EP1351022B1 - Air passage for turbine combustor with shingles - Google Patents

Air passage for turbine combustor with shingles Download PDF

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Publication number
EP1351022B1
EP1351022B1 EP03001782A EP03001782A EP1351022B1 EP 1351022 B1 EP1351022 B1 EP 1351022B1 EP 03001782 A EP03001782 A EP 03001782A EP 03001782 A EP03001782 A EP 03001782A EP 1351022 B1 EP1351022 B1 EP 1351022B1
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EP
European Patent Office
Prior art keywords
combustion chamber
air hole
tile
gas turbine
shingle
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Expired - Fee Related
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EP03001782A
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German (de)
French (fr)
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EP1351022A3 (en
EP1351022A2 (en
Inventor
Miklos Dr.-Ing. Gerendas
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Rolls Royce Deutschland Ltd and Co KG
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Rolls Royce Deutschland Ltd and Co KG
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Publication of EP1351022A3 publication Critical patent/EP1351022A3/en
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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/002—Wall structures
    • 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

Definitions

  • the invention relates to a gas turbine combustor having combustor shingles, the combustor shingles being affixed to a support structure of the gas turbine combustor and each having at least one mixing air hole disposed in alignment with a mixing air hole of the support structure.
  • the constructions known from the prior art are designed such that the diameter of the mixing air hole of the support structure (shingle support) is at most slightly larger than the diameter of the mixing air hole of the combustion chamber shingle.
  • the size difference is used in the prior art only to ensure that in the worst case combination of all manufacturing and assembly tolerances of the edge of the mixing air hole of the combustion chamber shingle is not surmounted by the edge of the mixing air hole of the support structure.
  • the US-A1-4132066 describes a gas turbine combustor with combustor shingles attached to a support structure.
  • the support structure and the combustion chamber shingle each have a recess into which a toroidal component is inserted, which introduces the cooling air through its annular structure and thereby completely seals the gap between the support structure and the combustion chamber shingle or separates from the cooling air flowing into the combustion chamber.
  • the GB-A-2353589 which forms the closest prior art, describes a gas turbine combustor having combustor shingles each provided with at least one mixing air hole. This is smaller in diameter than the associated diameter of a mixed air hole of the support structure.
  • the combustion chamber shingles are sealed by a wide flange directly to the support structure, so that the cooling air is passed during operation directly into the combustion chamber.
  • the invention is based on the object to provide a gas turbine combustor with combustor shingles of the type mentioned, which has a simple design, simple, cost-effective manufacturability and ease of assembly has a long life and avoids overheating of the entire construction.
  • the diameter of the mixing air hole of the support structure is significantly larger than the diameter of the mixing air hole of the combustion chamber shingle.
  • the embodiment of the invention is characterized by a number of significant advantages.
  • the shingle edge seen from the outside of the support structure, is clearly visible in the free diameter of the mixed-air hole. This creates a dynamic pressure on the thickened shingle edge. Furthermore, the flow coefficient becomes of the mixed air hole increased. If, during operation, a gap occurs between the shingle edge and that of the support structure, then the above-mentioned back pressure counteracts an outflow of cooling air from the shingle interior. With appropriate choice of the diameter of the mixing air hole of the support structure of the back pressure on the shingle edge is equal to the pressure in the shingled interior. Thus, a leakage of cooling air from the shingled interior is completely prevented.
  • the diameter of the mixing air hole of the support structure and the mixing air hole of the combustion chamber shingle can be achieved by the strong dynamic pressure on the thickened edge of the combustion chamber shingles when a gap between the combustion chamber shingle and the support structure, which is caused by overheating of the shingle , Additional cooling air flows from the mixing air hole in the shingled interior and thus intensifies the cooling of the combustion chamber shingles.
