EP2513562A1 - Brûleur pour une turbine - Google Patents

Brûleur pour une turbine

Info

Publication number
EP2513562A1
EP2513562A1 EP10786994A EP10786994A EP2513562A1 EP 2513562 A1 EP2513562 A1 EP 2513562A1 EP 10786994 A EP10786994 A EP 10786994A EP 10786994 A EP10786994 A EP 10786994A EP 2513562 A1 EP2513562 A1 EP 2513562A1
Authority
EP
European Patent Office
Prior art keywords
burner
fuel
fuel supply
oxidant
combustion chamber
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP10786994A
Other languages
German (de)
English (en)
Other versions
EP2513562B1 (fr
Inventor
Frank Reiss
Ulrich Orth
Holger Huitenga
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 Diesel and Turbo 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 Diesel and Turbo SE filed Critical MAN Diesel and Turbo SE
Publication of EP2513562A1 publication Critical patent/EP2513562A1/fr
Application granted granted Critical
Publication of EP2513562B1 publication Critical patent/EP2513562B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—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
    • F23R3/28—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

Definitions

  • the invention relates to a burner for a turbine, and more particularly to a device for premixing oxidant and fuel
  • turbines such as e.g.
  • Premix burner Gas turbines called "premix burner” or “Premix Burner” used.
  • premix burner gas turbines
  • Premix Burner By using premix technology, the mixing process of
  • Fuel and oxidants such as air are decoupled from the actual combustion process, i. preceded by this. This allows the peak combustion temperatures to be lowered. At the same time, the residence time of the fuel-oxidant mixture (e.g., fuel-air mixture) in the reaction zone may be shortened. In particular, this reduces the formation of NOx (especially thermal NOx).
  • fuel-oxidant mixture e.g., fuel-air mixture
  • Fuel injection should be carefully selected.
  • the burner for a turbine provided with a device for premixing air and fuel.
  • the burner has a cylindrical combustion chamber for gaseous or liquid fuel and a Haupindindüsung.
  • the combustion chamber is in an Axialnchtung of the burner bounded on one side by a burner bottom and radially by a flame tube.
  • the main injection is used to inject a premixed fuel-air mixture.
  • the injection takes place radially to a burner longitudinal axis via main nozzles, which open into a radial swirl generator.
  • the radial swirler is disposed between the burner bottom and the flame tube and causes the fuel-air mixture to be impinged with a swirl pulse and swirl into the combustion chamber.
  • Fuel burners are described in DE 198 59 210 A1 and in DE 38 19 898 A1.
  • the invention has for its object to provide a burner for a turbine, in a simple and cost-effective manner an extremely homogeneous premix of a in a combustion chamber of the burner
  • Fuel-air mixture is achieved.
  • a burner for a turbine comprises: a flame tube, in which a combustion chamber is formed, a jacket, which surrounds the flame tube from radially outside with a predetermined distance thereof, so that an oxidant collecting space is formed between flame tube and jacket, a combustor bottom defining the oxidizer plenum and combustion chamber at an axial end of the combustor, and a swirler axially disposed between the combustor tube and the burner floor axially adjacent the combustor bottom and radially adjacent to the oxidant plenum for supplying a fuel oxidant; Mixture in the combustion chamber, the
  • air is provided as the oxidizing agent, which is fed at atmospheric or elevated pressure into the oxidant collecting space.
  • Fuel supply pipes an optimal premix of fuel (eg fuel gas) and oxidizing agents (eg air) can be achieved. If the As fuel composition changes, the fuel delivery ports may be adjusted in size and shape.
  • fuel eg fuel gas
  • oxidizing agents eg air
  • all inlet passages are each provided with a fuel feed pipe.
  • At least one of the fuel supply pipes is arranged in the respective intake passage.
  • At least one of the fuel supply tubes is in the oxidant flow direction directly in front of the respective inlet passage, i. at the beginning of Einlasströmungs Kunststoffs arranged.
