EP2812636B1 - Annular-combustion-chamber bypass - Google Patents

Annular-combustion-chamber bypass Download PDF

Info

Publication number
EP2812636B1
EP2812636B1 EP13710388.3A EP13710388A EP2812636B1 EP 2812636 B1 EP2812636 B1 EP 2812636B1 EP 13710388 A EP13710388 A EP 13710388A EP 2812636 B1 EP2812636 B1 EP 2812636B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
annular combustion
outer shell
annular
ducts
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
Application number
EP13710388.3A
Other languages
German (de)
French (fr)
Other versions
EP2812636A2 (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

Images

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 a gas turbine with such an annular combustion chamber.
  • 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 achieves this object by providing an annular combustor for a gas turbine according to claim 1.
  • compressor air can be introduced in a region at the end of the combustion chamber, without participating in the combustion, that is, it is fed back to the air-fuel mixture after the combustion process.
  • 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.
  • the ring segments have the advantage of easier assembly and disassembly.
  • 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.
  • 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 mechanisms can also be mounted inside or outside 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 the last and the penultimate row of the heat shield plates, ie between the openings of the channels to the combustion chamber interior has a heat-insulating layer.
  • 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 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 brittleness and better thermal and thermal conductivity.
  • the infinitely adjustable actuator 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, permits carbon monoxide emissions to be carried out in part-load operation reduce, because set due to a richer mixture higher combustion temperatures.
  • 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. 1 shows schematically and exemplarily 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.
  • an adjusting device 15 is provided on the outside of the outer shell 12, as in FIG. 2 is shown.
  • the adjusting device 15 has ring segments 16, for example, two half rings, as in FIG. 3 one is shown. With appropriate essays 17 certain gap sizes can be set in the channels 14, or they are even completely closed.
  • the metallic inlet shell plates ie the plates of the last heat shield row 11 are shortened relative 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 ring combustion chamber of the prior art, as well as the dashed line cut to a metallic heat-shaving plate 11 to obtain, as FIG. 5 shows and how it is needed for the present invention.
  • FIG. 6 shows a view of the inside of the annular combustion chamber 1 with the last 11 and penultimate heat shield plate row 13 and the openings 20 of the channels 14 in the outer shell 12 for the air bypass at partial load.
  • the last row 11 of the heat shield plates is shortened compared to the heat shield plates of the prior art and is arranged on the outer shell 12 of the annular combustion chamber 1 so that it no longer directly adjoins 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.
  • 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.
  • the interior of the outer shell 12 is 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.
  • the attachments 17 of the ring segments 16 on their exposed to the hot gas combustion surfaces 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)

Description

Die Erfindung betrifft eine Ringbrennkammer mit einem Bypass zur Verringerung der Kohlenmonoxidemissionen im Teillastbetrieb sowie eine Gasturbine mit einer solchen Ringbrennkammer.The invention relates to an annular combustion chamber with a bypass for reducing the carbon monoxide emissions in part-load operation and a gas turbine with such an annular combustion chamber.

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 begrenzet. Dokument DE 10 116 452 offenbart eine Ringbrennkammer nach Stand der Technik.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. document DE 10 116 452 discloses an annular combustor of the prior art.

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, eine Ringbrennkammer fur eine Gasturbine gemäß Anspruch 1 bereitzustellen.The invention achieves this object by providing an annular combustor for a gas turbine according to claim 1.

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 Verbrennungsprozess wieder dem Luft-Brennstoffgemisch zugeführt. Das bewirkt, dass das fettere Gemisch im Brennraum unter höheren Temperaturen verbrannt werden kann und somit die Kohlenmonoxidemissionen im Teillastbetrieb verringert werden können.By 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 fed back to the air-fuel mixture after the combustion process. This means that the greasy mixture in the combustion chamber can be burned at higher temperatures and thus the carbon monoxide emissions can be reduced in part-load operation.

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.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.