  • an adaptive cooling is thus realized, in which the amount of cooling air is automatically adapted to the temperature load of the combustion chamber shingle.
  • the thickened edge of the combustion chamber shingle is cooled by a separate pattern of effusion holes.
  • the effusion holes can start on the back of the surface of the combustion chamber shingle or in the shingle edge, where they can enter on the shingle interior or the supporting structure side facing.
  • the effusion holes end on the surface of the combustion chamber shingle or on the inside of the mixing hole of the combustion chamber shingle.
  • the effusion holes may be without or with a peripheral component around the axis of the mixing air hole to. Hot gas side of the combustion chamber shingle run.
  • the amount of cooling air in the initial state of the gas turbine combustor can be chosen so that it is just sufficient for normal operation.
  • the maximum amount of air is available for the reduction of harmful gas.
  • the cooling is automatically increased, so that a long-lasting and safe operation is possible.
  • the Fig. 1 shows a schematic side sectional view of a known from the prior art gas turbine combustor.
  • a cover 1 of a combustion chamber head is shown.
  • the reference numeral 2 designates a base plate, combustion chamber shingles are designated by the reference numeral 3.
  • the combustion chamber shingles 3 have mixing air holes 4 and are fastened to a support structure 6.
  • the reference numeral 5 denotes a heat shield with a hole for a burner 8.
  • a turbine vane 9 is shown schematically.
  • Reference numeral 10 denotes a vane in the compressor outlet.
  • a combustion chamber outer housing 11 and a combustion chamber inner housing 12 delimits the combustion chamber.
  • Fig. 2a and 2b show the configuration of a mixing air hole 4 of the combustion chamber shingle 3 and a corresponding mixing air hole of the support structure 6 according to the prior art. It can be seen that the diameter 13 of the mixing air hole of the support structure 6 is slightly larger than the diameter 14 of the mixing air hole 4 of the combustion chamber shingle 3. Off Fig. 2b it can be seen that the air flow 15 in the mixing air hole 4 additionally draws air from the shingle interior.
  • Fig. 3a and 3b show the inventive design in an analogous representation to the Fig. 2a and 2b , It can be seen that the diameter 13 of the mixing air hole of the support structure 6 is significantly or significantly greater than the diameter 14 of the mixing air hole 4 of the combustion chamber shingle 3. From the Fig. 3b It can be seen that a back pressure of Air flow 15 leads to an additional inflow of cooling air into the shingled interior, as soon as a gap between the support structure 6 and the shingle edge 7 is formed.
  • the Fig. 4a shows an enlarged view of a portion of a combustion chamber shingle 3. It can be seen that 4 additional effusion holes 16 are provided by the shingle edge 7 in the region of the mixing air hole to supply cooling air from the shingled interior for cooling the combustion chamber shingle 3. As can be seen, the effusion holes 16 may be arranged in a different orientation to the plane of the combustion chamber shingle 3.
  • the effusion hole 16a is arranged at a very shallow angle, while the effusion holes 16b and 16d extend through the shingle edge 7 and are oriented at a greater angle to the main plane of the combustion chamber shingle 3.
  • the effusion hole 16e extends almost perpendicular to the main plane of the combustion chamber shingle 3 and flows through the shingle edge. 7
  • the Fig. 4b shows two different embodiments of the effusion holes 16 in the plan view of the mixing air hole 4 of the combustion chamber shingles 3.
  • the effusion holes are each arranged radially (regardless of the respective angle of inclination according to FIG Fig. 4a ), while in the right figure the Fig. 4b in addition, a tangential component about the axis of the mixing air hole or a tangential arrangement of the effusion holes 16 is realized. This allows a particularly efficient cooling done.

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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)

Description

Die Erfindung bezieht sich auf eine Gasturbinenbrennkammer mit Brennkammerschindeln, wobei die Brennkammerschindeln an einer Tragstruktur der Gasturbinenbrennkammer befestigt sind und jeweils zumindest ein Mischluftloch aufweisen, welches fluchtend zu einem Mischluftloch der Tragstruktur angeordnet ist.The invention relates to a gas turbine combustor having combustor shingles, the combustor shingles being affixed to a support structure of the gas turbine combustor and each having at least one mixing air hole disposed in alignment with a mixing air hole of the support structure.

