EP2809994B1 - Heat-shield element for a compressor-air bypass around the combustion chamber - Google Patents

Heat-shield element for a compressor-air bypass around the combustion chamber Download PDF

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Publication number
EP2809994B1
EP2809994B1 EP13712711.4A EP13712711A EP2809994B1 EP 2809994 B1 EP2809994 B1 EP 2809994B1 EP 13712711 A EP13712711 A EP 13712711A EP 2809994 B1 EP2809994 B1 EP 2809994B1
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EP
European Patent Office
Prior art keywords
combustion chamber
wall
heat
shield element
height
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.)
Not-in-force
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EP13712711.4A
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German (de)
French (fr)
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EP2809994A2 (en
Inventor
Francois Benkler
Thomas Brandenburg
Olga Deiss
Thomas Grieb
Marco Link
Nicolas Savilius
Daniel Vogtmann
Jan Wilkes
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Siemens AG
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Siemens AG
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Publication of EP2809994A2 publication Critical patent/EP2809994A2/en
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Publication of EP2809994B1 publication Critical patent/EP2809994B1/en
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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
    • F23R3/005—Combined with pressure or heat exchangers
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • 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
    • F23R3/02—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
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections

Definitions

  • the invention relates to a heat shield element of a combustion chamber, in particular an annular combustion chamber of a gas turbine plant, and refers to the bypass of compressor air around the combustion chamber at partial load.
  • the invention further relates to a combustion chamber and a corresponding gas turbine plant.
  • the increased temperature in the combustion chamber leads to the demand for better cooling of the heat shield elements facing the combustion chamber.
  • the EP 1 486 7630 A1 proposes for this purpose to provide the outwardly facing cold side of the heat shield elements with turbulators to improve the cooling by the cooling air.
  • the object of the present invention is to expand by specifying a bypass the carbon monoxide compliant driving range of the gas turbine as far as possible in the direction of low power.
  • Another object of the present invention is to provide an improved combustor. Finally, it is an object of the present invention to provide an improved gas turbine.
  • the first object is achieved by a heat shield element according to claim 1, the second object by a combustion chamber according to claim 6 and the third object by a gas turbine according to claim 10.
  • a heat shield element in particular for lining a combustion chamber wall, comprising a first wall with a hot side to be acted upon by a hot medium, a cold side facing the hot side and a peripheral edge located at a first, extending a second and a third narrow side of the first wall beyond the cold side substantially to a first height, the peripheral edge extends on a fourth narrow side to a second height which is smaller than the first height, and that substantially the second height is opposite to a second wall of the cold side and extends across the width of the fourth narrow side from the fourth narrow side over a portion of the length of the narrow side adjacent the fourth narrow side, wherein the second wall has an edge at its end facing away from the fourth narrow side, which he himself up to the first height treckt.
  • the invention is based on the idea that in an annular combustion chamber, which is largely lined with ceramic heat shield elements and only the inlet into the turbine is lined with metallic heat shield elements, the supply of the bypass air in the metallic heat shield elements of the combustion chamber wall should be done because the supply as possible far behind the combustion to prevent the flame from cooling but before the turbine to maximize gas turbine efficiency should.
  • a new design of the metallic heat shield elements is needed. This design is the subject of this invention.
  • the heat shield element is subdivided into two superimposed areas, which are sealed against each other and which in the installed state, i. with the combustion chamber wall, forming chambers.
  • a first chamber extends over the entire surface of the heat shield element and is used for normal cooling of the metallic heat shield.
  • a second chamber is located in the turbine facing portion of the heat shield element above the first chamber.
  • the heat shield element consists of a high-temperature-resistant metal or a high-temperature-resistant metal alloy, since these materials have a lower brittleness than, for example, ceramics and a comparatively good thermal and thermal conductivity behavior.
  • a plurality of cooling air openings arranged in the peripheral edge are provided, from which the compressor end air provided for cooling the heat shield element can escape into the combustion chamber.
  • cooling air openings are arranged at least in the region of the second wall between the first and the second wall.
  • the cooling holes are in the region of the first chamber for the cooling of the heat shield element.
  • the heat shield element further comprises a mounting opening, the enclosure of which extends from the first wall to the first height.
  • the heat shield element is used for protection against overheating of a component carrying hot gas, in particular a combustion chamber, preferably an annular combustion chamber of a gas turbine having a combustion chamber wall, with a burner side and a turbine side end, wherein the combustion chamber wall has a circumferential direction.
  • a number of heat shield elements is preferably arranged at the turbine-side end of the combustion chamber wall with the formation of two chambers in the circumferential direction, wherein the fourth narrow side is aligned towards the turbine end.
