EP2317227B1 - Burner for a turbine and gas turbine with same - Google Patents

Burner for a turbine and gas turbine with same Download PDF

Info

Publication number
EP2317227B1
EP2317227B1 EP10171616.5A EP10171616A EP2317227B1 EP 2317227 B1 EP2317227 B1 EP 2317227B1 EP 10171616 A EP10171616 A EP 10171616A EP 2317227 B1 EP2317227 B1 EP 2317227B1
Authority
EP
European Patent Office
Prior art keywords
burner
air
gap
chamber
head plate
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.)
Active
Application number
EP10171616.5A
Other languages
German (de)
French (fr)
Other versions
EP2317227A2 (en
EP2317227A3 (en
Inventor
Frank Reiss
Jaman El Masalme
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.)
MAN Energy Solutions SE
Original Assignee
MAN Energy Solutions SE
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 MAN Energy Solutions SE filed Critical MAN Energy Solutions SE
Publication of EP2317227A2 publication Critical patent/EP2317227A2/en
Publication of EP2317227A3 publication Critical patent/EP2317227A3/en
Application granted granted Critical
Publication of EP2317227B1 publication Critical patent/EP2317227B1/en
Active 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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
    • F23R2900/03045—Convection cooled combustion chamber walls provided with turbolators or means for creating turbulences to increase cooling
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers

Definitions

  • the invention relates to a burner for a turbine and a gas turbine equipped with such a burner.
  • burners of gas turbines are in DE 10 2006 048 842 A1 .
  • WO 96/04510 and in the magazine " ABBtechnik "from 4/1998 on pages 4 to 16 described.
  • a major objective with such burners is to make combustion in a large operating range stable, controlled, low in emissions and as complete as possible.
  • special components are used as "flame holders" to stabilize the combustion zone (zone of heat release).
  • Other burners are designed to provide stabilization near the wall - e.g. in the center of the burner - takes place. These components are thermally highly loaded, have a short life and must therefore be replaced often.
  • the invention has for its object to provide a burner for a turbine, in particular for a gas turbine, in which the central component or the flame holder can be effectively cooled without disturbing the / / combustion process in the burner.
  • the invention is further based on the object to provide a equipped with such a burner gas turbine.
  • a burner for a turbine in particular a gas turbine
  • the burner comprises: a housing in which an air collecting space, a combustion antechamber and a combustion chamber are formed, a burner top plate, which is arranged in the housing, so that the Burner head plate separates the combustion antechamber from the combustion chamber, a baffle plate which is arranged in the combustion antechamber so that the baffle plate divides the combustion pre-vent into a first subspace adjacent to an air feed fluidly connected to the air collection space and a second subspace adjacent to the burner head plate, wherein the baffle plate has a plurality of passage passages, which fluidly connect the first subspace with the second subspace, so that via the air supply from the air collecting space in the first subspace inflowing air flow through the passage passages in the second subspace and zugewan zu zu the second subspace
  • the back surface of the burner top plate can flow.
  • the burner top plate since cooling air is applied to the rear surface of the burner top plate so that efficient impingement cooling for the burner top plate is achieved, the burner top plate can be effectively achieved cooled and thus their thermal wear can be reduced.
  • the inventively proposed cooling thus significantly increases the life of the burner top plate. Since only the back of the burner top plate is charged with the cooling air, wherein the air is preferably supplied to an outer edge of the burner top plate to the combustion chamber, the air or cooling exerts no disturbing effect on the combustion process in the burner.
  • the baffle plate extends parallel to the burner top plate, so that air which has flowed into the second partial space impinges perpendicularly on the rear surface of the burner top plate.
  • a gap is provided on the outer circumference of the burner head plate, via which the second subspace is fluidly connected to the combustion chamber, so that air rebounding from the rear face of the burner head plate can flow out into the combustion chamber via the gap.
  • the cooling air can therefore not be introduced into the combustion chamber outside the edge of the burner top plate and thus the combustion process by the gap, as a result of which the air is retained in the overall process (burner, turbine).
  • the injection of the cooling air should be as far as possible "outsideā€, far away a mean recirculation flow of the burner, which ensures that a core zone of the recirculation flow is not disturbed.
  • the second subspace is bounded on the outside by an insertion part, wherein in a wall of the insert part is provided which extends perpendicular to the passages opening which fluidly connects the second subspace with the gap, so that bouncing from the rear surface of the burner head plate rebounding air can flow through the opening into the gap.
  • the cooling air can be routed across this opening, as required, transversely to the outer edge of the burner top plate or the combustion chamber, so that its influence on the combustion is minimized, and on the other hand, the air flow can be specifically influenced by its diameter.
  • the gap is formed as an annular gap, wherein in the wall of the insert part a plurality of perpendicular to the passages extending along a circumference of the gap distributed openings are provided, which fluidly connect the second subspace with the gap, so that rebounding air from the rear surface of the burner head can flow out into the gap via the openings.
  • the gap By forming the gap as an annular gap and by providing the circumferentially distributed plurality of openings, the air after cooling the burner top plate can be extremely evenly distributed in the combustion chamber, so that their influence on the combustion is further minimized.
  • the gap extends parallel to the passage passages, so that a flow direction of the air through the gap is parallel to a flow direction of the air through the passage passages.
  • a width of the gap is dimensioned such that a flow velocity of the Air at the exit from the gap is less than a flow velocity of the air entering the gap.
  • the width of the gap should be as large as possible to minimize the flow velocity of the air and thus its penetration into a main flow of combustion, which in turn ensures that the main flow is influenced as little as possible.
  • a plurality of passage openings are provided in the burner head plate, which fluidly connect the second subspace to the combustion chamber.
  • the through-openings each have a diameter in a range from 0.3 mm to 1.5 mm, so that the through-holes an effusion of the air flowed through the passage passages in the second sub-chamber through the burner head plate into the combustion chamber.
  • This embodiment of the invention advantageously supports both the cooling efficiency and the freedom from influencing the cooling air flow.
  • the burner top plate is formed by a porous material, so that in the second Subspace inflowed air can flow through pores of the burner head plate into the combustion chamber.
  • This embodiment of the invention is an advantageous way to dissipate the cooling air flow as possible without affecting the combustion and continued use of the air flow for Gesarntske after cooling.
  • an air discharge passage is provided in the second subspace, via which air rebounding from the rear face of the burner head plate can be fed into the combustion chamber downstream of the burner head plate with respect to a combustion process in the combustion chamber.
  • the advantage of these solutions is that an influence of the main flow and thus the combustion is excluded by the cooling air flow.
  • the usable pressure gradient of the cooling increases and thus a greater temperature reduction can be achieved.
  • the disadvantage of the solution is that the air can only partially or not at all be used for the gas turbine process.
  • a gas turbine with a burner according to one, several or all of the previously described embodiments of the invention is provided in any conceivable combination.
  • a burner 1 of a gas turbine (not completely shown) according to an embodiment of the invention comprises a housing 10, which in turn comprises a flame tube 11, in which the combustion V of an air-fuel gas mixture takes place, and a jacket 12, which Flame tube 11 surrounds. Between the flame tube 11 and the shell 12, an air collecting space 13 is formed, which is also called plenum and which is frontally bounded by a burner cap 70. In the flame tube, a combustion chamber 14 is formed, which is provided for the combustion V of the air-fuel gas mixture.
  • the housing 10 further has a mixing part 15, via which the air-fuel gas mixture for combustion V in the combustion chamber 14 is provided.
  • a combustion apron 16 is formed in the mixing part 15, a combustion apron 16 is formed.
  • the burner 1 further comprises a plate-shaped central cover 20, a baffle plate 30 and a burner top plate 40 which in the mixing part 15 of the housing 10th are arranged. More specifically, the central cover 20 forms for cooling air provided for cooling the burner top plate 40 No input. Arranged laterally or externally in the combustion chamber 14, the burner 1 also has a swirl body or mixing body 80, via which the air-fuel gas mixture for the combustion V is generated.
  • the air plenum 13 (plenum) is fluidly connected to air inlet openings 22 in the central cover 20 via supply elements 21 (such as pipes, for example), wherein control means 21a are provided in the supply line elements, e.g. are provided in the form of air valves, so that the from the air collection chamber 13 through the supply elements 21 flowing through partial air mass flow is controllable.
  • supply elements 21 such as pipes, for example
  • the baffle 30 is arranged parallel to this in the combustion chamber 16 between the central cover 20 and the baffle plate 30 in the form of a septplenums a first compartment 16a of the combustion antechamber 16 is formed.
  • the burner top plate 40 is arranged in the combustion passage 16 parallel to this. Between the baffle plate 30 and the burner top plate 40, a second subspace 16b of the combustion antechamber 16 is formed.
  • the baffle plate 30 is disposed in the combustion vestibule 16 so as to divide the combustion vestibule 16 into the first partial space 16a adjoining the supply elements 21 fluidly connected to the air collecting space 13 and the second partial space 16b adjoining the burner top plate 40.
  • the burner top plate 20 is arranged in the combustion chamber 16 of the housing 10 so as to separate the combustion vestibule 16 from the combustion chamber 14, and forms a central component of the burner 1.
  • the first subspace 16a (Zwischenplenum) is designed so that the cooling air K evenly distributed and the baffle plate (such as a baffle plate) 30 is supplied evenly with cooling air K.
  • the baffle plate 30 has a plurality of passage passages 31, which fluidly connect the first subspace 16a with the second subspace 16b, so that via the feed elements (air supply) 21 from the air collecting space 13 in the first subspace 16a flowing cooling air K via the passage passages 31 in the flow in second subspace 16b and on a second subspace 16b facing the rear surface 40a of the burner top plate 40 can flow.
  • the baffle plate 30 extends parallel to the burner top plate 40, so that the cooling air K, which has flowed into the second subspace 16b, impinges substantially perpendicularly on the rear surface 40a of the burner top plate 40.
  • the second subspace 16b is bounded on the outside by an insertion part 50, wherein a plurality of openings 51 extending perpendicularly to the passage passages 31 are provided in a wall of the insertion part 50.
  • a jacket part 60 is provided on the outside of the insertion part which delimits the mixing part 15 on the outside. The jacket part 60 is in turn inserted into the burner chamber 70 which closes or delimits the air collecting space 13 and is held by the latter.
  • a gap S is provided in the form of an annular gap, via which the second compartment 16b is fluidly connected to the combustion chamber 14, so that rebounding from the rear surface 40a of the burner top plate 40 Cooling air K can flow through the gap in the combustion chamber 14.
  • the second subspace 16b is fluidly connected to the gap S via the openings 51 distributed along a circumference of the gap S, so that cooling air K bouncing off the rear surface 40a of the burner top plate 40 can flow into the gap S via the openings 51.
  • the gap S extends parallel to the through passages 31 and opens into the combustion chamber 14, so that a flow direction of the cooling air K through the gap S is parallel to a flow direction of the cooling air K through the passage passages 31 therethrough.
  • the cooling air K is discharged via the lateral openings 51, which are preferably designed as bores, into the gap S and from there into the combustion chamber 14.
  • the efficiency of the impingement cooling can be varied by the choice of the perforation in the baffle plate 30 and the pressure loss (individual pressure losses of the cooling air path).
  • the driving pressure gradient is essentially predetermined by the pressure loss of a main air mass flow (for the combustion process) through the swirler 80
  • the heat load in the center of the burner top plate or burner plate 40 is highest, wherein in accordance with the invention realized cooling the center of the burner top plate 40 is cooled most efficiently.
  • the proposed cooling fits the impressed hot gas side or combustion chamber side thermal load of the burner top plate 40.
  • the injection of the cooling air K should be as "outsideā€ as possible, away from a mean recirculation flow RS of the burner 1, thus ensuring that a core zone of the recirculation flow RS is not disturbed. Furthermore, it has been recognized according to the invention that it is also important to keep the momentum of the cooling air K as low as possible when entering the combustion chamber 14, thus preventing too great a penetration depth of the cooling air flow into the main flow related to the combustion V and thus the main flow so little is influenced as possible.
  • a diameter D (see Fig.2 ) are chosen as large as possible for the introduction of the cooling air K into the combustion chamber 14 and can preferably result according to the specification D (> 1 / 2d), where d is a diameter of the burner top plate 40.
  • a width of the gap S should be as large as possible and the gap S should be arranged as far as possible radially outward with respect to the burner top plate 40.
  • the width of the gap S defined by the jacket part 60 and the insert part 50 is preferably dimensioned such that a flow velocity of the cooling air K at the exit from the gap S into the combustion chamber 14 is less than a flow velocity of the cooling air when entering the gap S.
  • the inventively realized cooling of the burner top plate 40 is based on an impingement cooling, which cools the burner top plate 40 as a central component of the burner 1 very efficiently.
  • the cooling air K remain the overall process (as a variant also described below external removal of the cooling air K is possible).
  • the design criterion for cooling is the pressure loss via the burner (s) 1 of the gas turbine.
  • valves can be easily implemented to optimize cooling or the amount of cooling air, e.g. the control means 21a.
  • FIGS. 1 and 2 may alternatively or in addition to the gap S and the openings 51 in the burner top plate 40 itself a plurality of through holes may be provided, which fluidly connect the second subspace 16b respectively with the combustion chamber 14.
  • cooling air K which has flowed into the second subspace 16b via the through passages 31 can then be removed from the second subspace 16b into the combustion chamber 14 directly via the burner head plate 40.
  • these passage openings may each have a diameter in a range from 0.3 mm to 1.5 mm, so that the passage openings cause an effusion of the cooling air K, which has flowed into the second subspace 16b via the passage passages 31, through the burner head plate 40 through into the combustion chamber 14 into effect.
  • the burner top plate 40 may be formed by a porous material, so that cooling air K which has flowed into the second subspace 16b can flow out into the combustion chamber 14 via pores of the burner top plate 40.
  • an air discharge passage may be provided in the second subspace 16b via which cooling air K rebounding from the rear surface 40a of the burner top plate 40 is fed away from the burner head plate 40 remote from the combustion process in the combustion chamber 14.
  • an external cooling wherein the removal of the cooling air K as described above in connection with the other embodiments of the invention or at another location between e.g. a compressor outlet and the air collection chamber 13 takes place.
  • the cooling air K is not injected directly into the combustion chamber 14, but derived.
  • the cooling air K is thus not immediately after the swirl body 80, but at a following position -stromab in the flow direction of the hot gas combustion V considered- initiated. Possible positions for the introduction of the cooling air K are in the range of a secondary zone of the combustion chamber 14 up to an exhaust stack of the gas turbine.
  • the advantage of these solutions is that an influence of the main flow and thus the combustion V is excluded by the cooling air flow.
  • the usable pressure gradient of the cooling increases and thus a greater temperature reduction can be achieved.
  • the disadvantage of the solution is that the cooling air K can only partially or not at all be used for the gas turbine process.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Description

