EP1484553B1 - Brûleur pour une chambre de combustion de turbine à gaz - Google Patents

Brûleur pour une chambre de combustion de turbine à gaz Download PDF

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Publication number
EP1484553B1
EP1484553B1 EP04090216A EP04090216A EP1484553B1 EP 1484553 B1 EP1484553 B1 EP 1484553B1 EP 04090216 A EP04090216 A EP 04090216A EP 04090216 A EP04090216 A EP 04090216A EP 1484553 B1 EP1484553 B1 EP 1484553B1
Authority
EP
European Patent Office
Prior art keywords
burner
air
fuel
main air
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.)
Expired - Fee Related
Application number
EP04090216A
Other languages
German (de)
English (en)
Other versions
EP1484553A3 (fr
EP1484553A2 (fr
Inventor
Ralf Sebastian Von Der Bank
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1484553A2 publication Critical patent/EP1484553A2/fr
Publication of EP1484553A3 publication Critical patent/EP1484553A3/fr
Application granted granted Critical
Publication of EP1484553B1 publication Critical patent/EP1484553B1/fr
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—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
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00018—Means for protecting parts of the burner, e.g. ceramic lining outside of the flame tube

Definitions

  • the invention relates to a burner for a gas turbine combustor, in particular for an aircraft gas turbine, which comprises a lean burn burner with centrically integrated support burner.
  • Magervormischbrenner for gas turbine engines and other gas turbines used in the combustion chamber a fuel-air mixture is burned with high air content and low combustion temperature and correspondingly reduced nitrogen oxide formation, are well known.
  • the use of such burners is disadvantageous in that the flame stability is not guaranteed. That is, as the combustion temperature decreases, the air-fuel mixture introduced into the combustion chamber can no longer burn or ignite continuously, so that the flame may fluctuate or go out. In aircraft gas turbine engines, this problem is particularly at low outside temperatures, hail or rain showers or similar unfavorable weather conditions and thereby reduced temperature of the air-fuel mixture.
  • a sufficiently high air temperature is required to rapidly vaporize the liquid fuel introduced as droplet mist into the combustion chamber, to preheat, depending on the composition of the fuel-air mixture, the highest possible temperature and thus easier to ignite can.
  • the arranged in the combustion chamber lean burn burners is known to assign a firing or support burner, with a high combustion temperature is generated in an air-fuel mixture with higher fuel content (rich mixture), to be able to ignite the lean, low combustion temperature producing air-fuel mixture produced by the lean burn burner or main burner even at low air temperature and corresponding unfavorable evaporation behavior of the liquid fuel and to ensure the flame stability.
  • the combustion chamber is designed graduated in lean burn burners with support measures, each master / lean burn burner in a lateral gradation in each case a support burner is assigned separately.
  • a support burner is assigned separately.
  • combustor concepts are commonly referred to as “axially stepped combustors” or “double annular combustors.”
  • a burner combination of the type mentioned above, which has a main burner and a centrally integrated support burner in this, is for example in the EP 0 660 038 B1 described.
  • This burner comprises a main burner with an annular outer fuel-air mixing duct for generating a fuel-air mixture to be introduced into the combustion chamber and a support burner formed in an axially extending channel of a central body, that is centrally accommodated in the main burner, at its discharge opening fuel sprayed and mixed with a core air is introduced into the gas turbine combustor.
  • a stable flame formation in any operating condition can not be achieved with this burner design.
  • Such a burner is also off EP 1 134 494 known.
  • the invention has the object of providing a burner of the type mentioned in such a way that over the entire operating range of a gas turbine engine, a stable flame formation in the combustion chamber and an always safe function of the gas turbine is ensured.
  • the basic idea of the invention is a lean premix burner with a lean air-fuel mixture supplied via a main air ring channel and a support burner centrally integrated in the lean burn burner with a core air ring channel surrounded by the main air ring channel and a spray nozzle for fuel arranged at the discharge opening therein in that a flame stabilizing ring highly heated by the combustion process is arranged in the adjoining mouth region of the concentrically arranged annular channels, the air guiding flanks of which guide the main air-fuel mixture outwards and the core air flow inwards.