  • the heat shield elements are preferably fastened with fastening bolts on the combustion chamber wall.
  • bores are introduced in the combustion chamber wall so that coolant can be supplied to the heat shield elements.
  • At least one supply channel per heat shield element is arranged in the region of the respective second wall in the combustion chamber wall, which opens into a plenum which at least partially surrounds the combustion chamber.
  • the combustion chamber to which heat shield elements are attached is preferably part of a gas turbine.
  • This gas turbine comprises at least one discharge for compressor air, which opens via at least one line with a valve in the plenum.
  • the invention enables the supply of bypass air in the hot gas path without far-reaching modifications to hot gas components.
  • the implementation will therefore probably be relatively inexpensive. It ensures that no hot gas is drawn in even when the bypass is switched off, since the second chamber is constantly purged and its outlet streamlined between heat shield element and turbine vane 1 is located.
  • FIG. 1 shows schematically and by way of example the combustion system of an annular combustion chamber 1 according to the prior art in a housing 2.
  • the annular combustion chamber 1 consists of a closed ring which is arranged around a rotor axis 3. Burner 4 are arranged in the upper region of the combustion chamber 1 in inlet openings 5. There, the mixing of the fuel 6 with the compressor air 7 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet at the turbine end 8 of the annular combustion chamber 1, the hot combustion gases enter the turbine 9, where they meet the first stationary vane 10.
  • the annular combustion chamber 1 is lined with ceramic heat shield elements 11 and metallic heat shield elements 12, which are fastened to the combustion chamber wall 13.
  • the supply of the bypass air in the area of the metallic heat shield elements 12 should take place, since the supply should be as far as possible behind the combustion and thus a cooling of the flame is avoided, but even before the turbine 9 in order to achieve the highest possible gas turbine efficiency.
  • FIG. 2 shows a metallic heat shield element 14 according to the invention, which is to be fastened to the combustion chamber wall 13 and forms with this a first 15 and a turbine open to the second chamber 16 which are sealed against each other.
  • the metallic heat shield element 14 itself comprises a first wall 17 with a hot side 18 which can be acted upon by a hot medium, a cold side 19 opposite the hot side 18 and four narrow sides 20, 21, 22, 23 located between them.
  • a peripheral edge 24 extends from each narrow side 20, 21, 22, 23 beyond the cold side 19 addition.
  • the edge 24 extends substantially up to a first height 25 relative to the cold side 19 of the first wall 17 and on the fourth narrow side 23 only to a smaller second height 26th
  • the installed metallic heat shield element 14 rests on the edges of three narrow sides 20, 21, 22 on the combustion chamber wall 13.
  • a second wall 27 is located substantially opposite to the second height 26 of the cold side 19. It extends over the width of the fourth narrow side 23 and from the fourth narrow side 23 over part of the length of the fourth narrow side 23 adjacent narrow sides 20, 22. Furthermore, the second wall 27 at its fourth narrow side 23 facing away from the end 28 has an edge 29, which extends from the second height 26 to the first height 25.
  • a plurality of cooling air openings 30 are provided in the peripheral edge 24 in the region of the first chamber 15.
  • the first chamber 15 is supplied, as in prior art heat shield elements 12, through holes through the combustor wall 13 with compressor discharge air for cooling, which escapes from the metallic heat shield element 14 via these cooling air openings 30.
  • the metallic heat shield element 14 has a mounting aperture 31, the skirt 32 of which extends from the first wall 17 to the first height 25. Through this attachment opening 31, the heat shield element 14 is fastened to the combustion chamber wall 13 by means of fastening bolts.
  • the supply of open in the direction of the turbine 9 second chamber 16 with compressor air consists of two components.
  • the second chamber 16 is permanently supplied with some compressor air for flushing via a few holes through the combustion chamber wall 13, so that no hot gas can penetrate into the second chamber 16 when the bypass is off.
  • the second chamber 16 can be engaged in a switchable manner with a bypass mass flow. This is done over comparatively large holes, i. compared to the holes for the flushing, fed in the combustion chamber wall 13.
  • the bypass mass flow then escapes via the opening at the trailing edge, i. the combustion chamber facing side of the heat shield element 14, on which the peripheral edge 24 extends only to the second height 26, in the gap between the metallic heat shield element 14 and the first stationary vane 10th
  • FIG. 3 shows how compressor air is initially led out of the gas turbine via a removal 33 for the bypass. Outside the gas turbine, the circuit via a valve 34. Thereafter, the air is returned via a line 35 into the gas turbine and entered into a circulating around the annular combustion chamber 1 plenum 36. From there, stub lines 37 or tap holes lead to the respective second chamber 16 of the respective metallic heat shield element 14.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Supercharger (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft ein Hitzeschildelement einer Brennkammer, insbesondere einer Ringbrennkammer einer Gasturbinenanlage, und bezieht sich auf den Bypass von Verdichterluft um die Brennkammer bei Teillast. Die Erfindung betrifft ferner eine Brennkammer und eine entsprechende Gasturbinenanlage.The invention relates to a heat shield element of a combustion chamber, in particular an annular combustion chamber of a gas turbine plant, and refers to the bypass of compressor air around the combustion chamber at partial load. The invention further relates to a combustion chamber and a corresponding gas turbine plant.