  • This embodiment of the invention represents a further advantageous variant for the arrangement of one or more or all Brennstoffzuzanrohre, wherein the mixing length or mixing distance of fuel and oxidant is maximally extended.
  • at least one of the fuel supply pipes is relative to a longitudinal center axis of the respective one
  • Inlet passage arranged off-center in the respective intake passage.
  • This embodiment of the invention represents yet another advantageous variant for the arrangement of one or more or all fuel supply pipes, wherein the respective off-center position in the inlet passage transversely to their
  • At least one of the fuel supply pipes or a plurality or all of the fuel supply pipes is arranged centrally in the respective intake passage with respect to the longitudinal central axis of the respective intake passage.
  • At least one of the fuel supply pipes has a plurality of fuel discharge openings spaced along the length of the fuel supply pipe.
  • the homogeneous mixing of fuel and oxidant can be further improved.
  • the fuel supply pipes each having a plurality of along the length of the BrennstoffzuWORKe each with a distance from each other
  • At least one of the Brennstoffzu classifiedrohre two fuel discharge openings which are arranged with respect to the length of the Brennstoffzu Technologyrohrs at the same position, so that these two fuel discharge openings fuel with two opposite direction components of the
  • Fuel supply tube can be dispensed.
  • the oxidant flow on both sides of the fuel supply pipe is utilized for fluidizing the fuel, thereby further improving homogeneous mixing of fuel and oxidant.
  • Fuel supply tube are arranged at the same position, so that these two fuel discharge openings fuel with two each other
  • the two fuel discharge openings are diametrically opposed to each other or include respective longitudinal center axes of the two fuel discharge openings at an obtuse angle.
  • Fuel supply pipes each have a cylindrical cross section or a wing-shaped cross-section or other suitable for optimum turbulence cross-sections. According to the invention, all
  • Fuel supply tubes have the same cross-sectional shape.
  • the airfoil shape may prove advantageous for reducing direct mixing in the pipe wake, which may be particularly necessary with reactive fuels (such as hydrogen).
  • the fuel supply tubes are each detachably mounted so that each is arranged in a predetermined manner
  • the fuel feed configuration formed fuel supply tube is individually replaceable with a fuel supply tube according to another predetermined fuel mixing configuration.
  • the burner according to the invention is suitable for the use of fuel gas as fuel.
  • the burner according to the invention can also be operated with liquid fuel, wherein, if necessary, special nozzles should be inserted into the fuel discharge openings.
  • Fuel gas) and oxidizing agent e.g., air. This can be low
  • Emission values can be achieved. At the same time can by the individual
  • FIG. 1 shows a schematic longitudinal sectional view of the structure of a
  • Burner of a gas turbine according to an embodiment of the invention.
  • FIG. 2 shows a schematic cross-sectional view of a part of the burner of FIG. 1, seen along a line A-A in FIG.
  • FIG. 3 shows in enlarged partial views of an inlet passage of the burner of Figure 2 three possible configuration variants of a
  • FIG. 4 shows two possible configuration variants of a fuel feed tube in an inlet passage of the burner according to the invention, as seen along a line B-B in FIG.
  • FIG. 1 shows the structure of a burner 1 of a gas turbine (not completely shown) according to an embodiment of the invention.
  • the burner 1 has a flame tube 10, in which a combustion chamber 1 1 is formed, and a tubular shell 20, the flame tube 10 from radially outward encloses it with a predetermined distance, so that between
  • Flame tube 10 and shell 20 an oxidant-collecting space 21 is formed.
  • Oxidizing agent for the fuel gas is provided atmospheric air, which is compressed by a compressor (not shown) and then the
  • Oxidant collecting space 21 is supplied.
  • the burner 1 further has a burner bottom 30 defining the Oxidationsffen- collecting space 21 and the combustion chamber 1 1 at an axial end of the burner 1, and a swirl generator 40, the axially adjacent to the burner bottom 30 and radially to the oxidant collecting space 21 axially between the flame tube 10 and the burner bottom 30 is arranged, for supplying a
