EP2812636A2 - Annular-combustion-chamber bypass - Google Patents

Annular-combustion-chamber bypass

Info

Publication number
EP2812636A2
EP2812636A2 EP13710388.3A EP13710388A EP2812636A2 EP 2812636 A2 EP2812636 A2 EP 2812636A2 EP 13710388 A EP13710388 A EP 13710388A EP 2812636 A2 EP2812636 A2 EP 2812636A2
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
annular combustion
ring
outer shell
heat shield
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
EP13710388.3A
Other languages
German (de)
French (fr)
Other versions
EP2812636B1 (en
Inventor
Francois Benkler
Thomas Brandenburg
Olga Deiss
Thomas Grieb
Marco Link
Nicolas Savilius
Daniel Vogtmann
Jan Wilkes
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Publication of EP2812636A2 publication Critical patent/EP2812636A2/en
Application granted granted Critical
Publication of EP2812636B1 publication Critical patent/EP2812636B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • 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 an annular combustion chamber with a bypass for reducing the carbon monoxide emissions in part-load operation and to a gas turbine with such an annular combustion chamber.
  • the combustion temperature drops in the combustion chamber.
  • the primary zone temperature relevant for the carbon monoxide emissions also falls below a minimum value, whereby carbon monoxide is increasingly generated or expelled. Since this should be avoided, the usable partial load range of the gas turbine is limited.
  • the object of the invention is to provide an annular combustion chamber of the type mentioned, which allows a considerable increase in the usable partial load range.
  • the invention solves this problem by providing that in such an annular combustion chamber for a gas turbine with an outer shell which has at least one inlet opening for a burner and an outlet opening into a turbine chamber, closable in the outer shell in the region of the outlet and substantially parallel to Symmetryeachse the annular combustion chamber aligned channels are provided, can be guided by the Verêtrendluft into the annular combustion chamber.
  • compressor air can be introduced in a region at the end of the combustion chamber without participating in the combustion, that is, it is returned to the air-fuel mixture only after the combustion process. This causes the greasy mixture in the combustion chamber to become higher
  • the annular combustion chamber comprises a last row of heat shield plates arranged in the region of the outlet in the interior of the annular combustion chamber on the outer shell and a penultimate row of heat shield plates arranged in the direction of the at least one inlet opening next to the last row, between the last and penultimate Series of heat shield plates in the region of the channels a gap is provided. Through this gap, the compressor discharge air can flow undisturbed into the combustion chamber.
  • an adjusting device which comprises ring segments which form a ring which is aligned coaxially with the annular combustion chamber and axially displaceable relative to the annular combustion chamber.
  • the ring segments have the advantage of easier assembly and disassembly. It is expedient if the ring of the adjusting device is continuously displaceable in order to set as desired a desired gap size and thus to be able to remove a certain amount of air from the Verêtrendluft prior to combustion can.
  • the ring segments on their turbine side facing away from essays for engagement in the channels are trapezoidal.
  • the air to be passed through the channels can be set very precisely.
  • the channels can of course be completely closed.
  • the ring is moved by a mechanism only in the axial direction.
  • Such a mechanism for controlling and moving the ring segments So this can be done via motors, levers, hydraulic mechanisms, etc., the z. B. axially move the ring on rails or other motion elements.
  • these metrics also be mounted inside or outside of the housing.
  • the attachments of the ring segments have a thermal barrier coating (TBC) on their surfaces exposed to the hot gas of the combustion.
  • TBC thermal barrier coating
  • the interior of the outer shell in the region of the gap between see the last and the penultimate row of the heat shield plates, ie between the openings of the channels to the combustion chamber interior towards a thermal barrier coating In prior art annular combustion chambers, the last and penultimate rows of heat shield plates still abut each other and the interior of the outer shell was sufficiently protected by the heat shield plates. Due to the gap caused by the invention, the outer shell in this area is more exposed to the combustion gases.
  • the invention can be implemented relatively easily, since the ring segments, for example two ring halves, are simple components which only have to be displaced axially.
  • FIG. 2 shows the turbine-facing side of the annular combustion chamber with adjusting device on the outer shell and bypass channels
  • FIG. 3 shows a half-ring of the adjusting device for the bypass
  • FIG. 4 shows a metal heat shield plate according to the prior art
  • Figure 5 shows a metallic heat shield plate for the annular combustion chamber according to the invention
  • FIG. 1 shows, schematically and by way of example, the combustion system of an annular combustion chamber 1 according to the invention.
  • the annular combustion chamber 1 consists of a closed ring which is arranged around a rotor axis 2.
  • Burner 3 are arranged in the upper region of the combustion chamber 1 in inlet openings 4. There, the mixing of the fuel 5 with the compressor air 6 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet 7, the hot combustion gases pass into the turbine chamber 8, where they meet the first stationary vane 9.
  • the annular combustion chamber 1 is lined with ceramic heat shields 10 and metallic heat shields 11, which are attached to the outer shell 12.
  • an adjusting device 15 is provided on the outer side of the outer shell 12, as shown in FIG.
  • the adjusting device 15 has ring segments 16, for example, two half rings, as shown in Figure 3 one. With appropriate essays 17 certain gap sizes can be set in the channels 14, or they are even completely closed.
  • FIG. 4 shows such a heat shield plate 18 of the last row of a prior art annular combustion chamber as well as the dashed line cut around a metal heat shield plate 11 as shown in FIG. 5 and required for the present invention
  • Figure 6 shows a view of the inside of the annular combustion chamber 1 with the last 11 and penultimate 13 Hitzeschildplatten #2 and the openings 20 of the channels 14 in the outer shell 12 for the air bypass at partial load.
  • the attachments 17 of the ring segments 16 on their surfaces exposed to the hot gas of the combustion also have a thermal barrier coating.