Durch das Absinken der zentralen Flammtemperatur beim Absenken der Leistung der Gasturbine erhöhen sich die Kohlenmonoxidemissionen sukzessive, bis sie ab einer gewissen Teillast die gesetzliche Emissionsgrenze überschreiten. Dadurch ergibt sich eine zulässige Mindestleistung. Es kann jedoch wichtig sein, die Maschine bei sehr tiefer Leistung bereit zu halten.By lowering the central flame temperature while lowering the power of the gas turbine, the carbon monoxide emissions increase successively until they exceed the statutory emission limit from a certain partial load. This results in a permissible minimum power. However, it can be important to keep the machine ready at very low power.

Aus dem Stand der Technik sind verschiedene Ansätze bekannt, den Wirkungsgrad durch eine Steigerung der Verbrennungstemperatur anzuheben bekannt. Hierzu offenbaren die EP 1 482 246 A1 sowie die US 2012/0036858 A1 Gasturbinen, bei denen die Brennkammerwand zweischalig ausgeführt ist, wobei Kühlluft zwischen den beiden Schalen entgegen der Strömungsrichtung in der Brennkammer zum Brenner geführt wird.Various approaches are known from the prior art to increase the efficiency by increasing the combustion temperature known. This is revealed by the EP 1 482 246 A1 as well as the US 2012/0036858 A1 Gas turbines in which the combustion chamber wall is designed clamshell, wherein cooling air is passed between the two shells against the flow direction in the combustion chamber to the burner.

Die gesteigerte Temperatur in der Brennkammer führt zur Forderung einer besseren Kühlung der zur Brennkammer weisenden Hitzeschildelemente. Die EP 1 486 7630 A1 schlägt hierzu vor, die nach außen weisende Kaltseite der Hitzeschildelemente mit Turbolatoren zur Verbesserung der Kühlung durch die Kühlluft zu versehen.The increased temperature in the combustion chamber leads to the demand for better cooling of the heat shield elements facing the combustion chamber. The EP 1 486 7630 A1 proposes for this purpose to provide the outwardly facing cold side of the heat shield elements with turbulators to improve the cooling by the cooling air.

Eine Möglichkeit die Flammtemperatur zu erhöhen und damit die Kohlenmonoxidemissionen zu verringern besteht darin, einen Teil der Verdichterendluft um die Verbrennung herumzuführen und vor dem Turbineneintritt dem Heißgaspfad wieder zuzuführen. Rechnungen haben gezeigt, dass diese Methode bei der Ringbrennkammer erfolgversprechend ist. Schwierig ist hierbei, dass der Bypass nur in den relevanten Leistungsbereichen aktiv sein soll, da sonst unnötig die Leistung der Gasturbine beeinflusst wird. Er muss also schaltbar sein, wobei auch bei abgeschaltetem Bypass kein Heißgas in diesen eindringen darf.One way to increase the flame temperature and thus reduce carbon monoxide emissions is to pass some of the final compressor air around the combustion and to supply the hot gas path again before the turbine entry. Calculations have shown that this method is promising in the annular combustion chamber. It is difficult here that the bypass should only be active in the relevant power ranges, since otherwise the performance of the gas turbine is unnecessarily affected. It must therefore be switchable, with no hot gas may penetrate even when the bypass is switched off.

Gegenüber dem beschriebenen Stand der Technik besteht die Aufgabe der vorliegenden Erfindung darin, durch Angabe eines Bypasses den kohlenmonoxidkonformen Fahrbereich der Gasturbine so weit wie möglich in Richtung geringer Leistung zu erweitern.Compared to the described prior art, the object of the present invention is to expand by specifying a bypass the carbon monoxide compliant driving range of the gas turbine as far as possible in the direction of low power.

Eine weitere Aufgabe der vorliegenden Erfindung besteht darin, eine verbesserte Brennkammer zur Verfügung zu stellen. Schließlich ist es eine Aufgabe der vorliegenden Erfindung, eine verbesserte Gasturbine zur Verfügung zu stellen.Another object of the present invention is to provide an improved combustor. Finally, it is an object of the present invention to provide an improved gas turbine.

Die erste Aufgabe wird durch ein Hitzeschildelement nach Anspruch 1, die zweite Aufgabe durch eine Brennkammer nach Anspruch 6 und die dritte Aufgabe durch eine Gasturbine nach Anspruch 10 gelöst.The first object is achieved by a heat shield element according to claim 1, the second object by a combustion chamber according to claim 6 and the third object by a gas turbine according to claim 10.

Die abhängigen Ansprüche enthalten vorteilhafte Ausgestaltungen der Erfindung.The dependent claims contain advantageous embodiments of the invention.