Aus dem Stand der Technik ist es bekannt, Schindeln in Gasturbinenbrennkammern einzusetzen, um die Trag- und Dichtstruktur vor der intensiven Wärmeeinstrahlung der Flamme zu schützen. Die Tragstruktur bleibt dadurch relativ kühl und behält ihre mechanische Festigkeit. Demgemäß ist es erforderlich, Mischluft durch ein Mischluftloch in der Tragstruktur sowie durch ein Mischluftloch der Brennkammerschindel von außen von einem Ringkanal nach innen in die Brennkammer zu führen.From the prior art, it is known to use shingles in gas turbine combustors to protect the support and sealing structure from the intense heat radiation of the flame. The support structure remains relatively cool and retains its mechanical strength. Accordingly, it is necessary to guide mixed air through a mixing air hole in the support structure and through a mixing air hole of the combustion chamber shingle from the outside of an annular channel inwardly into the combustion chamber.

Derartige Konstruktionen sind beispielsweise aus der US 6,145,319 oder EP 972 992 A2 bekannt.Such constructions are for example from the US 6,145,319 or EP 972 992 A2 known.

Die aus dem Stand der Technik bekannten Konstruktionen sind so ausgebildet, dass der Durchmesser des Mischluftloches der Tragstruktur (Schindelträger) höchstens geringfügig größer ist, als der Durchmesser des Mischluftlochs der Brennkammerschindel. Der Größenunterschied dient beim Stand der Technik nur dazu, sicherzustellen, dass bei der ungünstigsten Kombination aller Fertigungs- und Montagetoleranzen der Rand des Mischluftlochs der Brennkammerschindel nicht vom Rand des Mischluftlochs der Tragstruktur überragt wird.The constructions known from the prior art are designed such that the diameter of the mixing air hole of the support structure (shingle support) is at most slightly larger than the diameter of the mixing air hole of the combustion chamber shingle. The size difference is used in the prior art only to ensure that in the worst case combination of all manufacturing and assembly tolerances of the edge of the mixing air hole of the combustion chamber shingle is not surmounted by the edge of the mixing air hole of the support structure.

Falls nun während des Betriebes ein Spalt zwischen dem Schindelrand und der Tragstruktur auftritt, entweicht durch diesen wegen der großen Druckdifferenz zwischen dem Schindelinnenraum und dem Mischluftloch relativ viel Kühlluft.If now during operation, a gap between the shingle edge and the support structure occurs escapes through this relatively large amount of cooling air due to the large pressure difference between the shingled interior and the mixing air hole.

Um zu verhindern, dass durch die dabei auftretende Überhitzung die Brennkammerschindel vorzeitig versagt, muss deutlich mehr Kühlluft durch die Brennkammerschindel geleitet werden. Diese zusätzliche Kühlluft steht somit nicht mehr für eine Verbesserung der Brennstoffaufbereitung und der damit verbundenen Stickoxidemissionsverminderung zur Verfügung.In order to prevent the combustion chamber shingle from prematurely failing as a result of the overheating occurring, significantly more cooling air must be conducted through the combustion chamber shingle. This additional cooling air is thus no longer available for an improvement of the fuel processing and the associated reduction of nitrogen oxide emission.

Die US-A1-4132066 beschreibt eine Gasturbinenbrennkammer mit Brennkammerschindeln, welche an einer Tragstruktur befestigt sind. Die Tragstruktur sowie die Brennkammerschindel weisen jeweils eine Ausnehmung auf, in welche ein torusförmiges Bauelement eingesetzt ist, welches durch seine ringförmige Struktur die Kühlluft einführt und dabei den Zwischenraum zwischen der Tragstruktur und der Brennkammerschindel vollständig abdichtet bzw. von der in die Brennkammer einströmenden Kühlluft trennt.The US-A1-4132066 describes a gas turbine combustor with combustor shingles attached to a support structure. The support structure and the combustion chamber shingle each have a recess into which a toroidal component is inserted, which introduces the cooling air through its annular structure and thereby completely seals the gap between the support structure and the combustion chamber shingle or separates from the cooling air flowing into the combustion chamber.