Die Ringsegmente haben den Vorteil der einfacheren Montage bzw. Demontage.The ring segments have the advantage of easier assembly and disassembly.

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.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 Bewegung 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 Mechanismen 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 mechanisms can also be mounted inside or outside the housing.

Im Hinblick auf die hohen Temperaturen im Betrieb der Ringbrennkammer 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 zwischen 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.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 the last and the penultimate row of the heat shield plates, ie between the openings of the channels to the combustion chamber interior has a heat-insulating layer. 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.

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 Sprödigkeit und ein besseres Wärme- und Temperaturleitverhalten aufweisen.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 brittleness and better thermal and thermal conductivity.

Mit der Erfindung wird schließlich eine neuartige Gasturbine angegeben, in welche eine erfindungsgemäße Ringbrennkammer integriert ist.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 Teillastbetrieb verringern, weil sich aufgrund einer fetteren Mischung höhere Verbrennungstemperaturen einstellen.The infinitely adjustable actuator 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, permits carbon monoxide emissions to be carried out in part-load operation reduce, because set due to a richer mixture higher combustion temperatures.

Gegenüber aktuellen Designs erfolgt kein Kühlluftmehrverbrauch im Grundlastbetrieb.Compared to current designs, there is no additional cooling air consumption during 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:

  • Figur 1 ein Verbrennungssystem mit einer Ringbrennkammer nach der Erfindung,
  • 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,
  • Figur 5 eine metallische Hitzeschildplatte für die Ringbrennkammer nach der Erfindung und
  • Figur 6 die Innenseite der Ringbrennkammer im Bereich des Auslasses.
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 combustion system with an annular combustion chamber according to the invention,
  • FIG. 2 the turbine facing side of the annular combustion chamber with adjusting device on the outer shell and bypass channels,
  • FIG. 3 a half-ring of the adjusting device for the bypass,
  • FIG. 4 a metallic heat shield plate according to the prior art,
  • FIG. 5 a metallic heat shield plate for the annular combustion chamber according to the invention and
  • FIG. 6 the inside of the annular combustion chamber in the area 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.The FIG. 1 shows schematically and exemplarily 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.

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.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 geöffnet 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 needed, an adjusting device 15 is provided on the outside of the outer shell 12, as in FIG. 2 is shown. The adjusting device 15 has ring segments 16, for example, two half rings, as in FIG. 3 one is shown. 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 Linie 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, ie the plates of the last heat shield row 11 are shortened relative 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 ring combustion chamber of the prior art, as well as the dashed line cut to a metallic heat-shaving plate 11 to obtain, as FIG. 5 shows and how it is needed 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. FIG. 6 shows a view of the inside of the annular combustion chamber 1 with the last 11 and penultimate heat shield plate row 13 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 Hitzeschildplatten gegenüber den Hitzeschildplatten aus dem Stand der 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.Since according to the invention the last row 11 of the heat shield plates is shortened compared to the heat shield plates of the prior art and is arranged on the outer shell 12 of the annular combustion chamber 1 so that it no longer directly adjoins 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 is 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 Wärmedämmschicht auf.The attachments 17 of the ring segments 16 on their exposed to the hot gas combustion surfaces have a thermal barrier coating.

Claims (9)