Die Erfindung löst diese Aufgaben, indem sie vorsieht, dass bei einem Hitzeschildelement, insbesondere zur Auskleidung einer Brennkammerwand, umfassend eine erste Wand mit einer mit einem heißen Medium beaufschlagbaren Heißseite, einer der Heißseite gegenüberliegende Kaltseite und einem umlaufenden Rand, der sich an einer ersten, einer zweiten und einer dritten Schmalseite der ersten Wand über die Kaltseite hinaus im wesentlichen bis zu einer ersten Höhe erstreckt, sich der umlaufende Rand an einer vierten Schmalseite bis zu einer zweiten Höhe erstreckt, die kleiner als die erste Höhe ist, und dass im wesentlichen auf der zweiten Höhe eine zweite Wand der Kaltseite gegenüberliegt und sich über die Breite der vierten Schmalseite von der vierten Schmalseite ab über einen Teil der Länge der der vierten Schmalseite benachbarten Schmalseiten erstreckt, wobei die zweite Wand an ihrem der vierten Schmalseite abgewandten Ende einen Rand aufweist, der sich bis zur ersten Höhe erstreckt.The invention achieves these objects by providing that in a heat shield element, in particular for lining a combustion chamber wall, comprising a first wall with a hot side to be acted upon by a hot medium, a cold side facing the hot side and a peripheral edge located at a first, extending a second and a third narrow side of the first wall beyond the cold side substantially to a first height, the peripheral edge extends on a fourth narrow side to a second height which is smaller than the first height, and that substantially the second height is opposite to a second wall of the cold side and extends across the width of the fourth narrow side from the fourth narrow side over a portion of the length of the narrow side adjacent the fourth narrow side, wherein the second wall has an edge at its end facing away from the fourth narrow side, which he himself up to the first height treckt.

Die Erfindung beruht auf dem Gedanken, dass bei einer Ringbrennkammer, die größtenteils mit keramischen Hitzeschildelementen ausgekleidet ist und nur der Einlauf in die Turbine mit metallischen Hitzeschildelementen ausgekleidet ist, die Zuführung der Bypassluft im Bereich der metallischen Hitzeschildelemente der Brennkammerwand geschehen soll, da die Zuführung möglichst weit hinter der Verbrennung, um eine Kühlung der Flamme zu verhindern, aber vor der Turbine, um einen möglichst hohen Gasturbinenwirkungsgrad zu erreichen, erfolgen soll. Dazu wird ein neues Design der metallischen Hitzeschildelemente benötigt. Dieses Design ist Gegenstand dieser Erfindungsmeldung.The invention is based on the idea that in an annular combustion chamber, which is largely lined with ceramic heat shield elements and only the inlet into the turbine is lined with metallic heat shield elements, the supply of the bypass air in the metallic heat shield elements of the combustion chamber wall should be done because the supply as possible far behind the combustion to prevent the flame from cooling but before the turbine to maximize gas turbine efficiency should. For this purpose, a new design of the metallic heat shield elements is needed. This design is the subject of this invention.

Das Hitzeschildelement wird in zwei übereinander liegende Bereiche unterteilt, die gegeneinander dicht sind und die im eingebauten Zustand, d.h. mit der Brennkammerwand, Kammern bilden. Eine erste Kammer erstreckt sich über die komplette Fläche des Hitzeschildelements und wird zur normalen Kühlung des metallischen Hitzeschildes genutzt.The heat shield element is subdivided into two superimposed areas, which are sealed against each other and which in the installed state, i. with the combustion chamber wall, forming chambers. A first chamber extends over the entire surface of the heat shield element and is used for normal cooling of the metallic heat shield.

Eine zweite Kammer befindet sich im der Turbine zugewandten Teil des Hitzeschildelements über der ersten Kammer.A second chamber is located in the turbine facing portion of the heat shield element above the first chamber.

Vorteilhafter Weise besteht das Hitzeschildelement aus einem hochtemperaturbeständigen Metall oder einer hochtemperaturbeständigen Metalllegierung, da diese Materialien eine geringere Sprödigkeit als beispielsweise Keramik und ein vergleichsweise gutes Wärme- und Temperaturleitverhalten aufweisen.Advantageously, the heat shield element consists of a high-temperature-resistant metal or a high-temperature-resistant metal alloy, since these materials have a lower brittleness than, for example, ceramics and a comparatively good thermal and thermal conductivity behavior.

In einer vorteilhaften Ausführungsform ist eine Mehrzahl von im umlaufenden Rand angeordneten Kühlluftöffnungen vorgesehen, aus denen die zur Kühlung des Hitzeschildelements vorgesehene Verdichterendluft in die Brennkammer entweichen kann.In an advantageous embodiment, a plurality of cooling air openings arranged in the peripheral edge are provided, from which the compressor end air provided for cooling the heat shield element can escape into the combustion chamber.