Die Erfindung betrifft einen Brenner fĆ¼r eine Turbine und eine mit einem solchen Brenner ausgerĆ¼stete Gasturbine.The invention relates to a burner for a turbine and a gas turbine equipped with such a burner.

Es sind verschiedene Brenner zur atmosphƤrischen Verbrennung und zur Verbrennung unter Druck bekannt. Auch auf dem Gebiet der Gasturbinen werden verschiedene solche Brenner eingesetzt.Various burners for atmospheric combustion and combustion under pressure are known. Also in the field of gas turbines, various such burners are used.

Beispiele fĆ¼r Brenner von Gasturbinen sind in DE 10 2006 048 842 A1 , DE 195 42 521 A1 , DE 43 28 294 A1 , DE 195 49 143 A1 , WO 96/04510 und in der Zeitschrift " ABB Technik" aus 4/1998 auf den Seiten 4 bis 16 beschrieben.Examples of burners of gas turbines are in DE 10 2006 048 842 A1 . DE 195 42 521 A1 . DE 43 28 294 A1 . DE 195 49 143 A1 . WO 96/04510 and in the magazine " ABB Technik "from 4/1998 on pages 4 to 16 described.

Dokument EP 1 434 007 A2 offenbart einen Brenner gemƤƟ dem Oberbegriff des Anspruchs 1.document EP 1 434 007 A2 discloses a burner according to the preamble of claim 1.

Ein Hauptziel besteht bei solchen Brennern darin, die Verbrennung in einem groƟen Betriebsbereich stabil, kontrolliert, schadstoffarm und mƶglichst vollstƤndig ablaufen zu lassen. Bei bestimmten Brennern werden zur Stabilisierung der Verbrennungszone (Zone der WƤrmefreisetzung) spezielle Bauteile als "Flammenhalter" eingesetzt. Andere Brenner sind so ausgelegt, dass die Stabilisierung im wandnahen Bereich - z.B. im Zentrum des Brenners - erfolgt. Diese Bauteile sind thermisch hoch belastet, besitzen eine geringe Lebensdauer und mĆ¼ssen deshalb oft ausgetauscht werden.A major objective with such burners is to make combustion in a large operating range stable, controlled, low in emissions and as complete as possible. In certain burners, special components are used as "flame holders" to stabilize the combustion zone (zone of heat release). Other burners are designed to provide stabilization near the wall - e.g. in the center of the burner - takes place. These components are thermally highly loaded, have a short life and must therefore be replaced often.

Um die StabilitƤt der Verbrennung nicht zu beeintrƤchtigen bzw. dem Prozess keine KĆ¼hlluft zu entziehen, werden diese Bauteile gemƤƟ dem Stand der Technik nicht gekĆ¼hlt. Damit sind die Inspektions- und Wartungsintervalle fĆ¼r diese Bauteile entsprechend kurz, was zusammen mit den Stillstandszeiten der jeweiligen Anlage zu zusƤtzlichen, hohen Kosten fĆ¼hrt.In order not to impair the stability of the combustion or to remove the process no cooling air, these components are not cooled according to the prior art. Thus, the inspection and maintenance intervals for these components are correspondingly short, which together with the downtime of the respective system leads to additional, high costs.

Der Erfindung liegt die Aufgabe zugrunde, einen Brenner fĆ¼r eine Turbine, insbesondere fĆ¼r eine Gasturbine, bereitzustellen, bei dem das zentrale Bauteil bzw. der Flammenhalter effektiv gekĆ¼hlt werden kann ohne den \/erbrennungsprozess im Brenner zu stƶren. Der Erfindung liegt ferner die Aufgabe zugrunde, eine mit einem solchen Brenner ausgerĆ¼stete Gasturbine bereitzustellen.The invention has for its object to provide a burner for a turbine, in particular for a gas turbine, in which the central component or the flame holder can be effectively cooled without disturbing the / / combustion process in the burner. The invention is further based on the object to provide a equipped with such a burner gas turbine.

Die o.g. Aufgaben werden mit einem Brenner gemƤƟ Anspruch 1 bzw. einer Gasturbine gemƤƟ Anspruch 11 gelƶst. Weiterbildungen der Erfindung sind in den abhƤngigen AnsprĆ¼chen definiert.The o.g. Problems are solved with a burner according to claim 1 or a gas turbine according to claim 11. Further developments of the invention are defined in the dependent claims.