Die GB-A-2353589 , welche den nächstkommenden Stand der Technik bildet, beschreibt eine Gasturbinenbrennkammer mit Brennkammerschindeln, welche jeweils mit zumindest einem Mischluftloch versehen sind. Dieses ist im Durchmesser kleiner als der zugeordnete Durchmesser eines Mischluftlochs der Tragstruktur. Die Brennkammerschindeln liegen mittels eines breiten Flansches abgedichtet direkt an der Tragstruktur an, so dass die Kühlluft während des Betriebs direkt in die Brennkammer geleitet wird.The GB-A-2353589 , which forms the closest prior art, describes a gas turbine combustor having combustor shingles each provided with at least one mixing air hole. This is smaller in diameter than the associated diameter of a mixed air hole of the support structure. The combustion chamber shingles are sealed by a wide flange directly to the support structure, so that the cooling air is passed during operation directly into the combustion chamber.

Der Erfindung liegt die Aufgabe zu Grunde, eine Gasturbinenbrennkammer mit Brennkammerschindeln der eingangs genannten Art zu schaffen, welche bei einfachem Aufbau, einfacher, kostengünstiger Herstellbarkeit und einfacher Montage eine hohe Lebensdauer aufweist und Überhitzungen der gesamten Konstruktion vermeidet.The invention is based on the object to provide a gas turbine combustor with combustor shingles of the type mentioned, which has a simple design, simple, cost-effective manufacturability and ease of assembly has a long life and avoids overheating of the entire construction.

Erfindungsgemäß wird die Aufgabe durch die Merkmalskombination des Hauptanspruchs gelöst, die Unteransprüche zeigen weitere vorteilhafte Ausgestaltungen der Erfindung.According to the invention the object is achieved by the feature combination of the main claim, the subclaims show further advantageous embodiments of the invention.

Erfindungsgemäß ist vorgesehen, dass der Durchmesser des Mischluftlochs der Tragstruktur deutlich größer ist, als der Durchmesser des Mischluftlochs der Brennkammerschindel.According to the invention it is provided that the diameter of the mixing air hole of the support structure is significantly larger than the diameter of the mixing air hole of the combustion chamber shingle.

Die erfindungsgemäße Ausgestaltung zeichnet sich durch eine Reihe erheblicher Vorteile aus.The embodiment of the invention is characterized by a number of significant advantages.

Durch die erfindungsgemäße Wahl der Durchmesserverhältnisse steht der Schindelrand, von der Außenseite der Tragstruktur aus gesehen, deutlich sichtbar in den freien Durchmesser des Mischluftloches vor. Hierdurch bildet sich ein Staudruck auf dem verdickten Schindelrand. Weiterhin wird der Durchflusskoffizient des Mischluftloches erhöht. Tritt nun im Betrieb ein Spalt zwischen dem Schindelrand und dem der Tragstruktur auf, dann wirkt der oben genannte Staudruck einem Ausströmen von Kühlluft aus dem Schindelinnenraum entgegen. Bei entsprechender Wahl des Durchmessers des Mischluftloches der Tragstruktur ist der Staudruck auf dem Schindelrand gleich dem Druck im Schindelinnenraum. Somit wird ein Ausströmen von Kühlluft aus dem Schindelinnenraum gänzlich verhindert.As a result of the choice of the diameter ratios according to the invention, the shingle edge, seen from the outside of the support structure, is clearly visible in the free diameter of the mixed-air hole. This creates a dynamic pressure on the thickened shingle edge. Furthermore, the flow coefficient becomes of the mixed air hole increased. If, during operation, a gap occurs between the shingle edge and that of the support structure, then the above-mentioned back pressure counteracts an outflow of cooling air from the shingle interior. With appropriate choice of the diameter of the mixing air hole of the support structure of the back pressure on the shingle edge is equal to the pressure in the shingled interior. Thus, a leakage of cooling air from the shingled interior is completely prevented.