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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention relates to an annular combustion chamber (1) for a gas turbine having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) which opens into a turbine chamber (8), wherein ducts (14) which can be closed, which are oriented substantially parallel to the symmetry axis (2) of the annular combustion chamber (1), and through which final compressor air can be guided into the annular combustion chamber (1) are provided in the outer shell (12) in the region of the outlet (7). Furthermore, the invention relates to a gas turbine.

Description

Beschreibung description

Ringbrennkammer-Bypass Die Erfindung betrifft eine Ringbrennkammer mit einem Bypass zur Verringerung der Kohlenmonoxidemissionen im Teillastbetrieb sowie eine Gasturbine mit einer solchen Ringbrennkammer . Im Teillastbetrieb der Gasturbine fällt die Verbrennungstemperatur in der Brennkammer ab. Dadurch fällt auch die für die Kohlenmonoxidemissionen relevante Primärzonentemperatur unter einen Minimalwert, wodurch verstärkt Kohlenmonoxid erzeugt bzw. ausgestoßen wird. Da dies vermieden werden soll, ist der nutzbare Teillastbereich der Gasturbine begrenzt. The invention relates to an annular combustion chamber with a bypass for reducing the carbon monoxide emissions in part-load operation and to a gas turbine with such an annular combustion chamber. In part-load operation of the gas turbine, the combustion temperature drops in the combustion chamber. As a result, the primary zone temperature relevant for the carbon monoxide emissions also falls below a minimum value, whereby carbon monoxide is increasingly generated or expelled. Since this should be avoided, the usable partial load range of the gas turbine is limited.

Aufgabe der Erfindung ist es, eine Ringbrennkammer der eingangs genannten Art bereitzustellen, die eine beträchtliche Vergrößerung des nutzbaren Teillastbereichs ermöglicht. The object of the invention is to provide an annular combustion chamber of the type mentioned, which allows a considerable increase in the usable partial load range.