ErfindungsgemƤƟ wird ein Brenner fĆ¼r eine Turbine, insbesondere eine Gasturbine, bereitgestellt, wobei der Brenner aufweist: ein GehƤuse, in dem ein Luftsammelraum, ein Verbrennungsvorraum und ein Brennraum ausgebildet sind, eine Brenner-Kopfplatte, die in dem GehƤuse angeordnet ist, so dass die Brenner-Kopfplatte den Verbrennungsvorraum von dem Brennraum trennt, eine Prallplatte, die in dem Verbrennungsvorraum angeordnet ist, so dass die Prallplatte den Verbrennungsvorraum in einen an eine mit dem Luftsammelraum fluidverbundene LuftzufĆ¼hrung angrenzenden ersten Teilraum und einen an die Brenner-Kopfplatte angrenzenden zweiten Teilraum unterteilt, wobei die Prallplatte eine Mehrzahl von Durchgangspassagen aufweist, die den ersten Teilraum mit dem zweiten Teilraum fluidverbinden, so dass Ć¼ber die LuftzufĆ¼hrung aus dem Luftsammelraum in den ersten Teilraum eingestrƶmte Luft Ć¼ber die Durchgangspassagen in den zweiten Teilraum einstrƶmen und auf eine dem zweiten Teilraum zugewandte RĆ¼ckflƤche der Brenner-Kopfplatte strƶmen kann.According to the invention, a burner for a turbine, in particular a gas turbine, is provided, wherein the burner comprises: a housing in which an air collecting space, a combustion antechamber and a combustion chamber are formed, a burner top plate, which is arranged in the housing, so that the Burner head plate separates the combustion antechamber from the combustion chamber, a baffle plate which is arranged in the combustion antechamber so that the baffle plate divides the combustion pre-vent into a first subspace adjacent to an air feed fluidly connected to the air collection space and a second subspace adjacent to the burner head plate, wherein the baffle plate has a plurality of passage passages, which fluidly connect the first subspace with the second subspace, so that via the air supply from the air collecting space in the first subspace inflowing air flow through the passage passages in the second subspace and zugewan zu zu the second subspace The back surface of the burner top plate can flow.

Mit der erfindungsgemƤƟen Lƶsung kann, da die RĆ¼ckflƤche der Brenner-Kopfplatte mit kĆ¼hlender Luft beaufschlagt wird, so dass eine fĆ¼r die Brenner-Kopfplatte effiziente PrallkĆ¼hlung erreicht wird, die Brenner-Kopfplatte effektiv gekĆ¼hlt und damit deren thermischer VerschleiƟ reduziert werden. Die erfindungsgemƤƟ vorgeschlagene KĆ¼hlung erhƶht somit die Lebensdauer der Brenner-Kopfplatte deutlich. Da lediglich die RĆ¼ckseite der Brenner-Kopfplatte mit der kĆ¼hlenden Luft beaufschlagt wird, wobei die Luft bevorzugt an einem ƤuƟeren Rand der Brenner-Kopfplatte dem Verbrennungsraum zugefĆ¼hrt wird, Ć¼bt die Luft bzw. KĆ¼hlung keinen stƶrenden Einfluss auf den Verbrennungsprozess im Brenner aus.With the solution according to the invention, since cooling air is applied to the rear surface of the burner top plate so that efficient impingement cooling for the burner top plate is achieved, the burner top plate can be effectively achieved cooled and thus their thermal wear can be reduced. The inventively proposed cooling thus significantly increases the life of the burner top plate. Since only the back of the burner top plate is charged with the cooling air, wherein the air is preferably supplied to an outer edge of the burner top plate to the combustion chamber, the air or cooling exerts no disturbing effect on the combustion process in the burner.

ErfindungsgemƤƟ erstreckt sich die Prallplatte parallel zu der Brenner-Kopfplatte, so dass in den zweiten Teilraum eingestrƶmte Luft senkrecht auf die RĆ¼ckflƤche der Brenner-Kopfplatte auftrifft.According to the invention, the baffle plate extends parallel to the burner top plate, so that air which has flowed into the second partial space impinges perpendicularly on the rear surface of the burner top plate.

ErfindungsgemƤƟ ist auƟenumfƤnglich der Brenner-Kopfplatte ein Spalt vorgesehen, Ć¼ber den der zweite Teilraum mit dem Brennraum fluidverbunden ist, so dass von der RĆ¼ckflƤche der Brenner-Kopfplatte abprallende Luft Ć¼ber den Spalt in den Brennraum abstrƶmen kann.According to the invention, a gap is provided on the outer circumference of the burner head plate, via which the second subspace is fluidly connected to the combustion chamber, so that air rebounding from the rear face of the burner head plate can flow out into the combustion chamber via the gap.

Durch den Spalt kann somit die kĆ¼hlende Luft auƟen am Rand der Brenner-Kopfplatte und demnach den Verbrennungsprozess nicht stƶrend in den Brennraum eingeleitet werden, wodurch die Luft dem Gesamtprozess (Brenner, Turbine) erhalten bleibt.The cooling air can therefore not be introduced into the combustion chamber outside the edge of the burner top plate and thus the combustion process by the gap, as a result of which the air is retained in the overall process (burner, turbine).

GemƤƟ der Erfindung sollte die EindĆ¼sung der kĆ¼hlenden Luft mƶglichst "auƟen", fern einer mittleren Rezirkulationsstrƶmung des Brenners erfolgen, womit sichergestellt wird, dass eine Kernzone der Rezirkulationsstrƶmung nicht gestƶrt wird.According to the invention, the injection of the cooling air should be as far as possible "outside", far away a mean recirculation flow of the burner, which ensures that a core zone of the recirculation flow is not disturbed.

GemƤƟ noch einer weiteren AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners ist der zweite Teilraum auƟenumfƤnglich von einem Einsetzteil begrenzt, wobei in einer Wandung des Einsetzteils eine sich senkrecht zu den Durchgangspassagen erstreckende Ɩffnung vorgesehen ist, die den zweiten Teilraum mit dem Spalt fluidverbindet, so dass von der RĆ¼ckflƤche der Brenner-Kopfplatte abprallende Luft Ć¼ber die Ɩffnung in den Spalt abstrƶmen kann.According to yet another embodiment of the burner according to the invention, the second subspace is bounded on the outside by an insertion part, wherein in a wall of the insert part is provided which extends perpendicular to the passages opening which fluidly connects the second subspace with the gap, so that bouncing from the rear surface of the burner head plate rebounding air can flow through the opening into the gap.

Ober diese Ɩffnung kann einerseits die kĆ¼hlende Luft bedarfsgerecht quer zum ƤuƟeren Rand der Brenner-Kopfplatte bzw. des Brennraums hin geleitet werden, so dass deren Einfluss auf die Verbrennung minimiert wird, und kann andererseits der Luftstrom durch deren Durchmesser gezielt beeinflusst werden.On the one hand, the cooling air can be routed across this opening, as required, transversely to the outer edge of the burner top plate or the combustion chamber, so that its influence on the combustion is minimized, and on the other hand, the air flow can be specifically influenced by its diameter.

GemƤƟ noch einer AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners ist der Spalt als Ringspalt ausgebildet, wobei in der Wandung des Einsetzteils eine Mehrzahl von sich senkrecht zu den Durchgangspassagen erstreckenden entlang eines Umfangs des Spalts verteilten Ɩffnungen vorgesehen sind, die den zweiten Teilraum jeweils mit dem Spalt fluidverbinden, so dass von der RĆ¼ckflƤche der Brenner-Kopfpfatte abprallende Luft Ć¼ber die Ɩffnungen in den Spalt abstrƶmen kann.According to yet another embodiment of the burner according to the invention, the gap is formed as an annular gap, wherein in the wall of the insert part a plurality of perpendicular to the passages extending along a circumference of the gap distributed openings are provided, which fluidly connect the second subspace with the gap, so that rebounding air from the rear surface of the burner head can flow out into the gap via the openings.

Durch die Ausbildung des Spalts als Ringspalt und durch das Vorsehen der dazu umfƤnglich verteilten Mehrzahl von Ɩffnungen kann die Luft nach dem KĆ¼hlen der Brenner-Kopfplatte ƤuƟerst gleichmƤƟig in den Brennraum verteilt werden, so dass deren Einfluss auf die Verbrennung weiter minimiert wird.By forming the gap as an annular gap and by providing the circumferentially distributed plurality of openings, the air after cooling the burner top plate can be extremely evenly distributed in the combustion chamber, so that their influence on the combustion is further minimized.

GemƤƟ einer weiteren AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners erstreckt sich der Spalt parallel zu den Durchgangspassagen, so dass eine Strƶmungsrichtung der Luft durch den Spalt hindurch parallel zu einer Strƶmungsrichtung der Luft durch die Durchgangspassagen hindurch ist.According to a further embodiment of the burner according to the invention, the gap extends parallel to the passage passages, so that a flow direction of the air through the gap is parallel to a flow direction of the air through the passage passages.

ErfindugsgemƤƟ ist eine Weite des Spalts so bemessen, dass eine Strƶmungsgeschwindigkeit der Luft beim Austritt aus dem Spalt geringer als eine Strƶmungsgeschwindigkeit der Luft beim Eintritt in den Spalt ist.According to the invention, a width of the gap is dimensioned such that a flow velocity of the Air at the exit from the gap is less than a flow velocity of the air entering the gap.

Mit anderen Worten ist die Weite des Spalts mƶglichst so groƟ zu wƤhlen, dass die Strƶmungsgeschwindigkeit der Luft und damit deren Eindringtiefe in eine Hauptstrƶmung der Verbrennung minimiert werden, was wiederum sicher stellt, dass die Hauptstrƶmung so wenig wie mƶglich beeinflusst wird.In other words, the width of the gap should be as large as possible to minimize the flow velocity of the air and thus its penetration into a main flow of combustion, which in turn ensures that the main flow is influenced as little as possible.