Dabei ist es zweckmäßig, wenn die Kühlluftöffnungen zumindest im Bereich der zweiten Wand zwischen der ersten und der zweiten Wand angeordnet sind. Somit befinden sich die Kühlöffnungen im Bereich der ersten Kammer für die Kühlung des Hitzeschildelements.It is expedient if the cooling air openings are arranged at least in the region of the second wall between the first and the second wall. Thus, the cooling holes are in the region of the first chamber for the cooling of the heat shield element.

Vorteilhafter Weise umfasst das Hitzeschildelement weiterhin eine Befestigungsöffnung, deren Einfassung sich von der ersten Wand bis zur ersten Höhe erstreckt. Somit ist sichergestellt, dass die beiden Kammern gegeneinander dicht sind und keine Luft durch für die zur Befestigung des Hitzeschildelements benötigte Öffnung von der einen Kammer in die andere Kammer strömen kann.Advantageously, the heat shield element further comprises a mounting opening, the enclosure of which extends from the first wall to the first height. Thus, it is ensured that the two chambers are sealed against each other and no air can flow through from the one chamber into the other chamber for the required for attachment of the heat shield element opening.

Das Hitzeschildelement wird zum Schutz vor Überhitzungen einer heißgasführenden Komponente benutzt, insbesondere einer Brennkammer, vorzugsweise einer ringförmigen Brennkammer einer Gasturbine, die eine Brennkammerwand aufweist, mit einem brennerseitigen und einem turbinenseitigen Ende, wobei die Brennkammerwand eine Umfangsrichtung aufweist. Eine Anzahl von Hitzeschildelementen ist dabei vorzugsweise am turbinenseitigen Ende der Brennkammerwand unter Bildung von je zwei Kammern in Umfangsrichtung angeordnet, wobei die vierte Schmalseite zum turbinenseitigen Ende hin ausgerichtet ist.The heat shield element is used for protection against overheating of a component carrying hot gas, in particular a combustion chamber, preferably an annular combustion chamber of a gas turbine having a combustion chamber wall, with a burner side and a turbine side end, wherein the combustion chamber wall has a circumferential direction. A number of heat shield elements is preferably arranged at the turbine-side end of the combustion chamber wall with the formation of two chambers in the circumferential direction, wherein the fourth narrow side is aligned towards the turbine end.

Die Hitzeschildelemente sind dabei bevorzugt mit Befestigungsbolzen an der Brennkammerwand befestigt.The heat shield elements are preferably fastened with fastening bolts on the combustion chamber wall.

Bevorzugtermaßen sind in der Brennkammerwand Bohrungen eingebracht, so dass Kühlmittel den Hitzeschildelementen zuführbar ist.Preferably, bores are introduced in the combustion chamber wall so that coolant can be supplied to the heat shield elements.

In einer bevorzugten Ausgestaltung der Brennkammer ist in der Brennkammerwand mindestens ein Zufuhrkanal je Hitzeschildelement im Bereich der jeweils zweiten Wand angeordnet, der in ein zumindest teilweise um die Brennkammer umlaufendes Plenum einmündet.In a preferred embodiment of the combustion chamber, at least one supply channel per heat shield element is arranged in the region of the respective second wall in the combustion chamber wall, which opens into a plenum which at least partially surrounds the combustion chamber.

Die Brennkammer, an der Hitzeschildelemente angebracht sind, ist bevorzugtermaßen Teil einer Gasturbine. Diese Gasturbine umfasst mindestens eine Entnahme für Verdichterluft, die über mindestens eine Leitung mit einem Ventil in das Plenum mündet.The combustion chamber to which heat shield elements are attached is preferably part of a gas turbine. This gas turbine comprises at least one discharge for compressor air, which opens via at least one line with a valve in the plenum.

Die Erfindung ermöglicht die Zufuhr von Bypassluft in den Heißgaspfad ohne weitreichende Modifikationen an heißgasführenden Bauteilen. Die Umsetzung wird daher vermutlich vergleichsweise kostengünstig sein. Es wird gewährleistet, dass auch bei abgeschaltetem Bypass kein Heißgas eingezogen wird, da die zweite Kammer ständig gespült wird und ihr Austritt strömungsgünstig zwischen Hitzeschildelement und Turbinenleitschaufel 1 liegt.The invention enables the supply of bypass air in the hot gas path without far-reaching modifications to hot gas components. The implementation will therefore probably be relatively inexpensive. It ensures that no hot gas is drawn in even when the bypass is switched off, since the second chamber is constantly purged and its outlet streamlined between heat shield element and turbine vane 1 is located.

Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen schematisch und nicht maßstäblich:

Figur 1
einen Schnitt durch eine Ringbrennkammer nach dem Stand der Technik,
Figur 2
ein erfindungsgemäßes metallisches Hitzeschildelement und
Figur 3
einen Schnitt durch eine Ringbrennkammer nach der Erfindung mit Entnahmesystem für den Verdichterluftbypass.
The invention will be explained in more detail by way of example with reference to the drawings. Shown schematically and not to scale:
FIG. 1
a section through an annular combustion chamber according to the prior art,
FIG. 2
a metallic heat shield element according to the invention and
FIG. 3
a section through an annular combustion chamber according to the invention with removal system for the compressor air bypass.