  • Fuel-oxidizer mixture BOG in the combustion chamber 1 1.
  • the swirl generator 40 has a plurality of circumferentially spaced apart UR of the burner 1 (FIG. here eight) of vanes 41.
  • the guide vanes 41 are each shaped and arranged such that the respective distances between the guide vanes 41 form a plurality (in this case eight) of radial inlet passages 42 each having a tangential component in their course toward the combustion chamber 11.
  • a fuel supply pipe 43a, 43b, 43c, 43d each having a length in an axial direction AR (see FIG 1) of the burner 1 and extends transversely to an oxidant flow direction OR through the respective inlet passage 42 therethrough.
  • Fuel supply pipe 43a, 43b, 43c, 43d may also be provided in more or less or in all inlet passages 42 respective fuel supply pipes 43a, 43b, 43c, 43d.
  • each fuel supply pipe 43a, 43b, 43c, 43d has in its wall at least one fuel discharge port 44, 45 radial with respect to the fuel supply pipe 43a, 43b, 43c, 43d, over which
  • each fuel dispensing opening 44, 45 is formed as a bore or as a nozzle insert.
  • Inlet passages 42 may be arranged. As also seen from FIG. 2, the fuel supply pipes 43a, 43b, 43d may be disposed within the respective intake passages 42 at different positions along the length of the respective ones
  • Inlet passages 42 may be arranged.
  • Inlet passages 42 (ie at the entrance of the respective inlet passages 42 partially or completely in the oxidant collecting space 21) may be arranged.
  • one, several or all fuel supply pipes 43 a, 43 b, 43 c may be arranged centrally in the respective intake passages 42 with respect to longitudinal center axes L of the respective intake passages 42.
  • one, several or all of the fuel supply pipes 43d may be off-center with respect to the longitudinal center axes L of the respective ones
  • Inlet passages 42 may be arranged in these.
  • one or more, or all can
  • Fuel supply pipes 43 a, 43 b, 43 c, 43 d a plurality of
  • one, several or all fuel supply pipes 43a, 43b, 43c, 43d may have only a single fuel discharge opening 44, 45 with respect to the respective length of the fuel supply pipes 43a, 43b, 43c, 43d [variant b) in Fig. 4].
  • one, several or all of the central fuel supply pipes 43a, 43b, 43c (designated by 43a-c in FIG. 3) and also one, several or all off-center fuel supply pipes 43d (not in FIG shown) have two fuel discharge openings 44, 45, which are arranged at the same position with respect to the length of the Brennstoffzu Glassrohrs, so that these two fuel discharge openings 44, 45 fuel BS with two opposite direction components (as shown by the
  • Fuel supply pipe 43 a, 43 b, 43 c, 43 d seen diametrically
  • Fuel discharge openings 44, 45 is arranged.
  • the fuel supply pipes 43a, 43b, 43c, 43d each have a cylindrical cross section.
  • the fuel supply pipes 43a, 43b, 43c, 43d may also have a wing-shaped cross-section or other suitable for homogeneous mixing of oxidant and fuel
  • a hydrofoil shape is for example in
  • Each of fuel supply pipes 43a, 43b, 43c, 43d is detachably mounted in the burner 1 such that each of fuel supply pipes 43a, 43b, 43c formed according to a predetermined fuel mixing configuration (position of the fuel supply pipe in the intake passage, number and arrangement of the fuel discharge ports, cross sectional shape of the fuel supply pipe); 43d is individually replaceable with a fuel supply pipe 43a, 43b, 43c, 43d, if necessary, according to another predetermined fuel mixing configuration.
  • the fuel supply pipes 43a, 43b, 43c, 43d (designated 43a-d in Fig. 4) are detachably inserted into corresponding openings in the burner bottom 30, as shown in Fig. 4, with each fuel supply pipe 43a, 43b, 43c, 43d a longitudinal end of a flange or head portion 46, 47th which, on the side facing away from the swirl generator 40 of the
  • Burner bottom 30 abuts this and e.g. by means of screws (not shown) screwed to the burner bottom 30.
  • each fuel delivery tube 43a, 43b, 43c, 43d is naturally connected via respective conduits and control valves (both not shown) to a fuel source (not shown), such as a fuel source.
  • Fuel gas tank fluid-connected.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Combustion Of Fluid Fuel (AREA)