Die Erfindung löst diese Aufgabe, indem sie vorsieht, dass bei einer derartigen Ringbrennkammer für eine Gasturbine mit einer Außenschale die mindestens eine Einlassöffnung für einen Brenner und einen in einen Turbinenraum mündenden Auslass aufweist, in der Außenschale im Bereich des Auslasses verschließbare und im Wesentlichen parallel zur Symmetrieachse der Ringbrennkammer ausgerichtete Kanäle vorgesehen sind, durch die Verdichterendluft in die Ringbrennkammer führbar ist . The invention solves this problem by providing that in such an annular combustion chamber for a gas turbine with an outer shell which has at least one inlet opening for a burner and an outlet opening into a turbine chamber, closable in the outer shell in the region of the outlet and substantially parallel to Symmetryeachse the annular combustion chamber aligned channels are provided, can be guided by the Verdichterendluft into the annular combustion chamber.

Durch diese Maßnahme kann Verdichterluft in einem Bereich am Ende der Brennkammer eingeführt werden, ohne an der Verbrennung teilzunehmen, d.h., sie wird erst nach dem Verbrennungs- prozess wieder dem Luft-Brennstoffgemisch zugeführt. Das be- wirkt, dass das fettere Gemisch im Brennraum unter höherenBy this measure, compressor air can be introduced in a region at the end of the combustion chamber without participating in the combustion, that is, it is returned to the air-fuel mixture only after the combustion process. This causes the greasy mixture in the combustion chamber to become higher

Temperaturen verbrannt werden kann und somit die Kohlenmonoxidemissionen im Teillastbetrieb verringert werden können. In einer vorteilhaften Ausführungsform umfasst die Ringbrennkammer eine im Bereich des Auslasses im Inneren der Ringbrennkammer an der Außenschale in Umfangsrichtung angeordnete letzte Reihe von Hitzeschildplatten und eine in Richtung der mindestens einen Einlassöffnung neben der letzten Reihe angeordnete vorletzte Reihe von Hitzeschildplatten, wobei zwischen der letzten und vorletzten Reihe von Hitzeschildplatten im Bereich der Kanäle ein Spalt vorgesehen ist. Durch diesen Spalt kann die Verdichterendluft ungestört in die Brennkammer einströmen. Temperatures can be burned and thus the carbon monoxide emissions can be reduced in partial load operation. In an advantageous embodiment, the annular combustion chamber comprises a last row of heat shield plates arranged in the region of the outlet in the interior of the annular combustion chamber on the outer shell and a penultimate row of heat shield plates arranged in the direction of the at least one inlet opening next to the last row, between the last and penultimate Series of heat shield plates in the region of the channels a gap is provided. Through this gap, the compressor discharge air can flow undisturbed into the combustion chamber.

Weiterhin ist es vorteilhaft, wenn zum Schließen und Öffnen der Kanäle an der Außenseite der Außenschale eine Stellvorrichtung vorgesehen ist, die Ringsegmente umfasst, die einen Ring bilden, der koaxial zur Ringbrennkammer ausgerichtet und bezogen auf die Ringbrennkammer axial verschiebbar ist. Die Ringsegmente haben den Vorteil der einfacheren Montage bzw. Demontage . Dabei ist es zweckmäßig, wenn der Ring der Stellvorrichtung stufenlos verschiebbar ist, um je nach Bedarf eine gewünschte Spaltgröße einstellen und somit eine bestimmte Luftmenge aus der Verdichterendluft vor der Verbrennung entnehmen zu können . Furthermore, it is advantageous if, for closing and opening the channels on the outer side of the outer shell, an adjusting device is provided which comprises ring segments which form a ring which is aligned coaxially with the annular combustion chamber and axially displaceable relative to the annular combustion chamber. The ring segments have the advantage of easier assembly and disassembly. It is expedient if the ring of the adjusting device is continuously displaceable in order to set as desired a desired gap size and thus to be able to remove a certain amount of air from the Verdichterendluft prior to combustion can.