Erfindungsgemäß kann bei einer entsprechenden Abstimmung der Durchmesser des Mischluftlochs der Tragstruktur und des Mischluftlochs der Brennkammerschindel erreicht werden, dass durch den starken Staudruck auf dem verdickten Rand der Brennkammerschindel beim Auftreten eines Spalts zwischen der Brennkammerschindel und der Tragstruktur, welcher durch eine Überhitzung der Schindel hervorgerufen wird, zusätzliche Kühlluft aus dem Mischluftloch in den Schindelinnenraum fließt und damit die Kühlung der Brennkammerschindel intensiviert.According to the invention the diameter of the mixing air hole of the support structure and the mixing air hole of the combustion chamber shingle can be achieved by the strong dynamic pressure on the thickened edge of the combustion chamber shingles when a gap between the combustion chamber shingle and the support structure, which is caused by overheating of the shingle , Additional cooling air flows from the mixing air hole in the shingled interior and thus intensifies the cooling of the combustion chamber shingles.

Erfindungsgemäß ist somit eine adaptive Kühlung realisiert, bei welcher die Kühlluftmenge selbsttätig an die Temperaturbelastung der Brennkammerschindel angepasst wird.According to the invention, an adaptive cooling is thus realized, in which the amount of cooling air is automatically adapted to the temperature load of the combustion chamber shingle.

Erfindungsgemäß wird der verdickte Rand der Brennkammerschindel durch ein gesondertes Muster von Effusionslöchern gekühlt. Die Effusionslöcher können dabei auf der Rückseite der Oberfläche der Brennkammerschindel oder im Schindelrand beginnen, wobei sie auf der dem Schindelinnenraum oder der Tragstruktur zugewandten Seite eintreten können. Die Effusionslöcher enden auf der Oberfläche der Brennkammerschindel oder an der Innenseite des Mischluftlochs der Brennkammerschindel. Die Effusionslöcher können ohne oder mit einer Umfangskomponente um die Achse des Mischluftloches zur. Heißgasseite der Brennkammerschindel verlaufen.According to the invention, the thickened edge of the combustion chamber shingle is cooled by a separate pattern of effusion holes. The effusion holes can start on the back of the surface of the combustion chamber shingle or in the shingle edge, where they can enter on the shingle interior or the supporting structure side facing. The effusion holes end on the surface of the combustion chamber shingle or on the inside of the mixing hole of the combustion chamber shingle. The effusion holes may be without or with a peripheral component around the axis of the mixing air hole to. Hot gas side of the combustion chamber shingle run.

Es ergibt sich somit, dass die Kühlluftmenge im Ausgangszustand der Gasturbinenbrennkammer so gewählt werden kann, dass sie für den normalen Betrieb gerade ausreichend ist. Somit steht die maximale Luftmenge für die Schadgasreduzierung zur Verfügung. In Extremsituationen, bei denen die Brennkammerschindel thermisch stärker belastet wird, wird selbsttätig die Kühlung erhöht, sodass ein langanhaltender und sicherer Betrieb möglich ist.It thus follows that the amount of cooling air in the initial state of the gas turbine combustor can be chosen so that it is just sufficient for normal operation. Thus, the maximum amount of air is available for the reduction of harmful gas. In extreme situations, where the combustion chamber shingles are subject to higher thermal loads, the cooling is automatically increased, so that a long-lasting and safe operation is possible.

Im Folgenden wird die Erfindung anhand eines Ausführungsbeispiels in Verbindung mit der Zeichnung beschrieben. Dabei zeigt:

Abb. 1
eine schematische Schnittansicht einer Gasturbinenbrennkammer mit Brennkammerschindeln gemäß dem Stand der Technik,
Abb. 2a
eine Schnittansicht durch eine Brennkammerschindel nach dem Stand der Technik,
Abb. 2b
eine Detailansicht des Details 2b von Abb. 2a,
Abb. 3a
eine Schnittansicht, analog Abb. 2a einer erfindungsgemäßen Ausgestaltung einer Brennkammerschindel,
Abb. 3b
eine Detailansicht des Details 3b von Abb. 3a,
Abb. 4a
eine Detaildarstellung des Brennkammerschindelrandes analog zu der Darstellung der Abb. 3a, und
Abb. 4b
Darstellungen des Randbereichs eines erfindungsgemäßen Mischluftloches in Draufsicht mit unterschiedlicher Anordnung von Effusionslöchern.
In the following the invention will be described by means of an embodiment in conjunction with the drawing. Showing:
Fig. 1
a schematic sectional view of a gas turbine combustor with combustor shingles according to the prior art,
Fig. 2a
a sectional view through a combustion chamber shingle according to the prior art,
Fig. 2b
a detail view of the detail 2b of Fig. 2a .
Fig. 3a
a sectional view, analog Fig. 2a an inventive design of a combustion chamber shingle,
Fig. 3b
a detail view of the detail 3b of Fig. 3a .
Fig. 4a
a detailed representation of the combustion chamber shingle edge analogous to the representation of Fig. 3a , and
Fig. 4b
Representations of the edge region of a mixing air hole according to the invention in plan view with different arrangement of effusion holes.

Die Abb. 1 zeigt eine schematische Seiten-Schnittansicht einer aus dem Stand der Technik bekannten Gasturbinenbrennkammer. Dabei ist eine Abdeckung 1 eines Brennkammerkopfes dargestellt. Das Bezugszeichen 2 bezeichnet eine Grundplatte, Brennkammerschindeln sind mit dem Bezugszeichen 3 bezeichnet. Die Brennkammerschindeln 3 weisen Mischluftlöcher 4 auf und sind an einer Tragstruktur 6 befestigt. Mit dem Bezugszeichen 5 ist ein Hitzeschild mit einem Loch für einen Brenner 8 bezeichnet. Am Auslauf der Brennkammer ist eine Turbinenleitschaufel 9 schematisch dargestellt. Das Bezugszeichen 10 bezeichnet eine Leitschaufel im Verdichterauslass. Ein Brennkammeraußengehäuse 11 und ein Brennkammerinnengehäuse 12 begrenzt die Brennkammer.The Fig. 1 shows a schematic side sectional view of a known from the prior art gas turbine combustor. In this case, a cover 1 of a combustion chamber head is shown. The reference numeral 2 designates a base plate, combustion chamber shingles are designated by the reference numeral 3. The combustion chamber shingles 3 have mixing air holes 4 and are fastened to a support structure 6. The reference numeral 5 denotes a heat shield with a hole for a burner 8. At the outlet of the combustion chamber, a turbine vane 9 is shown schematically. Reference numeral 10 denotes a vane in the compressor outlet. A combustion chamber outer housing 11 and a combustion chamber inner housing 12 delimits the combustion chamber.

Die Abb. 2a und 2b zeigen die Ausgestaltung eines Mischluftlochs 4 der Brennkammerschindel 3 sowie eines entsprechenden Mischluftloches der Tragstruktur 6 gemäß dem Stand der Technik. Dabei ist ersichtlich, dass der Durchmesser 13 des Mischluftlochs der Tragstruktur 6 geringfügig größer ist, als der Durchmesser 14 des Mischluftlochs 4 der Brennkammerschindel 3. Aus Abb. 2b ist ersichtlich, dass die Luftströmung 15 im Mischluftloch 4 zusätzlich Luft aus dem Schindelinnenraum zieht.The Fig. 2a and 2b show the configuration of a mixing air hole 4 of the combustion chamber shingle 3 and a corresponding mixing air hole of the support structure 6 according to the prior art. It can be seen that the diameter 13 of the mixing air hole of the support structure 6 is slightly larger than the diameter 14 of the mixing air hole 4 of the combustion chamber shingle 3. Off Fig. 2b it can be seen that the air flow 15 in the mixing air hole 4 additionally draws air from the shingle interior.