GemƤƟ einer AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners sind in der Brenner-Kopfplatte eine Mehrzahl von Durchgangsƶffnungen vorgesehen, die den zweiten Teilraum jeweils mit dem Brennraum fluidverbinden.According to one embodiment of the burner according to the invention, a plurality of passage openings are provided in the burner head plate, which fluidly connect the second subspace to the combustion chamber.

Dies stellt eine weitere Mƶglichkeit dar, den Luftstrom mƶglichst ohne Beeinflussung der Verbrennung bevorzugt am ƤuƟeren Rand der Brenner-Kopfplatte bzw. des Brennraums und unter Weiternutzung des Luftstroms fĆ¼r den Gesamtprozess nach erfolgter KĆ¼hlung abzufĆ¼hren.This represents a further possibility to dissipate the air flow preferably without influencing the combustion, preferably at the outer edge of the burner top plate or the combustion chamber and, with continued use of the air flow for the entire process after cooling.

GemƤƟ einer weiteren AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners weisen die Durchgangsƶffnungen jeweils einen Durchmesser in einem Bereich von 0,3 mm bis 1,5 mm auf, so dass die Durchgangsƶffnungen eine Effusion der Ć¼ber die Durchgangspassagen in den zweiten Teilraum eingestrƶmten Luft durch die Brenner-Kopfplatte hindurch in den Brennraum hinein bewirken.According to a further embodiment of the burner according to the invention, the through-openings each have a diameter in a range from 0.3 mm to 1.5 mm, so that the through-holes an effusion of the air flowed through the passage passages in the second sub-chamber through the burner head plate into the combustion chamber.

Diese Ausgestaltung der Erfindung unterstĆ¼tzt in vorteilhafter Weise sowohl die KĆ¼hleffizienz als auch die Beeinflussungsfreiheit des kĆ¼hlenden Luftstroms.This embodiment of the invention advantageously supports both the cooling efficiency and the freedom from influencing the cooling air flow.

GemƤƟ noch einer AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners ist die Brenner-Kopfplatte von einem porƶsen Material gebildet, so dass in den zweiten Teilraum eingestrƶmte Luft Ć¼ber Poren der Brenner-Kopfplatte in den Brennraum hinein abstrƶmen kann.According to yet another embodiment of the burner according to the invention, the burner top plate is formed by a porous material, so that in the second Subspace inflowed air can flow through pores of the burner head plate into the combustion chamber.

Auch diese Ausgestaltung der Erfindung stellt eine vorteilhafte Mƶglichkeit dar, den kĆ¼hlenden Luftstrom mƶglichst ohne Beeinflussung der Verbrennung und unter Weiternutzung des Luftstroms fĆ¼r den Gesarntprozess nach erfolgter KĆ¼hlung abzufĆ¼hren.This embodiment of the invention is an advantageous way to dissipate the cooling air flow as possible without affecting the combustion and continued use of the air flow for Gesarntprozess after cooling.

GemƤƟ einer weiteren AusfĆ¼hrungsform des erfindungsgemƤƟen Brenners ist in dem zweiten Teilraum eine LuftabfĆ¼hrpassage vorgesehen, Ć¼ber die von der RĆ¼ckflƤche der Brenner-Kopfplatte abprallende Luft in Bezug auf einen Verbrennungsprozess im Brennraum strƶmungsabwƤrts der Brenner-Kopfplatte in den Brennraum eingespeist werden kann.According to a further embodiment of the burner according to the invention, an air discharge passage is provided in the second subspace, via which air rebounding from the rear face of the burner head plate can be fed into the combustion chamber downstream of the burner head plate with respect to a combustion process in the combustion chamber.

Mit anderen Worten wird hier eine externe KĆ¼hlung eingesetzt, wobei die Entnahme der kĆ¼hlenden Luft wie in Verbindung mit den anderen AusfĆ¼hrungsformen der Erfindung beschrieben oder an einem anderen Ort zwischen z.B. einem Verdichteraustritt und dem Luftsammelraum erfolgt. Nach erfolgter KĆ¼hlung wird die Luft nicht direkt in den Brennraum eingedĆ¼st, sondern abgeleitet. Die Luft wird also nicht unmittelbar nach dem Drallkƶrper, sondern an einer folgenden Position -stromab in Strƶmungsrichtung des HeiƟgases der Verbrennung betrachtet- eingeleitet. Mƶgliche Positionen fĆ¼r die Einleitung der Luft liegen im Bereich einer SekundƤrzone des Brennraums bis hin zu einem Abgaskamin der Gasturbine.In other words, external cooling is used here, the removal of the cooling air being described in connection with the other embodiments of the invention or at another location between e.g. a compressor outlet and the air collection chamber takes place. After cooling, the air is not injected directly into the combustion chamber, but derived. Thus, the air is not introduced immediately after the swirler but at a following position downstream from the direction of flow of the hot gas of combustion. Possible positions for the introduction of the air are in the range of a secondary zone of the combustion chamber up to an exhaust stack of the gas turbine.

Der Vorteil dieser Lƶsungen besteht darin, dass eine Beeinflussung der Hauptstrƶmung und damit der Verbrennung durch den kĆ¼hlenden Luftstrom ausgeschlossen wird. ZusƤtzlich steigt das nutzbare DruckgefƤlle der KĆ¼hlung und damit kann eine grĆ¶ĆŸere Temperaturabsenkung erreicht werden. Der Nachteil der Lƶsung besteht darin, dass die Luft nur noch teilweise oder gar nicht mehr fĆ¼r den Gasturbinen-Prozess genutzt werden kann.The advantage of these solutions is that an influence of the main flow and thus the combustion is excluded by the cooling air flow. In addition, the usable pressure gradient of the cooling increases and thus a greater temperature reduction can be achieved. The disadvantage of the solution is that the air can only partially or not at all be used for the gas turbine process.

GemƤƟ einem zweiten Aspekt der Erfindung wird eine Gasturbine mit einem Brenner gemƤƟ einer, mehreren oder allen zuvor beschriebenen AusfĆ¼hrungsformen der Erfindung in jeder denkbaren Kombination bereitgestellt.According to a second aspect of the invention, a gas turbine with a burner according to one, several or all of the previously described embodiments of the invention is provided in any conceivable combination.

Im Folgenden wird die Erfindung anhand bevorzugter AusfĆ¼hrungsformen und unter Bezugnahme auf die beigefĆ¼gten Figuren detaillierter beschrieben.

Fig.1
zeigt den Ć¼blichen Aufbau eines Brenners fĆ¼r eine Turbine wie eine Gasturbine.
Fig.2
zeigt in vergrĆ¶ĆŸerter Ansicht einen Bereich X aus Fig. 1, wobei der Brenner mit einer erfindungsgemƤƟen internen KĆ¼hlung fĆ¼r die Brenner-Kopfplatte ausgerĆ¼stet ist.
In the following the invention will be described in more detail by means of preferred embodiments and with reference to the attached figures.
Fig.1
shows the usual construction of a burner for a turbine such as a gas turbine.
Fig.2
shows an area X in an enlarged view Fig. 1 wherein the burner is equipped with an internal cooling according to the invention for the burner top plate.

Wie in Fig.1 und Fig.2 gezeigt, weist ein Brenner 1 einer Gasturbine (nicht vollstƤndig gezeigt) gemƤƟ einer AusfĆ¼hrungsform der Erfindung ein GehƤuse 10 auf, welches seinerseits ein Flammrohr 11, in dem die Verbrennung V eines Luft-Brenngas-Gemisches stattfindet, und einen Mantel 12 aufweist, welcher das Flammrohr 11 umgibt. Zwischen dem Flammrohr 11 und dem Mantel 12 ist ein Luftsammelraum 13 ausgebildet, welcher auch Plenum genannt wird und welcher stirnseitig von einem Brennerdeckel 70 begrenzt wird. In dem Flammrohr ist ein Brennraum 14 ausgebildet, welcher fĆ¼r die Verbrennung V des Luft-Brenngas-Gemisches vorgesehen ist.As in Fig.1 and Fig.2 1, a burner 1 of a gas turbine (not completely shown) according to an embodiment of the invention comprises a housing 10, which in turn comprises a flame tube 11, in which the combustion V of an air-fuel gas mixture takes place, and a jacket 12, which Flame tube 11 surrounds. Between the flame tube 11 and the shell 12, an air collecting space 13 is formed, which is also called plenum and which is frontally bounded by a burner cap 70. In the flame tube, a combustion chamber 14 is formed, which is provided for the combustion V of the air-fuel gas mixture.

Das GehƤuse 10 weist ferner einen Mischteil 15 auf, Ć¼ber welchen das Luft-Brenngas-Gemisch zur Verbrennung V im Brennraum 14 bereitgestellt wird. In dem Mischteil 15 ist ein Verbrennungsvorraum 16 ausgebildet.The housing 10 further has a mixing part 15, via which the air-fuel gas mixture for combustion V in the combustion chamber 14 is provided. In the mixing part 15, a combustion apron 16 is formed.

Der Brenner 1 weist ferner einen plattenfƶrmigen Zentraldeckel 20, eine Prallplatte 30 und eine Brenner-Kopfplatte 40 auf, die in dem Mischteil 15 des GehƤuses 10 angeordnet sind. Genauer gesagt bildet der Zentraldeckel 20 fĆ¼r zur KĆ¼hlung der Brenner-Kopfplatte 40 vorgesehene KĆ¼hlluft Keinen Eingang. Seitlich bzw, auƟenumfƤnglich in dem Brennraum 14 angeordnet weist der Brenner 1 ferner einen Drallkƶrper bzw. Mischkƶrper 80 auf, Ć¼ber den das Luft-Brenngas-Gemisch fĆ¼r die Verbrennung V erzeugt wird.The burner 1 further comprises a plate-shaped central cover 20, a baffle plate 30 and a burner top plate 40 which in the mixing part 15 of the housing 10th are arranged. More specifically, the central cover 20 forms for cooling air provided for cooling the burner top plate 40 No input. Arranged laterally or externally in the combustion chamber 14, the burner 1 also has a swirl body or mixing body 80, via which the air-fuel gas mixture for the combustion V is generated.