  • the gas flow generated by the hot flame stabilizing ring forms a hot, approximately hollow-cylindrical to barrel-shaped, stationary recirculation zone or hot gas zone which acts together with the stabilizing ring as an ignition element and in which the fuel discharged by the supporting burner is collected and completely burnt ,
  • the flame stabilization ring according to the invention it is possible to provide a stable, non-extinguishing flame in every operating state of a gas turbine equipped with a lean burn burner and integrated support burner, even when the air temperature is reduced due to external conditions, thus ensuring the functional safety of the gas turbine engine.
  • the flame stabilizing ring is formed as a conical ring, which has an enclosed by two legs, open towards the combustion chamber groove. On the side facing the burner, the legs form the guide flanks for the inwardly flowing core air or the outwardly flowing air-fuel mixture. At the same time its required cooling against overheating is ensured by the groove or the legs of the conical ring. The cooling takes place at the Lucasleitflanken the relatively thin-walled legs of Flame stabilizing ring with the supplied core air or main air.
  • the conical ring (flame stabilization ring) consists of a heat-resistant or heat-resistant or flame-side heat-resistant coated material.
  • the cone ring is mounted with the tip on the face of the central body, which separates the core air ring channel from the main air ring channel.
  • the burner 1 has a housing 2 and a central body 3 with a main air annular channel 4 formed between them for a main or lean burn burner, which is assigned to a combustion chamber 5 of a (aircraft) gas turbine.
  • main air swirl generator 6 are involved, which put the main air flow - arrow A - in a rotary motion.
  • liquid fuel is injected after the swirl generation, which mixes with the hot air stream and partially evaporated in this.
  • the introduced into the combustion chamber 5 - lean - fuel-air mixture has a high proportion of air and burns in the combustion chamber 5 with a correspondingly low combustion temperature, so that the nitrogen oxide emission and consequently the air pollution is extremely low.
  • the low pollutant emission achieved with low combustion temperatures is associated with a flame instability occurring in particular in unfavorable weather conditions due to the consequent reduced air inlet temperature.
  • a running in the central axis channel 7 for receiving a support burner comprising a nebulizer, consisting of atomizer fins 18, a fuel line 8, a subsequent thereto atomizer carrier tube 9 and an opening into the combustion chamber 5 atomizer nozzle 10, and formed on the circumference of the atomizer core air ring channel 11 comprises.
  • Core air supplied in accordance with the arrow B passes through the core air annular channel 11 and a core air swirler 12 for generating axial rotational movement of the core air into the gas turbine combustor 5 to produce a fuel air therein to produce a stable flame with the fuel sprayed from the atomizer nozzle 10 To provide a mixture with a high fuel content.
  • the direction of rotation of the main air flow and the core air flow is preferably in the same direction.
  • An essential component of the present lean burn burner with centrally integrated auxiliary burner is a flame stabilization ring adjoining the central body 3 in the mouth region of the core air ring channel 11 and the main air ring channel 4, which is in the form of a conical ring 13 with a tip adjoining the central body 3 and one of an annular core air flank 14 and an annular Hauptluftleitflanke 15 formed, facing the interior of the combustion chamber 5 groove 16 is executed.
  • the fuel exit angle from the atomizer nozzle 10 is adjusted so that the fuel droplets meet the very hot, stationary recirculation zone 17 and are burned there and can not reach the combustion chamber walls beyond this area.
  • the conical ring 13 is made of heat-resistant steel, optionally with a ceramic protective coating on the flame side, or even completely of a ceramic material (advantageous: fiber-ceramic composite materials). Overheating of the conical ring 13 is prevented by suitable choice of material and the good heat transfer to the relatively thin-walled core and Hauptluftleitflanken 14, 15 of the conical ring 13 and at the rear as a cooling medium flowing main air (air-fuel mixture) or core air.