In einer vorteilhaften Ausführung der Erfindung weisen die Ringsegmente auf ihrer turbinenabgewandten Seite Aufsätze zum Eingriff in die Kanäle auf. Dabei ist es zweckmäßig, wenn die Aufsätze trapezförmig ausgebildet sind. Durch die Aufsätze, insbesondere durch ihre Trapezform lässt sich die durch die Kanäle zu leitende Luftmenge besonders genau einstellen. Die Kanäle können natürlich auch ganz verschlossen werden. Dabei wird der Ring über einen Mechanismus nur in axialer Richtung bewegt. Für einen solchen Mechanismus zur Steuerung und Bewe- gung der Ringsegmente gibt es verschiedene Möglichkeiten. So kann dies über Motoren, Hebel-, Hydraulikmechanismen, etc. geschehen, die z. B. den Ring auf Schienen oder anderen Bewegungselementen axial verschieben. Wahlweise können diese Me- chanismen auch innerhalb oder außerhalb des Gehäuses angebracht sein. In an advantageous embodiment of the invention, the ring segments on their turbine side facing away from essays for engagement in the channels. It is expedient if the essays are trapezoidal. Through the essays, in particular by their trapezoidal shape, the air to be passed through the channels can be set very precisely. The channels can of course be completely closed. The ring is moved by a mechanism only in the axial direction. There are various possibilities for such a mechanism for controlling and moving the ring segments. So this can be done via motors, levers, hydraulic mechanisms, etc., the z. B. axially move the ring on rails or other motion elements. Optionally, these metrics also be mounted inside or outside of the housing.

Im Hinblick auf die hohen Temperaturen im Betrieb der Ring- brennkammer ist es vorteilhaft, wenn die Aufsätze der Ringsegmente auf ihren dem Heißgas der Verbrennung ausgesetzten Oberflächen eine Wärmedämmschicht (thermal barrier coating, TBC) aufweisen. Aus demselben Grund ist es zweckmäßig, wenn auch das Innere der Außenschale im Bereich des Spaltes zwi- sehen der letzten und der vorletzten Reihe der Hitzeschildplatten, also zwischen den Öffnungen der Kanäle zum Brennkammerinneren hin eine Wärmedämmschicht aufweist. In Ringbrennkammern aus dem Stand der Technik grenzen die letzte und die vorletzte Reihe der Hitzeschildplatten noch aneinander an und das Innere der Außenschale war durch die Hitzeschildplatten ausreichend geschützt. Durch den erfindungsbedingt entstandenen Spalt ist die Außenschale in diesem Bereich den Heißgasen der Verbrennung verstärkt ausgesetzt. Es ist weiterhin zweckmäßig, wenn die letzte Reihe von Hitzeschildplatten, die von allen Hitzeschildplatten von der Kernzone der Verbrennung am weitesten entfernt liegt, metallisch und die vorletzte Reihe keramisch ist, weil einerseits die Einsatztemperatur von keramischen Werkstoffen deutlich über der maximalen Einsatztemperatur von hochwarmfesten Metalllegierungen liegt und andererseits die hochwarmfesten metallischen Legierungen eine geringere Sprodigkeit und ein besseres Wärme- und Temperaturleitverhalten aufweisen. Mit der Erfindung wird schließlich eine neuartige Gasturbine angegeben, in welche eine erfindungsgemäße Ringbrennkammer integriert ist. In view of the high temperatures during operation of the annular combustion chamber, it is advantageous if the attachments of the ring segments have a thermal barrier coating (TBC) on their surfaces exposed to the hot gas of the combustion. For the same reason, it is expedient if the interior of the outer shell in the region of the gap between see the last and the penultimate row of the heat shield plates, ie between the openings of the channels to the combustion chamber interior towards a thermal barrier coating. In prior art annular combustion chambers, the last and penultimate rows of heat shield plates still abut each other and the interior of the outer shell was sufficiently protected by the heat shield plates. Due to the gap caused by the invention, the outer shell in this area is more exposed to the combustion gases. It is also useful if the last row of heat shield plates, which is the farthest from all heat shield plates of the core zone of combustion, metallic and the penultimate row is ceramic, because on the one hand, the operating temperature of ceramic materials is well above the maximum operating temperature of high temperature metal alloys and on the other hand, the high temperature metallic alloys have less spatter and better thermal and thermal conductivity. With the invention, finally, a novel gas turbine is specified, in which an annular combustion chamber according to the invention is integrated.