  1. 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) that opens into a turbine space (8), wherein ducts (14) are provided in the outer shell (12) in the region of the outlet (7), which ducts are closable and are oriented substantially parallel to the axis of symmetry (2) of the annular combustion chamber (1), and through these compressor outlet air can be guided into the annular combustion chamber (1), characterized in that an adjustment device (15), comprising ring segments (16) which form a ring that is oriented coaxially with the annular combustion chamber (1) and may be moved axially with respect to the annular combustion chamber (1), is provided on the exterior of the outer shell (12) for closing and opening the ducts (14).
  2. Annular combustion chamber (1) according to Claim 1, comprising a last row of heat-shield plates (11) arranged in the circumferential direction on the outer shell (12) in the region of the outlet (7) in the interior of the annular combustion chamber (1), and a second-to-last row of heat-shield plates (13) arranged next to the last row (11) in the direction of the at least one inlet opening (4), wherein a gap (19) is provided between the last (11) and second-to-last (13) rows of heat-shield plates, in the region of the opening (20) of the ducts (14) into the interior of the annular combustion chamber (1).
  3. Annular combustion chamber (1) according to either of the preceding claims, wherein the ring can be moved in a continuously variable manner.
  4. Annular combustion chamber (1) according to one of the preceding claims, wherein the ring segments (16) have, on their side facing away from the turbine, projections (17) for engaging in the ducts (14).
  5. Annular combustion chamber (1) according to Claim 4, wherein the projections (17) are of trapezoidal design.
  6. Annular combustion chamber (1) according to either of Claims 4 and 5, wherein the projections (17) have a thermal barrier coating on surfaces exposed to hot gas.
  7. Annular combustion chamber (1) according to one of Claims 2 to 6, wherein the interior of the outer shell (12) has a thermal barrier coating in the region of the gap (19).
  8. Annular combustion chamber (1) according to one of the preceding claims, wherein the last row of heat-shield plates (11) is metallic and the second-to-last row (13) is ceramic.
  9. Gas turbine having 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)

Application Number Priority Date Filing Date Title
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

Publications (2)

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

Family

ID=47901090

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13710388.3A Not-in-force EP2812636B1 (en) 2012-03-16 2013-03-15 Annular-combustion-chamber bypass

Country Status (6)

Country Link
US (1) US20150007573A1 (en)
EP (1) EP2812636B1 (en)
KR (1) KR20140138710A (en)
CN (1) CN104169649B (en)
DE (1) DE102012204162A1 (en)
WO (1) WO2013135859A2 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104566463B (en) * 2014-11-29 2016-12-07 哈尔滨广瀚燃气轮机有限公司 Gas turbine low discharging burning chamber conditioner
CN104807043A (en) * 2014-11-29 2015-07-29 哈尔滨广瀚燃气轮机有限公司 Annular combustion chamber of natural gas fuel gas turbine
DE102015202097A1 (en) * 2015-02-06 2016-08-11 Siemens Aktiengesellschaft Ring combustion chamber with bypass segment
DE102015205975A1 (en) * 2015-04-02 2016-10-06 Siemens Aktiengesellschaft Umführungs heat shield element
DE102015215207A1 (en) * 2015-08-10 2017-02-16 Siemens Aktiengesellschaft Combustion chamber for a gas turbine and heat shield element for lining such a combustion chamber
CN107923616B (en) * 2015-08-27 2019-12-13 西门子股份公司 Cooling air-optimized metal thermal insulation elements
CN108131399B (en) * 2017-11-20 2019-06-28 北京动力机械研究所 A kind of engine bearing seat cooling structure
EP3499125A1 (en) * 2017-12-12 2019-06-19 Siemens Aktiengesellschaft Pipe combustion chamber with ceramic cladding

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3958413A (en) * 1974-09-03 1976-05-25 General Motors Corporation Combustion method and apparatus
EP0660046B1 (en) * 1993-12-22 1999-12-01 Siemens Westinghouse Power Corporation Combustor bybass system for a gas turbine
US5636510A (en) * 1994-05-25 1997-06-10 Westinghouse Electric Corporation Gas turbine topping combustor
JP3846169B2 (en) * 2000-09-14 2006-11-15 株式会社日立製作所 Gas turbine repair method
JP2002317650A (en) * 2001-04-24 2002-10-31 Mitsubishi Heavy Ind Ltd Gas turbine combustor
SE523082C2 (en) * 2001-11-20 2004-03-23 Volvo Aero Corp Device at a combustion chamber of a gas turbine for controlling gas inflow to the combustion zone of the combustion chamber
US7631504B2 (en) * 2006-02-21 2009-12-15 General Electric Company Methods and apparatus for assembling gas turbine engines
US8281601B2 (en) * 2009-03-20 2012-10-09 General Electric Company Systems and methods for reintroducing gas turbine combustion bypass flow
US20110225947A1 (en) * 2010-03-17 2011-09-22 Benjamin Paul Lacy System and methods for altering air flow in a combustor
EP2423596A1 (en) * 2010-08-27 2012-02-29 Siemens Aktiengesellschaft Heat shield element
GB201200237D0 (en) * 2012-01-09 2012-02-22 Rolls Royce Plc A combustor for a gas turbine engine
DE102012204103A1 (en) * 2012-03-15 2013-09-19 Siemens Aktiengesellschaft Heat shield element for a compressor air bypass around the combustion chamber