Zu diesem Zweck ist der Luftsammelraum 13 (Plenum) Ć¼ber Zuleitungselemente 21 (wie hier z.B. Rohre) mit Lufteinlassƶffnungen 22 im Zentraldeckel 20 fluidverbunden, wobei in den Zuleitungselementen Steuermittel 21a z.B. in Form von Luftventilen vorgesehen sind, so dass der aus dem Luftsammelraum 13 durch die Zuleitungselemente 21 hindurch strƶmende Teilluftmassenstrom steuerbar ist.For this purpose, the air plenum 13 (plenum) is fluidly connected to air inlet openings 22 in the central cover 20 via supply elements 21 (such as pipes, for example), wherein control means 21a are provided in the supply line elements, e.g. are provided in the form of air valves, so that the from the air collection chamber 13 through the supply elements 21 flowing through partial air mass flow is controllable.

In einer Strƶmungsrichtung der KĆ¼hlluft K strƶmungsabwƤrts des Zentraldeckels 20 ist parallel zu diesem die Prallplatte 30 im Verbrennungsvorraum 16 angeordnet Zwischen dem Zentraldeckel 20 und der Prallplatte 30 ist in Form eines Zwischenplenums ein erster Teilraum 16a des Verbrennungsvorraums 16 ausgebildet.In a flow direction of the cooling air K downstream of the central cover 20, the baffle 30 is arranged parallel to this in the combustion chamber 16 between the central cover 20 and the baffle plate 30 in the form of a Zwischenplenums a first compartment 16a of the combustion antechamber 16 is formed.

In einer Strƶmungsrichtung der KĆ¼hlluft K strƶmungsabwƤrts der Prallplatte 30 ist parallel zu dieser die Brenner-Kopfplatte 40 im Verbrennungsvorraum 16 angeordnet. Zwischen der Prallplatte 30 und der Brenner-Kopfplatte 40 ist ein zweiter Teilraum 16b des Verbrennungsvorraums 16 ausgebildet.In a flow direction of the cooling air K downstream of the baffle plate 30, the burner top plate 40 is arranged in the combustion passage 16 parallel to this. Between the baffle plate 30 and the burner top plate 40, a second subspace 16b of the combustion antechamber 16 is formed.

Mit anderen Worten ist die Prallplatte 30 so in dem Verbrennungsvorraum 16 angeordnet, dass sie den Verbrennungsvorraum 16 in den an die mit dem Luftsammelraum 13 fluidverbundenen Zuleitungselemente 21 angrenzenden ersten Teilraum 16a und den an die Brenner-Kopfplatte 40 angrenzenden zweiten Teilraum 16b unterteilt.In other words, the baffle plate 30 is disposed in the combustion vestibule 16 so as to divide the combustion vestibule 16 into the first partial space 16a adjoining the supply elements 21 fluidly connected to the air collecting space 13 and the second partial space 16b adjoining the burner top plate 40.

Die Brenner-Kopfplatte 20 ist in dem Verbrennungsorraum 16 des GehƤuses 10 so angeordnet, dass sie den Verbrennungsvorraum 16 von dem Brennraum 14 trennt, und bildet ein zentrales Bauteil des Brenners 1.The burner top plate 20 is arranged in the combustion chamber 16 of the housing 10 so as to separate the combustion vestibule 16 from the combustion chamber 14, and forms a central component of the burner 1.

Eine symmetrische Entnahme des Teilluftmassenstroms aus dem Luftsammelraum 13, wie z.B. mittels mehreren Zuleitungselementen 21, gewƤhrleistet sowohl eine homogenen Entnahme als auch eine homogene Zustrƶmung der KĆ¼hlluft K in den ersten Teilraum 16a. Der erste Teilraum 16a (Zwischenplenum) ist dabei so gestaltet, dass sich die KĆ¼hlluft K gleichmƤƟig verteilt und die Prallplatte (wie z.B. ein Prallblech) 30 gleichmƤƟig mit KĆ¼hlluft K versorgt wird.A symmetrical removal of the partial air mass flow from the air collection chamber 13, as e.g. by means of several supply elements 21, ensures both a homogeneous removal and a homogeneous inflow of the cooling air K in the first subspace 16 a. The first subspace 16a (Zwischenplenum) is designed so that the cooling air K evenly distributed and the baffle plate (such as a baffle plate) 30 is supplied evenly with cooling air K.

Die Prallplatte 30 weist eine Mehrzahl von Durchgangspassagen 31 auf, die den ersten Teilraum 16a mit dem zweiten Teilraum 16b fluidverbinden, so dass Ć¼ber die Zuleitungselemente (LuftzufĆ¼hrung) 21 aus dem Luftsammelraum 13 in den ersten Teilraum 16a eingestrƶmte KĆ¼hlluft K Ć¼ber die Durchgangspassagen 31 in den zweiten Teilraum 16b einstrƶmen und auf eine dem zweiten Teilraum 16b zugewandte RĆ¼ckflƤche 40a der Brenner-Kopfplatte 40 strƶmen kann.The baffle plate 30 has a plurality of passage passages 31, which fluidly connect the first subspace 16a with the second subspace 16b, so that via the feed elements (air supply) 21 from the air collecting space 13 in the first subspace 16a flowing cooling air K via the passage passages 31 in the flow in second subspace 16b and on a second subspace 16b facing the rear surface 40a of the burner top plate 40 can flow.

Die Prallplatte 30 erstreckt sich parallel zu der Brenner-Kopfplatte 40, so dass die in den zweiten Teilraum 16b eingestrƶmte KĆ¼hlluft K im Wesentlichen senkrecht auf die RĆ¼ckflƤche 40a der Brenner-Kopfplatte 40 auftrifft.The baffle plate 30 extends parallel to the burner top plate 40, so that the cooling air K, which has flowed into the second subspace 16b, impinges substantially perpendicularly on the rear surface 40a of the burner top plate 40.

Der zweite Teilraum 16b ist auƟenumfƤnglich von einem Einsetzteil 50 begrenzt, wobei in einer Wandung des Einsetzteils 50 eine Mehrzahl von sich senkrecht zu den Durchgangspassagen 31 erstreckenden Ɩffnungen 51 vorgesehen sind, AuƟenumfƤnglich des Einsetzteils ist ein Mantelteil 60 vorgesehen, welches den Mischteil 15 auƟenumfƤnglich begrenzt. Das Mantelteil 60 ist wiederum in den den Luftsammelraum 13 verschlieƟenden bzw. begrenzenden Brennerdeckel 70 des Brenners 1 eingesetzt und wird von diesem gehalten.The second subspace 16b is bounded on the outside by an insertion part 50, wherein a plurality of openings 51 extending perpendicularly to the passage passages 31 are provided in a wall of the insertion part 50. A jacket part 60 is provided on the outside of the insertion part which delimits the mixing part 15 on the outside. The jacket part 60 is in turn inserted into the burner chamber 70 which closes or delimits the air collecting space 13 and is held by the latter.

Zwischen dem Einsetzteil 50 und dem Mantelteil 60 sowie auƟenumfƤnglich der Brenner-Kopfplatte 40 ist ein Spalt S in Form eines Ringspalts vorgesehen, Ć¼ber den der zweite Teilraum 16b mit dem Brennraum 14 fluidverbunden ist, so dass von der RĆ¼ckflƤche 40a der Brenner-Kopfplatte 40 abprallende KĆ¼hlluft K Ć¼ber den Spalt in den Brennraum 14 abstrƶmen kann.Between the insertion part 50 and the shell part 60 and the outer circumference of the burner top plate 40, a gap S is provided in the form of an annular gap, via which the second compartment 16b is fluidly connected to the combustion chamber 14, so that rebounding from the rear surface 40a of the burner top plate 40 Cooling air K can flow through the gap in the combustion chamber 14.

Genauer gesagt ist der zweite Teilraum 16b Ć¼ber die entlang eines Umfangs des Spalts S verteilten Ɩffnungen 51 mit dem Spalt S fluidverbunden, so dass von der RĆ¼ckflƤche 40a der Brenner-Kopfplatte 40 abprallende KĆ¼hlluft K Ć¼ber die Ɩffnungen 51 in den Spalt S abstrƶmen kann.More specifically, the second subspace 16b is fluidly connected to the gap S via the openings 51 distributed along a circumference of the gap S, so that cooling air K bouncing off the rear surface 40a of the burner top plate 40 can flow into the gap S via the openings 51.

Der Spalt S erstreckt sich parallel zu den Durchgangspassagen 31 und mĆ¼ndet in den Brennraum 14, so dass eine Strƶmungsrichtung der KĆ¼hlluft K durch den Spalt S hindurch parallel zu einer Strƶmungsrichtung der KĆ¼hlluft K durch die Durchgangspassagen 31 hindurch ist.The gap S extends parallel to the through passages 31 and opens into the combustion chamber 14, so that a flow direction of the cooling air K through the gap S is parallel to a flow direction of the cooling air K through the passage passages 31 therethrough.

Im Fazit wird, nachdem die Ć¼ber die Durchgangspassagen 31 erzeugten KĆ¼hlluftjets der Flammhalteplatte 40 WƤrme entzogen haben, die KĆ¼hlluft K Ć¼ber die seitlichen Ɩffnungen 51, welche vorzugsweise als Bohrungen ausgefĆ¼hrt sind, in den Spalt S und von dort in den Brennraum 14 abgefĆ¼hrt.In conclusion, after the cooling air jets of the flame holding plate 40 generated via the through passages 31 have extracted heat, the cooling air K is discharged via the lateral openings 51, which are preferably designed as bores, into the gap S and from there into the combustion chamber 14.