Die Figur 1 zeigt schematisch und beispielhaft das Verbrennungssystem einer Ringbrennkammer 1 nach dem Stand der Technik in einem Gehäuse 2. Die Ringbrennkammer 1 besteht aus einem geschlossenen Ring der um eine Rotorachse 3 angeordnet ist. Brenner 4 sind im oberen Bereich der Brennkammer 1 in Einlassöffnungen 5 angeordnet. Dort findet die Vermischung des Brennstoffs 6 mit der Verdichterluft 7 statt. In der Brennkammer 1 erfolgt die eigentliche Verbrennung. Durch den Auslass am turbinenseitigen Ende 8 der Ringbrennkammer 1 gelangen die heißen Verbrennungsgase in die Turbine 9, wo sie auf die erste stehende Leitschaufel 10 treffen. Zum Schutz vor Verzunderungen ist die Ringbrennkammer 1 mit keramischen Hitzeschildelementen 11 und metallischen Hitzeschildelementen 12 ausgekleidet, die an der Brennkammerwand 13 befestigt sind.The FIG. 1 shows schematically and by way of example the combustion system of an annular combustion chamber 1 according to the prior art in a housing 2. The annular combustion chamber 1 consists of a closed ring which is arranged around a rotor axis 3. Burner 4 are arranged in the upper region of the combustion chamber 1 in inlet openings 5. There, the mixing of the fuel 6 with the compressor air 7 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet at the turbine end 8 of the annular combustion chamber 1, the hot combustion gases enter the turbine 9, where they meet the first stationary vane 10. For protection against scaling, the annular combustion chamber 1 is lined with ceramic heat shield elements 11 and metallic heat shield elements 12, which are fastened to the combustion chamber wall 13.

Gemäß der Erfindung soll die Zuführung der Bypassluft im Bereich der metallischen Hitzeschildelemente 12 erfolgen, da die Zuführung möglichst weit hinter der Verbrennung geschehen soll und somit eine Kühlung der Flamme vermieden wird, aber noch vor der Turbine 9, um einen möglichst hohen Gasturbinenwirkungsgrad zu erreichen.According to the invention, the supply of the bypass air in the area of the metallic heat shield elements 12 should take place, since the supply should be as far as possible behind the combustion and thus a cooling of the flame is avoided, but even before the turbine 9 in order to achieve the highest possible gas turbine efficiency.

Figur 2 zeigt ein metallisches Hitzeschildelement 14 nach der Erfindung, welches an der Brennkammerwand 13 zu befestigen ist und mit dieser eine erste 15 und eine in Richtung der Turbine offene zweite Kammer 16 bildet, die gegeneinander dicht sind. FIG. 2 shows a metallic heat shield element 14 according to the invention, which is to be fastened to the combustion chamber wall 13 and forms with this a first 15 and a turbine open to the second chamber 16 which are sealed against each other.

Das metallische Hitzeschildelement 14 selbst umfasst eine erste Wand 17 mit einer mit einem heißen Medium beaufschlagbaren Heißseite 18, einer der Heißseite 18 gegenüberliegende Kaltseite 19 und vier dazwischenliegenden Schmalseiten 20, 21, 22, 23. Ein umlaufender Rand 24 erstreckt sich von jeder Schmalseite 20, 21, 22, 23 über die Kaltseite 19 hinaus. An der ersten 20, der zweiten 21 und der dritten 22 Schmalseite erstreckt sich der Rand 24 im wesentlichen bis zu einer ersten Höhe 25 bezogen auf die Kaltseite 19 der ersten Wand 17 und an der vierten Schmalseite 23 lediglich bis zu einer kleineren zweiten Höhe 26. Dadurch liegt das eingebaute metallische Hitzeschildelement 14 an den Rändern dreier Schmalseiten 20, 21, 22 an der Brennkammerwand 13 an.The metallic heat shield element 14 itself comprises a first wall 17 with a hot side 18 which can be acted upon by a hot medium, a cold side 19 opposite the hot side 18 and four narrow sides 20, 21, 22, 23 located between them. A peripheral edge 24 extends from each narrow side 20, 21, 22, 23 beyond the cold side 19 addition. At the first 20, the second 21 and the third narrow side 22, the edge 24 extends substantially up to a first height 25 relative to the cold side 19 of the first wall 17 and on the fourth narrow side 23 only to a smaller second height 26th As a result, the installed metallic heat shield element 14 rests on the edges of three narrow sides 20, 21, 22 on the combustion chamber wall 13.