Die Abb. 3a und 3b zeigen die erfindungsgemäße Ausgestaltung in analoger Darstellung zu den Abb. 2a und 2b. Dabei ist ersichtlich, dass der Durchmesser 13 des Mischluftlochs der Tragstruktur 6 deutlicher oder erheblich größer ist, als der Durchmesser 14 des Mischluftlochs 4 der Brennkammerschindel 3. Aus der Abb. 3b ist ersichtlich, dass ein Staudruck der Luftströmung 15 zu einem zusätzlichen Einströmen von Kühlluft in den Schindelinnenraum führt, sobald sich ein Spalt zwischen der Tragstruktur 6 und dem Schindelrand 7 bildet.The Fig. 3a and 3b show the inventive design in an analogous representation to the Fig. 2a and 2b , It can be seen that the diameter 13 of the mixing air hole of the support structure 6 is significantly or significantly greater than the diameter 14 of the mixing air hole 4 of the combustion chamber shingle 3. From the Fig. 3b It can be seen that a back pressure of Air flow 15 leads to an additional inflow of cooling air into the shingled interior, as soon as a gap between the support structure 6 and the shingle edge 7 is formed.

Die Abb. 4a zeigt in vergrößerter Darstellung einen Teilbereich einer erfindungsgemäßen Brennkammerschindel 3. Dabei ist ersichtlich, dass durch den Schindelrand 7 im Bereich des Mischluftlochs 4 zusätzliche Effusionslöcher 16 vorgesehen sind, um Kühlluft aus dem Schindelinnenraum zur Kühlung der Brennkammerschindel 3 zuzuführen. Wie ersichtlich, können die Effusionslöcher 16 in unterschiedlicher Ausrichtung zu der Ebene der Brennkammerschindel 3 angeordnet sein. Das Effusionsloch 16a ist mit einem sehr flachen Winkel angeordnet, während die Effusionslöcher 16b und 16d sich durch den Schindelrand 7 erstrecken und in einem größeren Winkel zur Hauptebene der Brennkammerschindel 3 ausgerichtet sind. Das Effusionsloch 16e erstreckt nahezu senkrecht zur Hauptebene der Brennkammerschindel 3 und durchströmt den Schindelrand 7.The Fig. 4a shows an enlarged view of a portion of a combustion chamber shingle 3. It can be seen that 4 additional effusion holes 16 are provided by the shingle edge 7 in the region of the mixing air hole to supply cooling air from the shingled interior for cooling the combustion chamber shingle 3. As can be seen, the effusion holes 16 may be arranged in a different orientation to the plane of the combustion chamber shingle 3. The effusion hole 16a is arranged at a very shallow angle, while the effusion holes 16b and 16d extend through the shingle edge 7 and are oriented at a greater angle to the main plane of the combustion chamber shingle 3. The effusion hole 16e extends almost perpendicular to the main plane of the combustion chamber shingle 3 and flows through the shingle edge. 7

Die Abb. 4b zeigt zwei unterschiedliche Ausführungsvarianten der Effusionslöcher 16 in der Draufsicht auf das Mischluftloch 4 der Brennkammerschindel 3. In der linken Figur der Abb. 4b sind die Effusionslöcher jeweils radial angeordnet (unabhängig von dem jeweiligen Neigungswinkel gemäß Abb. 4a), während in der rechten Figur der Abb. 4b zusätzlich eine Tangentialkomponenten um die Achse des Mischluftloches oder eine tangentiale Anordnung der Effusionslöcher 16 realisiert ist. Hierdurch kann eine besonders effiziente Kühlung erfolgen.The Fig. 4b shows two different embodiments of the effusion holes 16 in the plan view of the mixing air hole 4 of the combustion chamber shingles 3. In the left figure of Fig. 4b the effusion holes are each arranged radially (regardless of the respective angle of inclination according to FIG Fig. 4a ), while in the right figure the Fig. 4b in addition, a tangential component about the axis of the mixing air hole or a tangential arrangement of the effusion holes 16 is realized. This allows a particularly efficient cooling done.