Die Effizienz der PrallkĆ¼hlung lƤsst sich durch die Wahl der Belochung in der Prallplatte 30 und des Druckverlustes (Einzeldruckverluste der KĆ¼hlluftstrecke) variieren. Das treibende DruckgefƤlle wird im Wesentlichen durch den Druckverlust eines Hauptluftmassenstromes (fĆ¼r den Verbrennungsprozess) durch den Drallkƶrper 80 hindurch vorgegebenThe efficiency of the impingement cooling can be varied by the choice of the perforation in the baffle plate 30 and the pressure loss (individual pressure losses of the cooling air path). The driving pressure gradient is essentially predetermined by the pressure loss of a main air mass flow (for the combustion process) through the swirler 80

Wie schon eingangs erwƤhnt, ist die WƤrmebelastung im Zentrum der Brenner-Kopfplatte bzw. Brennerplatte 40 am hƶchsten, wobei bei der erfindungsgemƤƟ realisierten KĆ¼hlung das Zentrum der Brenner-Kopfplatte 40 am effizientesten gekĆ¼hlt wird. Mit zunehmendem Durchmesser steigt ein Querstrom an und die Effizienz der KĆ¼hlung verringert sich. Insofern passt die vorgeschlagene KĆ¼hlung zu der aufgeprƤgten heiƟgasseitigen bzw. brennraumseitigen thermischen Belastung der Brenner-Kopfplatte 40.As already mentioned, the heat load in the center of the burner top plate or burner plate 40 is highest, wherein in accordance with the invention realized cooling the center of the burner top plate 40 is cooled most efficiently. As the diameter increases, cross-flow increases and cooling efficiency decreases. In this respect, the proposed cooling fits the impressed hot gas side or combustion chamber side thermal load of the burner top plate 40.

ErfindungsgemƤƟ wurde erkannt, dass die EindĆ¼sung der KĆ¼hlluft K mƶglichst "auƟen", fern einer mittleren Rezirkulationsstrƶmung RS des Brenners 1 erfolgen sollte, womit sichergestellt wird, dass eine Kemzone der Rezirkulationsstrƶmung RS nicht gestƶrt wird. Ferner wurde erfindungsgemƤƟ erkannt, dass es ebenfalls wichtig ist, den Impuls der KĆ¼hlluft K beim Eintritt in den Brennraum 14 mƶglichst gering zu halten, womit eine zu groƟe Eindringtiefe des KĆ¼hlluftstromes in die auf die Verbrennung V bezogene Hauptstrƶmung verhindert wird und damit die Hauptstrƶmung so wenig wie mƶglich beeinflusst wird.According to the invention, it has been recognized that the injection of the cooling air K should be as "outside" as possible, away from a mean recirculation flow RS of the burner 1, thus ensuring that a core zone of the recirculation flow RS is not disturbed. Furthermore, it has been recognized according to the invention that it is also important to keep the momentum of the cooling air K as low as possible when entering the combustion chamber 14, thus preventing too great a penetration depth of the cooling air flow into the main flow related to the combustion V and thus the main flow so little is influenced as possible.

Um diesen Erfordernissen zu genĆ¼gen, sollte ein Durchmesser D (siehe Fig.2) fĆ¼r die Einleitung der KĆ¼hlluft K in den Brennraum 14 mƶglichst groƟ gewƤhlt werden und kann sich bevorzugt nach der Vorschrift D (>1/2d) ergeben, wobei d ein Durchmesser der Brenner-Kopfplatte 40 ist. Mit anderen Worten sollte eine Weite des Spalts S mƶglichst groƟ bemessen sein und sollte der Spalt S mƶglichst weit radial auƟen in Bezug auf die Brenner-Kopfplatte 40 angeordnet sein. Die durch das Mantelteil 60 und das Einsetzteil 50 definierte Weite des Spalts S ist dabei bevorzugt so bemessen, dass eine Strƶmungsgeschwindigkeit der KĆ¼hlluft K beim Austritt aus dem Spalt S in den Brennraum 14 hinein geringer als eine Strƶmungsgeschwindigkeit der KĆ¼hlluft beim Eintritt in den Spalt S ist.To meet these requirements, a diameter D (see Fig.2 ) are chosen as large as possible for the introduction of the cooling air K into the combustion chamber 14 and can preferably result according to the specification D (> 1 / 2d), where d is a diameter of the burner top plate 40. In other words, a width of the gap S should be as large as possible and the gap S should be arranged as far as possible radially outward with respect to the burner top plate 40. The width of the gap S defined by the jacket part 60 and the insert part 50 is preferably dimensioned such that a flow velocity of the cooling air K at the exit from the gap S into the combustion chamber 14 is less than a flow velocity of the cooling air when entering the gap S. ,

Im Fazit beruht die erfindungsgemƤƟ realisierte KĆ¼hlung der Brenner-Kopfplatte 40 auf einer PrallkĆ¼hlung, die die Brenner-Kopfplatte 40 als zentrales Bauteil des Brenners 1 sehr effizient kĆ¼hlt. Durch eine geeignete Wahl der KĆ¼hllufteindĆ¼sung am Rand der Brenner-Kopfplatte 40 wird der Verbrennungsprozess nicht negativ beeinflusst. AuƟerdem kann gemƤƟ der in den Figuren gezeigten AusfĆ¼hrungsform der Erfindung die KĆ¼hlluft K dem Gesamtprozess erhalten bleiben (als Variante ist auch eine nachfolgend noch beschriebene externe Abfuhr der KĆ¼hlluft K mƶglich). Als Auslegungskriterium der KĆ¼hlung dient der Druckverlust Ć¼ber den bzw. die Brenner 1 der Gasturbine.In summary, the inventively realized cooling of the burner top plate 40 is based on an impingement cooling, which cools the burner top plate 40 as a central component of the burner 1 very efficiently. By a suitable choice of KĆ¼hllufteindĆ¼sung the edge of the burner top plate 40, the combustion process is not adversely affected. In addition, according to the shown in the figures Embodiment of the invention, the cooling air K remain the overall process (as a variant also described below external removal of the cooling air K is possible). The design criterion for cooling is the pressure loss via the burner (s) 1 of the gas turbine.

ZusƤtzlich lassen sich bei der vorgeschlagenen Lƶsung leicht Armaturen zur Optimierung der KĆ¼hlung bzw, der KĆ¼hlluftmenge implementieren, wie z.B. die Steuermittel 21a.In addition, in the proposed solution, valves can be easily implemented to optimize cooling or the amount of cooling air, e.g. the control means 21a.

Obwohl in den Figuren 1 und 2 nicht dargestellt, kƶnnen alternativ oder zusƤtzlich zu dem Spalt S und den Ɩffnungen 51 auch in der Brenner-Kopfplatte 40 selbst eine Mehrzahl von Durchgangsƶffnungen vorgesehen sein, die den zweiten Teilraum 16b jeweils mit dem Brennraum 14 fluidverbinden.Although in the FIGS. 1 and 2 not shown, may alternatively or in addition to the gap S and the openings 51 in the burner top plate 40 itself a plurality of through holes may be provided, which fluidly connect the second subspace 16b respectively with the combustion chamber 14.

Auf diese Weise kann die Ć¼ber die Durchgangspassagen 31 in den zweiten Teilraum 16b eingestrƶmte KĆ¼hlluft K dann direkt Ć¼ber die Brenner-Kopfplatte 40 aus dem zweiten Teilraum 16b in den Brennraum 14 abgefĆ¼hrt werden.In this way, the cooling air K which has flowed into the second subspace 16b via the through passages 31 can then be removed from the second subspace 16b into the combustion chamber 14 directly via the burner head plate 40.

GemƤƟ einer bevorzugten Variante kƶnnen diese Durchgangsƶffnungen jeweils einen Durchmesser in einem Bereich von 0,3 mm bis 1,5 mm aufweisen, so dass die Durchgangsƶffnungen eine Effusion der Ć¼ber die Durchgangspassagen 31 in den zweiten Teilraum 16b eingestrƶmten KĆ¼hlluft K durch die Brenner-Kopfplatte 40 hindurch in den Brennraum 14 hinein bewirken.According to a preferred variant, these passage openings may each have a diameter in a range from 0.3 mm to 1.5 mm, so that the passage openings cause an effusion of the cooling air K, which has flowed into the second subspace 16b via the passage passages 31, through the burner head plate 40 through into the combustion chamber 14 into effect.

Alternativ zu den Durchgangsƶffnungen kann die Brenner-Kopfplatte 40 von einem porƶsen Material gebildet sein, so dass in den zweiten Teilraum 16b eingestrƶmte KĆ¼hlluft K Ć¼ber Poren der Brenner-Kopfplatte 40 in den Brennraum 14 hinein abstrƶmen kann.As an alternative to the passage openings, the burner top plate 40 may be formed by a porous material, so that cooling air K which has flowed into the second subspace 16b can flow out into the combustion chamber 14 via pores of the burner top plate 40.

In jedem dieser vorgenannten FƤlle wird die KĆ¼hlluft K dem primƤren Verbrennungsprozess wieder zugefĆ¼hrt.In each of these cases, the cooling air K is returned to the primary combustion process.

Alternativ dazu kann, obwohl ebenfalls nicht in den Figuren 1 und 2 gezeigt, in dem zweiten Teilraum 16b eine LuftabfĆ¼hrpassage vorgesehen sein, Ć¼ber die von der RĆ¼ckflƤche 40a der Brenner-Kopfplatte 40 abprallende KĆ¼hlluft K in Bezug auf den Verbrennungsprozess im Brennraum 14 strƶmungsabwirts der Brenner-Kopfplatte 40 entfernt von dieser eingespeist wird.Alternatively, although not in the FIGS. 1 and 2 2, an air discharge passage may be provided in the second subspace 16b via which cooling air K rebounding from the rear surface 40a of the burner top plate 40 is fed away from the burner head plate 40 remote from the combustion process in the combustion chamber 14.