Durch die stufenlos einstellbare Stellvorrichtung gemäß der Erfindung zum Einleiten von Verdichterendluft in eine Zone am Ende der Brennkammer, d.h. nachdem die Verbrennung stattgefunden hat, lassen sich Kohlenmonoxidemissionen im Teillast- betrieb verringern, weil sich aufgrund einer fetteren Mischung höhere Verbrennungstemperaturen einstellen. Due to the infinitely adjustable adjusting device according to the invention for introducing compressor discharge air into a zone at the end of the combustion chamber, ie after the combustion has taken place, carbon monoxide emissions in the partial load reduce operation because of a richer mixture to set higher combustion temperatures.

Gegenüber aktuellen Designs erfolgt kein Kühlluftmehr- verbrauch im Grundlastbetrieb. Compared to current designs, there is no additional cooling air consumption in base load operation.

Weiterhin lässt sich die Erfindung relativ einfach umsetzen, da die Ringsegmente, beispielsweise zwei Ringhälften, einfache Bauteile sind, die nur axial verschoben werden müssen. Furthermore, the invention can be implemented relatively easily, since the ring segments, for example two ring halves, are simple components which only have to be displaced axially.

Die Erfindung wird beispielhaft anhand der Zeichnungen näher erläutert. Es zeigen schematisch und nicht maßstäblich: The invention will be explained in more detail by way of example with reference to the drawings. Shown schematically and not to scale:

Figur 1 ein Verbrennungssystem mit einer Ringbrennkammer nach der Erfindung, 1 shows a combustion system with an annular combustion chamber according to the invention,

Figur 2 die der Turbine zugewandte Seite der Ringbrennkammer mit Stellvorrichtung auf der Außenschale und Bypasskanälen, Figur 3 einen Halbring der Stellvorrichtung für den Bypass, Figur 4 eine metallische Hitzeschildplatte nach dem Stand der Technik,  2 shows the turbine-facing side of the annular combustion chamber with adjusting device on the outer shell and bypass channels, FIG. 3 shows a half-ring of the adjusting device for the bypass, FIG. 4 shows a metal heat shield plate according to the prior art,

Figur 5 eine metallische Hitzeschildplatte für die Ringbrennkammer nach der Erfindung und  Figure 5 shows a metallic heat shield plate for the annular combustion chamber according to the invention and

Figur 6 die Innenseite der Ringbrennkammer im Bereich des Auslasses .  6 shows the inside of the annular combustion chamber in the region of the outlet.

Die Figur 1 zeigt schematisch und beispielhaft das Verbrennungssystem einer Ringbrennkammer 1 nach der Erfindung. Die Ringbrennkammer 1 besteht aus einem geschlossenen Ring der um eine Rotorachse 2 angeordnet ist. Brenner 3 sind im oberen Bereich der Brennkammer 1 in Einlassöffnungen 4 angeordnet. Dort findet die Vermischung des Brennstoffs 5 mit der Verdichterluft 6 statt. In der Brennkammer 1 erfolgt die eigentliche Verbrennung. Durch den Auslass 7 gelangen die heißen Verbrennungsgase in den Turbinenraum 8, wo sie auf die erste stehende Leitschaufel 9 treffen. Zum Schutz vor Verzunderungen ist die Ringbrennkammer 1 mit keramischen Hitzeschilden 10 und metallischen Hitzeschilden 11 ausgekleidet, die an der Außenschale 12 befestigt sind. Gemäß der Erfindung wird die Brennkammeraußenschale 12 im Bereich des Auslasses 7 zwischen der letzten keramischen Hitzeschildreihe 13 (= der vorletzten Hitzeschildreihe) und der metallischen Einlaufschalenplatte (= der letzten Hitzeschildreihe 11) mit Kanälen 14 versehen, die im Wesentlichen parallel zur Achse 2 der Ringbrennkammer 1 orientiert sind. FIG. 1 shows, schematically and by way of example, the combustion system of an annular combustion chamber 1 according to the invention. The annular combustion chamber 1 consists of a closed ring which is arranged around a rotor axis 2. Burner 3 are arranged in the upper region of the combustion chamber 1 in inlet openings 4. There, the mixing of the fuel 5 with the compressor air 6 takes place. In the combustion chamber 1, the actual combustion takes place. Through the outlet 7, the hot combustion gases pass into the turbine chamber 8, where they meet the first stationary vane 9. To protect against scaling, the annular combustion chamber 1 is lined with ceramic heat shields 10 and metallic heat shields 11, which are attached to the outer shell 12. According to the invention, the combustion chamber outer shell 12 is provided in the region of the outlet 7 between the last ceramic heat shield row 13 (= the penultimate heat shield row) and the metallic inlet shell plate (= the last heat shield row 11) with channels 14 which are substantially parallel to the axis 2 of the annular combustion chamber. 1 are oriented.