Eine zweite Wand 27 liegt im Wesentlichen auf der zweiten Höhe 26 der Kaltseite 19 gegenüber. Sie erstreckt sich über die Breite der vierten Schmalseite 23 und von der vierten Schmalseite 23 ab über einen Teil der Länge der der vierten Schmalseite 23 benachbarten Schmalseiten 20, 22. Weiterhin weist die zweite Wand 27 an ihrem der vierten Schmalseite 23 abgewandten Ende 28 einen Rand 29 auf, der sich von der zweiten Höhe 26 bis zur ersten Höhe 25 erstreckt.A second wall 27 is located substantially opposite to the second height 26 of the cold side 19. It extends over the width of the fourth narrow side 23 and from the fourth narrow side 23 over part of the length of the fourth narrow side 23 adjacent narrow sides 20, 22. Furthermore, the second wall 27 at its fourth narrow side 23 facing away from the end 28 has an edge 29, which extends from the second height 26 to the first height 25.

Zur Kühlung des metallischen Hitzeschildelements 14 ist im umlaufenden Rand 24 im Bereich der ersten Kammer 15 eine Mehrzahl von Kühlluftöffnungen 30 vorgesehen.For cooling the metallic heat shield element 14, a plurality of cooling air openings 30 are provided in the peripheral edge 24 in the region of the first chamber 15.

Die erste Kammer 15 wird wie bei Hitzeschildelementen 12 aus dem Stand der Technik über Bohrungen durch die Brennkammerwand 13 mit Verdichterendluft zur Kühlung versorgt, die aus dem metallischen Hitzeschildelement 14 über diese Kühlluftöffnungen 30 entweicht.The first chamber 15 is supplied, as in prior art heat shield elements 12, through holes through the combustor wall 13 with compressor discharge air for cooling, which escapes from the metallic heat shield element 14 via these cooling air openings 30.

Das metallische Hitzeschildelement 14 weist eine Befestigungsöffnung 31 auf, deren Einfassung 32 sich von der ersten Wand 17 bis zur ersten Höhe 25 erstreckt. Durch diese Befestigungsöffnung 31 wird das Hitzeschildelement 14 mittels Befestigungsbolzen an der Brennkammerwand 13 befestigt.The metallic heat shield element 14 has a mounting aperture 31, the skirt 32 of which extends from the first wall 17 to the first height 25. Through this attachment opening 31, the heat shield element 14 is fastened to the combustion chamber wall 13 by means of fastening bolts.

Die Versorgung der in Richtung der Turbine 9 offenen zweiten Kammer 16 mit Verdichterluft besteht aus zwei Komponenten. Zum Einen wird die zweite Kammer 16 permanent über einige Bohrungen durch die Brennkammerwand 13 mit etwas Verdichterluft zum Spülen versorgt, damit kein Heißgas in die zweite Kammer 16 eindringen kann, wenn der Bypass aus ist.The supply of open in the direction of the turbine 9 second chamber 16 with compressor air consists of two components. On the one hand, the second chamber 16 is permanently supplied with some compressor air for flushing via a few holes through the combustion chamber wall 13, so that no hot gas can penetrate into the second chamber 16 when the bypass is off.

Zum Anderen kann die zweite Kammer 16 schaltbar mit einem Bypassmassenstrom beaufschlagt werden. Dieser wird über vergleichsweise große Bohrungen, d.h. im Vergleich zu den Bohrungen für das Spülen, in der Brennkammerwand 13 zugeführt. Der Bypassmassenstrom entweicht dann über die Öffnung an der Hinterkante, d.h. der brennkammerzugewandten Seite des Hitzeschildelements 14, an der der umlaufende Rand 24 nur bis zur zweiten Höhe 26 reicht, in den Spalt zwischen metallischem Hitzeschildelement 14 und der ersten stehenden Leitschaufel 10.On the other hand, the second chamber 16 can be engaged in a switchable manner with a bypass mass flow. This is done over comparatively large holes, i. compared to the holes for the flushing, fed in the combustion chamber wall 13. The bypass mass flow then escapes via the opening at the trailing edge, i. the combustion chamber facing side of the heat shield element 14, on which the peripheral edge 24 extends only to the second height 26, in the gap between the metallic heat shield element 14 and the first stationary vane 10th

Figur 3 zeigt, wie für den Bypass zunächst Verdichterluft über eine Entnahme 33 aus der Gasturbine hinausgeführt wird. Außerhalb der Gasturbine erfolgt die Schaltung über ein Ventil 34. Danach wird die Luft über eine Leitung 35 in die Gasturbine zurückgeführt und in ein um die Ringbrennkammer 1 umlaufendes Plenum 36 eingegeben. Von dort führen Stichleitungen 37 oder Stichbohrungen zur jeweiligen zweiten Kammer 16 des jeweiligen metallischen Hitzeschildelements 14. FIG. 3 shows how compressor air is initially led out of the gas turbine via a removal 33 for the bypass. Outside the gas turbine, the circuit via a valve 34. Thereafter, the air is returned via a line 35 into the gas turbine and entered into a circulating around the annular combustion chamber 1 plenum 36. From there, stub lines 37 or tap holes lead to the respective second chamber 16 of the respective metallic heat shield element 14.