Die Erfindung ist nicht auf die gezeigten Ausführungsbeispiele beschränkt, vielmehr ergeben sich im Rahmen der Er-findung vielfältige Abwandlungs- und Modifikationsmöglichkeiten.The invention is not limited to the embodiments shown, but rather arise in the context of the invention various modifications and modifications.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Abdeckung des BrennkammerkopfesCover of the combustion chamber head
22
Grundplattebaseplate
33
Brennkammerschindelcombustion chamber tile
44
MischluftlochMixed air hole
55
Hitzeschild (mit Loch für Brenner)Heat shield (with hole for burner)
66
Tragstruktursupporting structure
77
Schindelrandtile rim
88th
Brenner (mit Brennerarm und Drallerzeuger)Burner (with burner arm and swirl generator)
99
Turbinenleitschaufelturbine vane
1010
Leitschaufel im VerdichterauslassGuide vane in the compressor outlet
1111
BrennkammeraußengehäuseCombustion chamber outer housing
1212
BrennkammerinnengehäuseCombustion chamber inner housing
1313
Durchmesser des Mischluftlochs in der Tragstruktur 6Diameter of the mixed air hole in the support structure 6
1414
Durchmesser des Mischluftlochs 4 in der Schindel 3Diameter of the mixing air hole 4 in the shingle 3rd
1515
Luftströmung im Mischluftloch 4Air flow in the mixed air hole 4
1616
Effusionslocheffusion

Claims (7)

  1. Gas turbine combustion chamber with combustion chamber tiles, with the combustion chamber tiles (3) being attached to a supporting structure (6) of the gas turbine combustion chamber, and each tile possessing at least one dilution air hole (4) which is flush with a dilution air hole of the supporting structure (6), with the diameter of the dilution air hole of the supporting structure (6) being 15 percent to 25 percent larger than the diameter (14) of the dilution air hole (4) of the combustion chamber tile (3), characterized in that the combustion chamber tile (3) is not sealed at the location of its tile rim (7) on the supporting structure (6) and a gap can form between the supporting structure (6) and the tile rim (7), with, for the formation of a dynamic pressure on a tile rim (7), the tile rim (7) protruding into the free diameter of the dilution air hole (4), as seen from the outside of the supporting structure (6).
  2. Gas turbine combustion chamber in accordance with Claim 1, characterized in that effusion holes (16) are provided on the tile rim (7) which connect to the tile interior.
  3. Gas turbine combustion chamber in accordance with Claim 2, characterized in that the effusion holes (16) are provided in the tile rim (7).
  4. Gas turbine combustion chamber in accordance with Claim 2 or 3, characterized in that the effusion holes (16) are provided in the combustion chamber tile (3).
  5. Gas turbine combustion chamber in accordance with one of the Claims 2 to 4, characterized in that the effusion holes (16) are arranged radially to the dilution air hole (4).
  6. Gas turbine combustion chamber in accordance with one of the Claims 2 to 4, characterized in that the effusion holes (16) are arranged tangentially to the dilution air hole (4).
  7. Gas turbine combustion chamber in accordance with one of the Claims 2 to 4, characterized in that the effusion holes (16) have both a radial and a tangential component relative to the axis of the dilution air hole (4).
EP03001782A 2002-04-02 2003-01-28 Air passage for turbine combustor with shingles Expired - Fee Related EP1351022B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10214570A DE10214570A1 (en) 2002-04-02 2002-04-02 Mixed air hole in gas turbine combustion chamber with combustion chamber shingles
DE10214570 2002-04-02

Publications (3)

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EP1351022A2 EP1351022A2 (en) 2003-10-08
EP1351022A3 EP1351022A3 (en) 2005-01-26
EP1351022B1 true EP1351022B1 (en) 2010-08-04

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US (1) US7059133B2 (en)
EP (1) EP1351022B1 (en)
DE (2) DE10214570A1 (en)

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Also Published As

Publication number Publication date
DE10214570A1 (en) 2004-01-15
US20030182942A1 (en) 2003-10-02
EP1351022A3 (en) 2005-01-26
DE50312938D1 (en) 2010-09-16
US7059133B2 (en) 2006-06-13
EP1351022A2 (en) 2003-10-08

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