Damit diese Kanäle 14 je nach Bedarf geschlossen oder geöff- net werden können, ist an der Außenseite der Außenschale 12 eine Stellvorrichtung 15 vorgesehenen, wie sie in Figur 2 dargestellt ist. Die Stellvorrichtung 15 weist Ringsegmente 16, beispielsweise zwei Halbringe, auf, wie in Figur 3 einer gezeigt ist. Mit entsprechenden Aufsätzen 17 können bestimmte Spaltgrößen in den Kanälen 14 eingestellt, bzw. diese sogar ganz verschlossen werden. So that these channels 14 can be closed or opened as required, an adjusting device 15 is provided on the outer side of the outer shell 12, as shown in FIG. The adjusting device 15 has ring segments 16, for example, two half rings, as shown in Figure 3 one. With appropriate essays 17 certain gap sizes can be set in the channels 14, or they are even completely closed.

Um diese Lufteinströmung in die Ringbrennkammer 1 zu ermöglichen, sind die metallischen Einlaufschalenplatten, d.h. die die Platten der letzten Hitzeschildreihe 11 gegenüber einer Hitzeschildplatte 18 der letzten Reihe einer Ringbrennkammer aus dem Stand der Technik verkürzt. Figur 4 zeigt eine solche Hitzeschildplatte 18 der letzten Reihe einer Ringbrennkammer aus dem Stand der Technik, sowie die an der gestrichelten Li- nie vorgenommene Kürzung um eine metallische Hitzeschilplatte 11 zu erhalten, wie sie Figur 5 zeigt und wie sie für die vorliegende Erfindung benötigt wird. In order to allow this air inflow into the annular combustion chamber 1, the metallic inlet shell plates, i. which shortens the plates of the last heat shield row 11 with respect to a heat shield plate 18 of the last row of a ring combustion chamber of the prior art. FIG. 4 shows such a heat shield plate 18 of the last row of a prior art annular combustion chamber as well as the dashed line cut around a metal heat shield plate 11 as shown in FIG. 5 and required for the present invention ,

Figur 6 zeigt eine Sicht der Innenseite der Ringbrennkammer 1 mit letzter 11 und vorletzter 13 Hitzeschildplattenreihe sowie die Öffnungen 20 der Kanäle 14 in der Außenschale 12 für den Luftbypass bei Teillast. Figure 6 shows a view of the inside of the annular combustion chamber 1 with the last 11 and penultimate 13 Hitzeschildplattenreihe and the openings 20 of the channels 14 in the outer shell 12 for the air bypass at partial load.