Landscapes

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

Claims (4)

  1. Brûleur (1) pour la chambre de combustion (5) d'une turbine à gaz, en particulier d'une turbine à gaz aéronautique, avec brûleur stabilisateur central intégré,
    sachant qu'un canal annulaire d'air primaire (11) logeant une buse d'atomisation (10) du brûleur stabilisateur (20) aboutissant dans la chambre de combustion (5) est entouré par un canal annulaire d'air principal (4),
    que l'angle de sortie de carburant de la buse d'atomisation (10) est compris entre 60° et 130°, et est de préférence égal à 95°,
    que des générateurs de tourbillonnement d'air principal et d'air primaire (respectivement 6 et 12) sont disposés dans le canal annulaire d'air principal et dans le canal annulaire d'air primaire (4, 11),
    que dans la zone où se rejoignent le canal annulaire d'air principal et le canal annulaire d'air primaire (4, 11) est disposé un anneau stabilisateur de flamme (13) conçu comme anneau conique, qui se raccorde avec son sommet à un corps central (3) séparant le canal annulaire d'air primaire (11) du canal annulaire d'air principal (4), et caractérisé en ce que l'anneau conique est muni d'un flanc de guidage d'air primaire (14) orienté vers l'intérieur pour dévier le flux d'air primaire (flèche B) vers l'intérieur, et d'un flanc de guidage d'air principal (15) orienté vers l'extérieur pour dévier le flux d'air principal (flèche A) vers l'extérieur, et présente une gorge (16) sur son côté orienté vers la chambre de combustion (5) de la turbine à gaz,
    sachant que le brûleur (1) reçoit par le canal annulaire d'air principal (4) un mélange air-carburant pauvre et par le canal annulaire d'air primaire (11) et la buse d'atomisation (10) du brûleur stabilisateur (20) un mélange carburant-air à forte teneur en carburant
    et qu'à partir de la gorge (16) est formée avec la racine de flamme située dans la gorge (16) une zone de recirculation (17) pour l'essentiel en forme de cylindre creux et cambrée, stationnaire et chaude en tant que partie de flamme stable et qui s'étend avec une température maximale dans la chambre de combustion (5) de la turbine à gaz.
  2. Brûleur selon la revendication n° 1, caractérisé en ce que l'anneau conique (21) est constitué d'un acier thermorésistant.
  3. Brûleur selon la revendication n° 1 ou n° 2, caractérisé en ce que l'anneau conique (21) est muni d'un revêtement céramique dans la zone de la gorge (16).
  4. Brûleur selon la revendication n° 1, caractérisé en ce que l'anneau conique (21) est constitué d'un matériau céramique.
EP04090216A 2003-06-06 2004-06-02 Brûleur pour une chambre de combustion de turbine à gaz Expired - Fee Related EP1484553B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10326720A DE10326720A1 (de) 2003-06-06 2003-06-06 Brenner für eine Gasturbinenbrennkammer
DE10326720 2003-06-06

Publications (3)

Publication Number Publication Date
EP1484553A2 EP1484553A2 (fr) 2004-12-08
EP1484553A3 EP1484553A3 (fr) 2006-11-29
EP1484553B1 true EP1484553B1 (fr) 2011-09-28

Family

ID=33154610

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04090216A Expired - Fee Related EP1484553B1 (fr) 2003-06-06 2004-06-02 Brûleur pour une chambre de combustion de turbine à gaz

Country Status (3)

Country Link
US (1) US7621131B2 (fr)
EP (1) EP1484553B1 (fr)
DE (1) DE10326720A1 (fr)

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Also Published As

Publication number Publication date
US7621131B2 (en) 2009-11-24
DE10326720A1 (de) 2004-12-23
EP1484553A3 (fr) 2006-11-29
EP1484553A2 (fr) 2004-12-08
US20050028526A1 (en) 2005-02-10

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