Im Ausführungsbeispiel der Figur 3 sind jeweils nur eine Entnahme 33, ein Ventil 34, eine Leitung 35 und ein Plenum 36 gezeigt. Möglich sind aber auch Lösungen mit mehr Entnahmen, Ventilen, Leitungen und Plenen.In the embodiment of FIG. 3 In each case, only one withdrawal 33, a valve 34, a conduit 35 and a plenum 36 are shown. However, solutions with more withdrawals, valves, pipes and plenums are also possible.

Claims (10)

  1. Heat-shield element (14), in particular for cladding a combustion chamber wall (13), comprising a first wall (17) having a hot side (18) which can be exposed to a hot medium, a cold side (19) opposite the hot side (18) and a circumferential edge (24) which extends on a first (20), a second (21) and a third narrow side (22) substantially up to a first height (25) around the cold side (19) of the first wall (17), characterized in that the circumferential edge (24) extends up to a second height (26), smaller than the first height (25), on a fourth narrow side (23), and in that substantially at the second height (26) a second wall (27) lies opposite the cold side (19) and extends over the breadth of the fourth narrow side (23) from the fourth narrow side (23) over part of the length of the narrow sides (20, 22) adjacent to the fourth narrow side (23), wherein the second wall (27) has, at its end (28) facing away from the fourth narrow side (23), an edge (29) which extends up to the first height (25).
  2. Heat-shield element (14) according to Claim 1, wherein the heat-shield element (14) consists of a metal or metal alloy which is capable of withstanding high temperatures.
  3. Heat-shield element (14) according to either of Claims 1 and 2, wherein a plurality of cold air openings (30) arranged in the circumferential edge (24) is provided.
  4. Heat-shield element (14) according to Claim 3, wherein the cold air openings (30) are arranged at least in the region of the second wall (27) between the first (26) and the second wall (27).
  5. Heat-shield element (14) according to one of the preceding claims, further comprising an attachment opening (31) whose surround (32) extends from the first wall (17) up to the first height (25).
  6. Combustion chamber (1) having a combustion chamber wall with a burner-side and a turbine-side end (8), wherein the combustion chamber wall (13) has a circumferential direction comprising a number of heat-shield elements (14) according to one of the preceding claims, which are arranged circumferentially at the turbine-side end (8) of the combustion chamber wall (13), respectively forming two chambers (15, 16), wherein the fourth narrow side (23) is oriented toward the turbine-side end (8).
  7. Combustion chamber (1) according to Claim 6, wherein the heat-shield elements (14) are attached to the combustion chamber wall (13) by means of attachment bolts.
  8. Combustion chamber (1) according to either of Claims 6 and 7, wherein bores are introduced into the combustion chamber wall (13), such that coolant can be supplied to the heat-shield elements (14).
  9. Combustion chamber (1) according to one of Claims 6 to 8, wherein at least one supply duct per heat-shield element (14) is arranged in the combustion chamber wall (13) in the region of the respective second wall (27) and opens into a plenum (36) which at least partially surrounds the combustion chamber (1).
  10. Gas turbine having a combustion chamber (1) according to one of Claims 6 to 9, wherein the gas turbine comprises at least one tapping (33) for compressor air, which opens into the plenum (36) via at least one line (35) having a valve (34).
EP13712711.4A 2012-03-15 2013-03-12 Heat-shield element for a compressor-air bypass around the combustion chamber Not-in-force EP2809994B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012204103A DE102012204103A1 (en) 2012-03-15 2012-03-15 Heat shield element for a compressor air bypass around the combustion chamber
PCT/EP2013/055007 WO2013135702A2 (en) 2012-03-15 2013-03-12 Heat-shield element for a compressor-air bypass around the combustion chamber

Publications (2)

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EP2809994A2 EP2809994A2 (en) 2014-12-10
EP2809994B1 true EP2809994B1 (en) 2016-05-04

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US (1) US20150027128A1 (en)
EP (1) EP2809994B1 (en)
CN (1) CN104169648B (en)
DE (1) DE102012204103A1 (en)
RU (1) RU2622590C2 (en)
WO (1) WO2013135702A2 (en)

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Publication number Publication date
RU2014141355A (en) 2016-05-10
CN104169648A (en) 2014-11-26
RU2622590C2 (en) 2017-06-16
EP2809994A2 (en) 2014-12-10
WO2013135702A3 (en) 2013-11-14
DE102012204103A1 (en) 2013-09-19
CN104169648B (en) 2016-03-02
WO2013135702A2 (en) 2013-09-19
US20150027128A1 (en) 2015-01-29

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