also Published As

Publication number Publication date
EP0813669B1 (en) 1999-09-22
CA2214691A1 (en) 1996-09-12
DE19508111A1 (en) 1996-09-12
WO1996027765A1 (en) 1996-09-12
US5894732A (en) 1999-04-20
DE59603160D1 (en) 1999-10-28

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