Da gemäß der Erfindung die letzte Reihe 11 der Hitzeschild- platten gegenüber den Hitzeschildplatten aus dem Stand derSince according to the invention, the last row 11 of the heat shield plates relative to the heat shield plates from the prior

Technik verkürzt ist und an der Außenschale 12 der Ringbrennkammer 1 so angeordnet ist, dass sie nicht mehr unmittelbar an die vorletzte Reihe der Hitzeschildplatten 13 anschließt, besteht ein Spalt 19 in Umfangsrichtung der Ringbrennkammer 1 ohne den bisherigen Hitzeschutz. In diesem Spalt 19 öffnen sich die Kanäle 14 in das Innere der Ringbrennkammer 1. Die Außenschale 12 zwischen diesen Öffnungen 20 ist im Betrieb der Ringbrennkammer 1 sehr hohen Temperaturen ausgesetzt. Um die Außenschale 12 trotz Spalt 19 vor diesen Temperaturen zu schützen, ist das Innere der Außenschale 12 im Bereich des Spalts 19 zwischen der letzten 11 und der vorletzten Reihe 13 der Hitzeschildplatten, also zwischen den Öffnungen 20 der Kanäle 14 zum Brennkammerinneren hin mit einer Wärmedämmschicht versehen. Technique is shortened and is arranged on the outer shell 12 of the annular combustion chamber 1 so that it no longer connects directly to the penultimate row of the heat shield plates 13, there is a gap 19 in the circumferential direction of the annular combustion chamber 1 without the previous heat protection. In this gap 19, the channels 14 open into the interior of the annular combustion chamber 1. The outer shell 12 between these openings 20 is exposed to very high temperatures during operation of the annular combustion chamber 1. In order to protect the outer shell 12 despite gap 19 from these temperatures, the interior of the outer shell 12 in the region of the gap 19 between the last 11 and the penultimate row 13 of the heat shield plates, ie between the openings 20 of the channels 14 to the combustion chamber interior out with a thermal barrier coating Mistake.

Auch die Aufsätze 17 der Ringsegmente 16 auf ihren dem Heißgas der Verbrennung ausgesetzten Oberflächen weisen eine Wär- medämmschicht auf. The attachments 17 of the ring segments 16 on their surfaces exposed to the hot gas of the combustion also have a thermal barrier coating.