Abstract

L'invention concerne un brûleur pour une turbine, comprenant: un tube foyer dans lequel est formée une chambre de combustion, une enveloppe qui entoure le tube foyer extérieurement de manière radiale à une distance déterminée de sorte qu'une chambre collectrice d'agent d'oxydation est formée entre le tube foyer et l'enveloppe, un fond de brûleur qui limite la chambre collectrice d'agent d'oxydation et la chambre de combustion à une extrémité axiale du brûleur, et un générateur de tourbillon qui est disposé sur le fond de brûleur et de manière radialement limitrophe de la chambre collectrice d'agent d'oxydation et axialement entre le tube foyer et le fond du brûleur pour acheminer un mélange de combustible et d'agent d'oxydation dans la chambre de combustion. Le générateur de tourbillon présente plusieurs aubes de guidage disposées le long d'une direction circonférentielle du brûleur à distance circonférentielle les unes des autres de sorte que les distances entre les aubes de guidage forment plusieurs passages d'entrée radiaux en direction de la chambre de combustion qui présentent respectivement dans leur tracé une composante tangentielle. Un tube d'alimentation en combustible qui s'étend le long d'une direction axiale du brûleur et transversalement à une direction d'écoulement d'agent d'oxydation à travers le passage d'entrée concerné est prévu dans la région d'écoulement d'entrée d'au moins certains des passages d'entrée et chaque tube d'alimentation en combustible présente dans sa paroi au moins une ouverture radiale de délivrance de combustible par laquelle le combustible peut être mélangé dans le passage d'entrée en question avec une composante de direction s'étendant transversalement à la direction d'écoulement de l'agent d'oxydation.
EP10786994.3A 2009-12-15 2010-09-28 Brûleur pour une turbine Active EP2513562B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009054669A DE102009054669A1 (de) 2009-12-15 2009-12-15 Brenner für eine Turbine
PCT/DE2010/050074 WO2011072665A1 (fr) 2009-12-15 2010-09-28 Brûleur pour une turbine

Publications (2)

Publication Number Publication Date
EP2513562A1 true EP2513562A1 (fr) 2012-10-24
EP2513562B1 EP2513562B1 (fr) 2018-07-18

Family

ID=43568285

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10786994.3A Active EP2513562B1 (fr) 2009-12-15 2010-09-28 Brûleur pour une turbine

Country Status (6)

Country Link
US (1) US20120227407A1 (fr)
EP (1) EP2513562B1 (fr)
JP (1) JP2013517440A (fr)
CA (1) CA2782196C (fr)
DE (1) DE102009054669A1 (fr)
WO (1) WO2011072665A1 (fr)

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US9581333B2 (en) * 2012-05-01 2017-02-28 Aerco International, Inc. Igniter assembly and method for operating
US9677766B2 (en) * 2012-11-28 2017-06-13 General Electric Company Fuel nozzle for use in a turbine engine and method of assembly
KR102184778B1 (ko) 2013-12-19 2020-11-30 한화에어로스페이스 주식회사 가스터빈용 선회기
JP6602004B2 (ja) * 2014-09-29 2019-11-06 川崎重工業株式会社 燃料噴射器及びガスタービン
EP3098514A1 (fr) * 2015-05-29 2016-11-30 Siemens Aktiengesellschaft Agencement de chambre de combustion
US10215415B2 (en) * 2015-09-23 2019-02-26 General Electric Company Premix fuel nozzle assembly cartridge
EP3236157A1 (fr) * 2016-04-22 2017-10-25 Siemens Aktiengesellschaft Générateur de tourbillonnement pour mélanger un combustible avec de l'air dans un moteur à combustion
JP6995696B2 (ja) * 2018-05-28 2022-01-17 三菱重工業株式会社 燃料噴射装置及びガスタービン
CN113310071B (zh) * 2021-06-16 2022-11-15 哈尔滨工程大学 一种用于气体燃料燃气轮机低污染燃烧室的同轴分级燃烧器
CN113834094B (zh) * 2021-09-15 2022-11-01 中国船舶重工集团公司第七0三研究所 一种带有切向旋流结构的喷嘴

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Also Published As

Publication number Publication date
US20120227407A1 (en) 2012-09-13
WO2011072665A1 (fr) 2011-06-23
JP2013517440A (ja) 2013-05-16
CA2782196A1 (fr) 2011-06-23
DE102009054669A1 (de) 2011-06-16
CA2782196C (fr) 2014-07-29
EP2513562B1 (fr) 2018-07-18

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