Also Published As

Publication number Publication date
DE102012204162A1 (en) 2013-09-19
EP2812636A2 (en) 2014-12-17
KR20140138710A (en) 2014-12-04
CN104169649A (en) 2014-11-26
WO2013135859A3 (en) 2013-11-14
WO2013135859A2 (en) 2013-09-19
CN104169649B (en) 2016-11-09
US20150007573A1 (en) 2015-01-08

Similar Documents

Publication Publication Date Title
EP2812636B1 (en) Annular-combustion-chamber bypass
EP1005620B1 (en) Thermal shield component with recirculation of cooling fluid
EP3186498B1 (en) Gas turbine arrangement
EP2809994B1 (en) Heat-shield element for a compressor-air bypass around the combustion chamber
EP1654495A1 (en) Heat shield arrangement for a hot gas-guiding component, particularly for a combustion chamber of a gas turbine
EP2808611B1 (en) Injector for introducing a fuel-air mixture into a combustion chamber
EP3132202B1 (en) Bypass heat shield element
EP2184445A1 (en) Axial segmented vane support for a gas turbine
EP2852735B1 (en) Gas turbine
WO2009086982A1 (en) Compressor for a gas turbine
EP2230458A1 (en) Burner assembly for fluid fuels and method for producing a burner assembly
EP2411631B1 (en) Sealplate and rotor blade system
EP2409086B1 (en) Burner assembly for a gas turbine
EP1662202B1 (en) Burner for a gas turbine
EP1724526A1 (en) Shell for a Combustion Chamber, Gas Turbine and Method for Powering up and down a Gas Turbine.
EP2271876B1 (en) Burner arrangement for liquid fuels and method for producing a burner arrangement
EP3926238B1 (en) Gas turbine module with combustion chamber air bypass
EP1422479B1 (en) Chamber for the combustion of a fluid combustible mixture
EP2808610A1 (en) Gas turbine combustion chamber with tangential late lean injection
EP1221571B1 (en) Cooled combustion apparatus
EP2270397A1 (en) Gas turbine combustor and gas turbine
EP2808612A1 (en) Gas turbine combustion chamber with tangential late lean injection
EP1707758B1 (en) Shell Element for a Combustion Chamber and Combustion Chamber
EP1284392A1 (en) Combustion chamber
EP2159384A1 (en) Stator vane support for a gas turbine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140908

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

DAX Request for extension of the european patent (deleted)
REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502013003539

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F23R0003040000

Ipc: F23R0003080000

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/04 20060101ALI20151020BHEP

Ipc: F23R 3/08 20060101AFI20151020BHEP

Ipc: F23R 3/26 20060101ALI20151020BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20160126

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 809419

Country of ref document: AT

Kind code of ref document: T

Effective date: 20160715

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502013003539

Country of ref document: DE

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160929

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20160629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160930

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161029

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20161031

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502013003539

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

26N No opposition filed

Effective date: 20170330

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160929

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170315

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20171130

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170315

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170331

Ref country code: IT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170315

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170331

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170315

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170315

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170331

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20170331

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20180518

Year of fee payment: 6

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 809419

Country of ref document: AT

Kind code of ref document: T

Effective date: 20180315

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20130315

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502013003539

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20180315

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20191001

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20160629