Claims

Ringbrennkammer (1) für eine Gasturbine mit einer Außenschale (12) die mindestens eine Einlassöffnung (4) für einen Brenner (3) und einen in einen Turbinenraum (8) mündenden Auslass (7) aufweist, dadurch gekennzeichnet, dass in der Außenschale (12) im Bereich des Auslasses (7) verschließbare und im Wesentlichen parallel zur Symmetrieachse (2) der Ringbrennkammer (1) ausgerichtete KanäleRing combustion chamber (1) for a gas turbine having an outer shell (12) which has at least one inlet opening (4) for a burner (3) and an outlet (7) opening into a turbine chamber (8), characterized in that in the outer shell (12 ) in the region of the outlet (7) closable and substantially parallel to the axis of symmetry (2) of the annular combustion chamber (1) aligned channels (14) vorgesehen sind, durch die Verdichterendluft in die Ringbrennkammer (1) führbar ist. (14) are provided, through the compressor discharge air in the annular combustion chamber (1) can be guided. Ringbrennkammer (1) nach Anspruch 1, umfassend eine im Bereich des Auslasses (7) im Inneren der Ringbrennkammer (1) an der Außenschale (12) in Umfangsrichtung angeordnete letzte Reihe von Hitzeschildplatten (11) und eine in Richtung der mindestens einen Einlassöffnung (4) neben der letzten Reihe (11) angeordnete vorletzte Reihe von Hitzeschildplatten (13), wobei zwischen der letzten (11) und vorletzten (13) Reihe von Hitzeschildplatten im Bereich der Öffnung (20) der Kanäle (14) in das Innere der Ringbrennkammer (1) ein Spalt (19) vorgesehen ist. Annular combustion chamber (1) according to claim 1, comprising a last row of heat shield plates (11) arranged in the circumferential direction in the region of the outlet (7) in the interior of the annular combustion chamber (1) and directed towards the at least one inlet opening (4) ) next to the last row (11) arranged next to last row of heat shield plates (13), wherein between the last (11) and penultimate (13) series of heat shield plates in the region of the opening (20) of the channels (14) into the interior of the annular combustion chamber ( 1) a gap (19) is provided. Ringbrennkammer (1) nach einem der vorhergehenden Ansprüche, wobei zum Schließen und Öffnen der Kanäle (14) an der Außenseite der Außenschale (12) eine StellvorrichtungAnnular combustion chamber (1) according to one of the preceding claims, wherein for closing and opening the channels (14) on the outer side of the outer shell (12) an adjusting device (15) vorgesehen ist, die Ringsegmente (16) umfasst, die einen Ring bilden, der koaxial zur Ringbrennkammer (1) ausgerichtet ist und bezogen auf die Ringbrennkammer (1) axial verschiebbar ist. (15) is provided, the ring segments (16) which form a ring which is aligned coaxially with the annular combustion chamber (1) and with respect to the annular combustion chamber (1) is axially displaceable. Ringbrennkammer (1) nach Anspruch 3, wobei der Ring stufenlos verschiebbar ist. Ring combustion chamber (1) according to claim 3, wherein the ring is continuously displaceable. Ringbrennkammer (1) nach einem der Ansprüche 3 oder 4, wobei die Ringsegmente (16) auf ihrer turbinenabgewandten Seite Aufsätze (17) zum Eingriff in die Kanäle (14) aufweisen . Ring combustion chamber (1) according to one of claims 3 or 4, wherein the ring segments (16) on their turbine side facing away from essays (17) for engagement in the channels (14). 6. Ringbrennkammer (1) nach Anspruch 5, wobei die Aufsätze (17) trapezförmig ausgebildet sind. 6. annular combustion chamber (1) according to claim 5, wherein the attachments (17) are trapezoidal. 7. Ringbrennkammer (1) nach einem der Ansprüche 5 oder 6, wobei die Aufsätze (17) auf Heißgas ausgesetzten Oberflächen eine Wärmedämmschicht aufweisen. 7. annular combustion chamber (1) according to any one of claims 5 or 6, wherein the attachments (17) exposed to hot gas surfaces have a thermal barrier coating. 8. Ringbrennkammer (1) nach einem der Ansprüche 2 bis 7, wobei das Innere der Außenschale (12) im Bereich des Spalts (19) eine Wärmedämmschicht aufweist. 8. annular combustion chamber (1) according to one of claims 2 to 7, wherein the interior of the outer shell (12) in the region of the gap (19) has a thermal barrier coating. 9. Ringbrennkammer (1) nach einem der vorhergehenden Ansprüche, wobei die letzte Reihe von Hitzeschildplatten (11) metallisch und die vorletzte Reihe (13) keramisch ist. 9. annular combustion chamber (1) according to any one of the preceding claims, wherein the last row of heat shield plates (11) metallic and the penultimate row (13) is ceramic. 10. Gasturbine mit einer Ringbrennkammer (1) nach einem der vorhergehenden Ansprüche . 10. Gas turbine with an annular combustion chamber (1) according to one of the preceding claims.
EP13710388.3A 2012-03-16 2013-03-15 Annular-combustion-chamber bypass Not-in-force EP2812636B1 (en)

Applications Claiming Priority (2)

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DE102012204162A DE102012204162A1 (en) 2012-03-16 2012-03-16 Ring combustor bypass
PCT/EP2013/055344 WO2013135859A2 (en) 2012-03-16 2013-03-15 Annular-combustion-chamber bypass

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EP2812636A2 true EP2812636A2 (en) 2014-12-17
EP2812636B1 EP2812636B1 (en) 2016-06-29

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DE102012204162A1 (en) 2013-09-19
WO2013135859A3 (en) 2013-11-14
CN104169649B (en) 2016-11-09
US20150007573A1 (en) 2015-01-08
CN104169649A (en) 2014-11-26
KR20140138710A (en) 2014-12-04
WO2013135859A2 (en) 2013-09-19
EP2812636B1 (en) 2016-06-29

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