Mit anderen Worten wird hier eine externe KĆ¼hlung eingesetzt, wobei die Entnahme der KĆ¼hlluft K wie bereits oben in Verbindung mit den anderen AusfĆ¼hrungsformen der Erfindung beschrieben oder an einem anderen Ort zwischen z.B. einem Verdichteraustritt und dem Luftsammelraum 13 erfolgt. Nach erfolgter KĆ¼hlung wird die KĆ¼hlluft K nicht direkt in den Brennraum 14 eingedĆ¼st, sondern abgeleitet. Die KĆ¼hlluft K wird also nicht unmittelbar nach dem Drallkƶrper 80, sondern an einer folgenden Position -stromab in Strƶmungsrichtung des HeiƟgases der Verbrennung V betrachtet- eingeleitet. Mƶgliche Positionen fĆ¼r die Einleitung der KĆ¼hlluft K liegen im Bereich einer SekundƤrzone des Brennraums 14 bis hin zu einem Abgaskamin der Gasturbine.In other words, here an external cooling is used, wherein the removal of the cooling air K as described above in connection with the other embodiments of the invention or at another location between e.g. a compressor outlet and the air collection chamber 13 takes place. After cooling, the cooling air K is not injected directly into the combustion chamber 14, but derived. The cooling air K is thus not immediately after the swirl body 80, but at a following position -stromab in the flow direction of the hot gas combustion V considered- initiated. Possible positions for the introduction of the cooling air K are in the range of a secondary zone of the combustion chamber 14 up to an exhaust stack of the gas turbine.

Der Vorteil dieser Lƶsungen besteht darin, dass eine Beeinflussung der Hauptstrƶmung und damit der Verbrennung V durch den KĆ¼hlluftstrom ausgeschlossen wird. ZusƤtzlich steigt das nutzbare DruckgefƤlle der KĆ¼hlung und damit kann eine grĆ¶ĆŸere Temperaturabsenkung erreicht werden. Der Nachteil der Lƶsung besteht darin, dass die KĆ¼hlluft K nur noch teilweise oder gar nicht mehr fĆ¼r den Gasturbinen-Prozess genutzt werden kann.The advantage of these solutions is that an influence of the main flow and thus the combustion V is excluded by the cooling air flow. In addition, the usable pressure gradient of the cooling increases and thus a greater temperature reduction can be achieved. The disadvantage of the solution is that the cooling air K can only partially or not at all be used for the gas turbine process.

BezugszeichenlisteLIST OF REFERENCE NUMBERS

11
Brennerburner
1010
GehƤusecasing
1111
Flammrohrflame tube
1212
Mantelcoat
1313
LuftsammelraumAir plenum
1414
Brennraumcombustion chamber
1515
Mischteilmixing section
1616
VerbrennungsvorraumVerbrennungsvorraum
16a16a
erster Teilraumfirst subspace
16b16b
zweiter Teilraumsecond subspace
2020
ZentraldeckelCentral cover
2121
Zuleitungselementsupplying member
21a21a
Steuermittelcontrol means
2222
LufteinlassƶffnungenAir intake openings
3030
Prallplatteflapper
3131
DurchgangspassagenThrough passages
4040
Brenner-KopfplatteBurner head plate
40a40a
RĆ¼ckflacherear Flat
5050
Einsetzteilinsert
5151
Ɩffnungopening
6060
Mantelteiljacket part
7070
Brennerdeckelburner caps
8080
Drallkƶrperswirler
SS
Spaltgap
VV
Verbrennungcombustion
KK
KuhlluftKuhlluft
RSRS
Rezirkulationsstrƶmungrecirculation

Claims (11)

  1. A burner (1) for a turbine, comprising:
    a housing (10), in which an air collection chamber (13), a combustion prechamber (16) and a combustion chamber (14) are formed,
    a burner head plate (40), which is arranged in the housing (10), so that the burner head plate (40) separates the combustion prechamber (16) from the combustion chamber (14),
    a baffle plate (30), which is arranged in the combustion prechamber (16) so that the baffle plate (30) subdivides the combustion prechamber (16) into a first part chamber (16a) adjoining an air supply that is fluidically connected to the air collection chamber (13) and a second part chamber (16b) adjoining the burner head plate (40),
    wherein the baffle plate (30) comprises a plurality of through-passages (31), which fluidically connect the first part chamber (16a) to the second part chamber (16b), so that air flowed via the air supply out of the air collection chamber (13) into the first part chamber (16a) can flow via the through-passages (31) into the second part chamber (16b) and flow onto a back surface (40a) of the burner head plate (40) facing the second part chamber (16b), wherein the baffle plate (30) extends parallel to the burner head plate (40), so that air flowed into the second part chamber (16b) perpendicularly strikes the back surface (40a) of the burner head plate (40) and wherein on the outer circumference of the burner head plate (40) a gap (S) is provided, via which the second part chamber (16b) is fluidically connected to the combustion chamber (14), so that air bouncing off the back surface (40a) of the burner head plate (40) can flow out via the gap (S) into the combustion chamber (14), characterized in that
    a width of the gap (S) is dimensioned so that a flow velocity of the air on exiting the gap (S) into the combustion chamber (14) is lower than a flow velocity of the air on entering the gap (S).
  2. The burner (1) according to Claim 1, wherein the second part chamber (16b) on the outer circumference is limited by an insert part (50), and wherein on a wall of the insert part (50) an opening (51) extending perpendicularly to the through-passages (31) is provided, which fluidically connects the second part chamber (16b) to the gap (S), so that air bouncing off the back surface (40a) of the burner head plate (40) can flow out into the gap (S) via the opening (51).
  3. The burner (1) according to Claim 1 or 2, wherein the gap (S) is formed as annular gap, and wherein in the wall of the insert part (50) a plurality of openings (51) extending perpendicularly to the through-passages (31) which are distributed along a circumference of the gap (S) are provided, which each fluidically connect the second part chamber (16b) to the gap (S), so that air bouncing off the back surface (40a) of the burner head plate (40) can flow out via the openings (51) into the gap (S).
  4. The burner (1) according to any one of the Claims 1 to 3, wherein the gap (S) extends parallel to the through-passages (31), so that a flow direction of the air through the gap (S) is parallel to a flow direction of the air through the through-passages (31) .
  5. The burner (1) according to any one of the Claims 1 to 4, wherein in the burner head plate (40) a plurality of through-openings is provided, which fluidically connect the second part chamber (16b) in each case to the combustion chamber (14).
  6. The burner (1) according to Claim 5, wherein the through-openings each have a diameter in a range from 0.3 mm to 1.5 mm, so that the through-openings bring about an effusion of the air flowed via the through-passages (31) into the second part chamber (31) through the burner head plate (40) into the combustion chamber (14).
  7. The burner (a) according to any one of the Claims 1 to 6, wherein the burner head plate (40) is formed from a porous material so that air flowed into the second part chamber (16b) can flow out via the pores of the burner head plate (40) into the combustion chamber (14) .
  8. The burner (1) according to any one of the Claims 1 to 6, wherein in the second part chamber (16b) an air discharge passage is provided, via which the air bouncing off the back surface (40a) of the burner head plate (40), with respect to a combustion process in the combustion chamber (14), can be fed in downstream of the burner head plate (40).
  9. The burner (1) according to Claim 8, wherein the air discharge passage opens into a secondary zone of the combustion chamber (14).
  10. The burner (1) according to Claim 8, wherein the air discharge passage opens into an exhaust stack of the burner (1).
  11. A gas turbine having a burner (1) according to any one of the Claims 1 to 10.
EP10171616.5A 2009-10-28 2010-08-02 Burner for a turbine and gas turbine with same Active EP2317227B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102009046066A DE102009046066A1 (en) 2009-10-28 2009-10-28 Burner for a turbine and thus equipped gas turbine

Publications (3)

Publication Number Publication Date
EP2317227A2 EP2317227A2 (en) 2011-05-04
EP2317227A3 EP2317227A3 (en) 2017-09-13
EP2317227B1 true EP2317227B1 (en) 2019-10-02

Family

ID=43532770

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10171616.5A Active EP2317227B1 (en) 2009-10-28 2010-08-02 Burner for a turbine and gas turbine with same

Country Status (5)

Country Link
US (1) US9140452B2 (en)
EP (1) EP2317227B1 (en)
JP (1) JP5160616B2 (en)
CA (1) CA2714259C (en)
DE (1) DE102009046066A1 (en)

Families Citing this family (5)

* Cited by examiner, ā€  Cited by third party
Publication number Priority date Publication date Assignee Title
DE102011082884A1 (en) 2011-09-16 2013-03-21 Man Diesel & Turbo Se Burner and gas turbine with such a burner
US10612781B2 (en) * 2014-11-07 2020-04-07 United Technologies Corporation Combustor wall aperture body with cooling circuit
WO2018044266A1 (en) * 2016-08-30 2018-03-08 Siemens Aktiengesellschaft Impingement cooling features for gas turbines
CN110925795A (en) * 2019-11-06 2020-03-27 č„æ北巄äøšå¤§å­¦ Afterburning chamber of doublestage burning
DE102020116245B4 (en) 2020-06-19 2024-03-07 Man Energy Solutions Se Gas turbine assembly with combustion chamber air bypass

Citations (2)

* Cited by examiner, ā€  Cited by third party
Publication number Priority date Publication date Assignee Title
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
US6679063B2 (en) * 2000-10-02 2004-01-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head for a gas turbine

Family Cites Families (34)

* Cited by examiner, ā€  Cited by third party
Publication number Priority date Publication date Assignee Title
DE2018641C2 (en) * 1970-04-18 1972-05-10 Motoren Turbinen Union REVERSE COMBUSTION CHAMBER FOR GAS TURBINE ENGINES
US4008568A (en) * 1976-03-01 1977-02-22 General Motors Corporation Combustor support
GB2098719B (en) * 1981-05-20 1984-11-21 Rolls Royce Gas turbine engine combustion apparatus
FR2572463B1 (en) * 1984-10-30 1989-01-20 Snecma INJECTION SYSTEM WITH VARIABLE GEOMETRY.
GB2204672B (en) * 1987-05-06 1991-03-06 Rolls Royce Plc Combustor
US5012645A (en) * 1987-08-03 1991-05-07 United Technologies Corporation Combustor liner construction for gas turbine engine
GB2219653B (en) * 1987-12-18 1991-12-11 Rolls Royce Plc Improvements in or relating to combustors for gas turbine engines
GB9112324D0 (en) * 1991-06-07 1991-07-24 Rolls Royce Plc Gas turbine engine combustor
CA2070518C (en) * 1991-07-01 2001-10-02 Adrian Mark Ablett Combustor dome assembly
DE4328294A1 (en) 1993-08-23 1995-03-02 Abb Management Ag Method for cooling a component and device for carrying out the method
GB2287310B (en) * 1994-03-01 1997-12-03 Rolls Royce Plc Gas turbine engine combustor heatshield
DE4427222A1 (en) 1994-08-01 1996-02-08 Bmw Rolls Royce Gmbh Heat shield for a gas turbine combustor
US5623827A (en) * 1995-01-26 1997-04-29 General Electric Company Regenerative cooled dome assembly for a gas turbine engine combustor
US5605046A (en) * 1995-10-26 1997-02-25 Liang; George P. Cooled liner apparatus
DE19542521A1 (en) 1995-11-15 1997-05-22 Ruhrgas Ag Air=fuel mixture combustion process
DE19549143A1 (en) 1995-12-29 1997-07-03 Abb Research Ltd Gas turbine ring combustor
FR2751731B1 (en) * 1996-07-25 1998-09-04 Snecma BOWL DEFLECTOR ASSEMBLY FOR A TURBOMACHINE COMBUSTION CHAMBER
FR2753779B1 (en) * 1996-09-26 1998-10-16 AERODYNAMIC INJECTION SYSTEM FOR A FUEL AIR MIXTURE
US6546733B2 (en) * 2001-06-28 2003-04-15 General Electric Company Methods and systems for cooling gas turbine engine combustors
US6495207B1 (en) * 2001-12-21 2002-12-17 Pratt & Whitney Canada Corp. Method of manufacturing a composite wall
US6749396B2 (en) * 2002-06-17 2004-06-15 General Electric Company Failsafe film cooled wall
US20040083734A1 (en) * 2002-11-05 2004-05-06 Kendall Robert M. Sintered metal fiber liner for gas burners
US6792757B2 (en) * 2002-11-05 2004-09-21 Honeywell International Inc. Gas turbine combustor heat shield impingement cooling baffle
US6871501B2 (en) * 2002-12-03 2005-03-29 General Electric Company Method and apparatus to decrease gas turbine engine combustor emissions
US7080515B2 (en) * 2002-12-23 2006-07-25 Siemens Westinghouse Power Corporation Gas turbine can annular combustor
EP1605209B1 (en) * 2004-06-07 2010-08-04 Siemens Aktiengesellschaft Combustor with thermo-acoustic vibrations dampening device
US7334408B2 (en) * 2004-09-21 2008-02-26 Siemens Aktiengesellschaft Combustion chamber for a gas turbine with at least two resonator devices
FR2889732B1 (en) * 2005-08-12 2011-09-23 Snecma COMBUSTION CHAMBER WITH IMPROVED THERMAL STRENGTH
US7878000B2 (en) * 2005-12-20 2011-02-01 General Electric Company Pilot fuel injector for mixer assembly of a high pressure gas turbine engine
US7631503B2 (en) * 2006-09-12 2009-12-15 Pratt & Whitney Canada Corp. Combustor with enhanced cooling access
GB2455021B (en) * 2006-09-14 2011-03-23 Solar Turbines Inc Splash plate dome assembly for a turbine engine
DE102006048842B4 (en) 2006-10-13 2019-10-10 Man Energy Solutions Se Combustion chamber for a gas turbine
US20090199563A1 (en) * 2008-02-07 2009-08-13 Hamilton Sundstrand Corporation Scalable pyrospin combustor
US9587832B2 (en) * 2008-10-01 2017-03-07 United Technologies Corporation Structures with adaptive cooling

Patent Citations (2)

* Cited by examiner, ā€  Cited by third party
Publication number Priority date Publication date Assignee Title
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
US6679063B2 (en) * 2000-10-02 2004-01-20 Rolls-Royce Deutschland Ltd & Co Kg Combustion chamber head for a gas turbine

Also Published As

Publication number Publication date
JP2011094949A (en) 2011-05-12
US20110265483A1 (en) 2011-11-03
EP2317227A2 (en) 2011-05-04
CA2714259A1 (en) 2011-04-28
CA2714259C (en) 2012-11-20
JP5160616B2 (en) 2013-03-13
EP2317227A3 (en) 2017-09-13
US9140452B2 (en) 2015-09-22
DE102009046066A1 (en) 2011-05-12

Similar Documents

Publication Publication Date Title
EP1654495B1 (en) Heat shield arrangement for a high temperature gas conveying component, in particular for a gas turbine combustion chamber
EP1005620B1 (en) Thermal shield component with recirculation of cooling fluid
DE2710618C2 (en) Fuel injector for gas turbine engines
DE69210118T2 (en) Construction of a combustion chamber dome
DE102009044585B4 (en) Method for operating a turbine engine and arrangement in a turbine engine
EP2317227B1 (en) Burner for a turbine and gas turbine with same
EP2224099B1 (en) Gas turbine active tip clearance control
DE602005001742T2 (en) Aerodynamic foaming fuel / air injection system for a gas turbine combustor
EP2260180B1 (en) Guide vane for a gas turbine
DE60218565T2 (en) Method and apparatus for cooling a gas turbine combustion chamber
EP2084368B1 (en) Turbine blade
DE102009026379A1 (en) Cooling chamber component cooled by impingement cooling and effusion cooling
DE112009000822T5 (en) Burner component and method of manufacture
CH699125A2 (en) Cooling of the rear end of a combustor transition piece and associated method.
WO2014177371A1 (en) Burner lance having heat shield for a burner of a gas turbine
EP2275743A2 (en) Gas turbine combustion chamber with starter film for cooling the combustion chamber wall
EP2954262B1 (en) Jet burner with cooling duct in the base plate
EP3132202B1 (en) Bypass heat shield element
EP3219918B1 (en) Gasturbine with a cooling device for cooling platforms of a guide blade assembly of the gas turbine
EP2340397A1 (en) Burner inserts for a gas turbine combustion chamber and gas turbine
EP2808611B1 (en) Injector for introducing a fuel-air mixture into a combustion chamber
EP2230458A1 (en) Burner assembly for fluid fuels and method for producing a burner assembly
DE2116429A1 (en) Combustion chamber for gas turbine engines
CH706962B1 (en) Serpentine cooling of the vane end wall.
DE102011057131A1 (en) Combustor assemblies for use in turbines and methods of assembling same

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

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 SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME RS

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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 SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME RS

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/14 20060101AFI20170810BHEP

Ipc: F23R 3/42 20060101ALI20170810BHEP

Ipc: F23R 3/04 20060101ALI20170810BHEP

Ipc: F23R 3/26 20060101ALI20170810BHEP

Ipc: F23R 3/28 20060101ALI20170810BHEP

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

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20171106

RBV Designated contracting states (corrected)

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 SE SI SK SM TR

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

Free format text: STATUS: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20180420

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: MAN ENERGY SOLUTIONS SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20190613

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

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 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

Ref country code: AT

Ref legal event code: REF

Ref document number: 1186600

Country of ref document: AT

Kind code of ref document: T

Effective date: 20191015

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502010016283

Country of ref document: DE

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: CH

Ref legal event code: NV

Representative=s name: E. BLUM AND CO. AG PATENT- UND MARKENANWAELTE , CH

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20191002

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: 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: 20200103

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: 20191002

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: 20191002

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: 20191002

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: 20191002

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: 20200102

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: 20191002

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: 20200102

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: 20191002

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: 20200203

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

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: 20200224

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: 20191002

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: 20191002

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: 20191002

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502010016283

Country of ref document: DE

PG2D Information on lapse in contracting state deleted

Ref country code: IS

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: 20191002

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: 20191002

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: 20191002

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: 20200202

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: 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: 20191002

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: 20191002

26N No opposition filed

Effective date: 20200703

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

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: 20191002

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: 20191002

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: 20200802

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20200831

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

Ref country code: IE

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

Effective date: 20200802

Ref country code: BE

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

Effective date: 20200831

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1186600

Country of ref document: AT

Kind code of ref document: T

Effective date: 20200802

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: 20200802

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: 20191002

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: 20191002

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: 20191002

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: 20191002

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

Ref country code: IT

Payment date: 20230825

Year of fee payment: 14

Ref country code: GB

Payment date: 20230822

Year of fee payment: 14

Ref country code: CH

Payment date: 20230902

Year of fee payment: 14

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

Ref country code: SE

Payment date: 20230821

Year of fee payment: 14

Ref country code: FR

Payment date: 20230824

Year of fee payment: 14

Ref country code: DE

Payment date: 20230821

Year of fee payment: 14