EP1319895B1 - Brûleur à prémélange à combustion pauvre pour turbine à gaz et son procédé de fonctionnement - Google Patents

Brûleur à prémélange à combustion pauvre pour turbine à gaz et son procédé de fonctionnement Download PDF

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Publication number
EP1319895B1
EP1319895B1 EP02023428A EP02023428A EP1319895B1 EP 1319895 B1 EP1319895 B1 EP 1319895B1 EP 02023428 A EP02023428 A EP 02023428A EP 02023428 A EP02023428 A EP 02023428A EP 1319895 B1 EP1319895 B1 EP 1319895B1
Authority
EP
European Patent Office
Prior art keywords
fuel
nozzles
lean
burn
accordance
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
EP02023428A
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German (de)
English (en)
Other versions
EP1319895A3 (fr
EP1319895A2 (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
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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 EP1319895A2 publication Critical patent/EP1319895A2/fr
Publication of EP1319895A3 publication Critical patent/EP1319895A3/fr
Application granted granted Critical
Publication of EP1319895B1 publication Critical patent/EP1319895B1/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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2201/00—Staged combustion
    • F23C2201/20—Burner staging

Definitions

  • the invention relates to a lean burn burner for a gas turbine with the features of the preamble of the main claim and to a method for operating a lean burn burner.
  • the invention relates to a lean burn burner with at least one fuel feed ring provided with primary fuel nozzles.
  • Such a lean burn burner can be designed either as an LPP module or as a swirl cup.
  • Magervormischbrenner are known from the prior art in a variety of Ausgestaltunsformen.
  • lean burn burners have been developed to prevent the formation of nitrogen oxides.
  • the air-fuel ratio is set high due to the process, resulting in a very lean mixture. This produces relatively low combustion temperatures in the main burnup zone.
  • a further disadvantage is that a combustion guide is achieved by the very lean mixture, which under normal circumstances can not be carried much further without creating instabilities. Another transformation finally leads to the extinction of the flame. It follows that additional so-called pilot burners must be available for safe, aviation-efficient operation. These pilot burners ensure a high local combustion temperature. This in turn leads to a high flame stability. A disadvantage of the operation of the pilot burner, it turns out that relatively high NO x emissions arise.
  • the US Pat. No. 6,109,038 A discloses a burner having two concentric independent fuel supply rings. These are each provided with fuel outlet openings, which serve to introduce fuel into different air flow paths
  • the US 5,351,477 A. discloses a separate fuel conduit disposed in a gas-fuel conduit and serving to deliver additional fuel. It is thus provided fuel supply ring, which is equipped with additional fuel nozzles.
  • the US 4 222 243 A shows fuel ports, which are arranged on two axially staggered rings and can be controlled separately.
  • the invention is based on the object to provide a lean burn burner and a method for operating a lean burn burner, which lead in a simple structure while avoiding the prior art to a low thermal load and burn safely even under very lean conditions.
  • the object is achieved with regard to the lean burn burner by the combination of features of the main claim, with regard to the method, the solution of the problem by the feature combination of the independent claim.
  • the respective subclaims show further advantageous embodiments of the invention.
  • the lean burn burner according to the invention is characterized by a number of significant advantages.
  • the additional fuel secondary nozzles it is possible to locally enrich the fuel-air mixture. It is thus not necessary to provide additional pilot burners or the like. Rather, according to the invention, there are areas on the fuel injection ring at which a richer fuel-air mixture is present. This leads to combustion at higher temperatures and thus to a more stable flame guidance. This results in a more stable operation of the lean burn burner, the risk of extinction is thereby avoided in a reliable manner.
  • the fuel primary nozzles are evenly distributed on the circumference of the fuel supply ring, while the fuel secondary nozzles are distributed unevenly around the circumference. It is particularly advantageous if the fuel secondary nozzles are arranged only in some sectors of the fuel injection system. This ensures that individual areas of the fuel injection system can be supplied with a richer mixture.
  • the fuel supply is switched according to the invention so that selectively at low or low load in the vicinity of at least two primary fuel nozzles additional, adjacent fuel secondary nozzles for enrichment of the fuel-air mixture are put into operation.
  • the primary fuel nozzles are switched on again in order to achieve a continuous increase in the fuel mass flow. The then no longer required fuel secondary nozzles are blown out accordingly.
  • fuel mini nozzles are formed on the fuel injection ring. These fuel mini nozzles can be arranged in groups (clusters).
  • a richer air-fuel mixture is locally adjusted at the fuel supply ring, while no fuel is injected at other locations of the fuel supply ring.
  • the total amount of fuel supplied to the lean premix burner remains substantially the same.
  • Another significant advantage of the invention is that a continuous transition from full load to low or low load can be made.
  • discontinuous fuel shift between pilot burners and Magervormischbrennern and the systems required for this purpose can be completely dispensed with according to the invention. This in turn results in a better thrust curve when switching the gas turbine to different load ranges.
  • the reference numeral 1 shows a schematic side view of an inventive lean premix module in a gas turbine combustor.
  • the reference numeral 1 denotes a flame tube, which is preceded by a lean premix burner. This comprises an outer housing 2 and an inner housing 3. On the inner housing, a fuel-injection ring 4 is formed.
  • the reference numeral 5 describes an inner body of the lean premix burner, with the reference numeral 6 are generally fuel nozzles shown.
  • FIG. 2 shows a sectional view along the line A-B of FIG. 1.
  • a plurality of fuel nozzles 6 are shown schematically on the fuel supply ring 4.
  • FIG. 2 explains that individual ones of the fuel nozzles 6, namely the fuel nozzles 6a are in operation while the illustrated fuel nozzles 6b are out of operation.
  • Fig. 3 is again enlarged a section through an embodiment of the fuel supply ring according to the invention 4.
  • This comprises two fuel supply ducts 7, which each have a plurality of fuel primary nozzles 8 and fuel secondary nozzles 9 are assigned at the periphery. From the representation of FIG. 3 it follows that the fuel primary nozzles 8 and the fuel primary nozzles 9 are each provided with their own fuel supply channels 7, so that a different supply of fuel can take place.
  • FIGS. 4 and 5 each show in an end view (greatly simplified) the arrangement of the fuel nozzles on the circumference of the fuel supply ring 4.
  • the individual fuel primary nozzles 8 are evenly distributed around the circumference and are accordingly in Business.
  • Fig. 5 shows a total of four fuel nozzle sectors in which different, unevenly distributed over the circumference arrangements of fuel secondary nozzles 9 are shown. Since the fuel primary nozzles 8 and the fuel primary nozzles 9 are located in different planes (see FIG. 3), the arrangement of the fuel secondary nozzles 9 shown in FIG. 5 results.
  • FIG. 6 shows a symmetrical peripheral circuit in which lean premix modules 14 which are in operation alternate with lean premix modules 15 which are out of operation.
  • FIG. 7 a diagram is selected in which an asymmetrical circumferential step (grouping peripheral circuit) is selected.
  • Each of a plurality of lean premix modules 14 are operating side-by-side, while adjacent several bulk premix modules 15 are taken out of service.
  • FIG. 8 shows a sectional view, similar to FIG. 2, in which fuel mini-nozzles 13 are additionally provided in a clustered arrangement on the fuel supply ring 4. These fuel mini-nozzles 13 have a higher injection speed of the fuel and thereby lead to a locally richer fuel-air mixture. Adjacent to the fuel mini-nozzles 13 schematically fuel-primary nozzles 8 are shown.
  • Fig. 9 is a diagram is shown, in which the fuel mass flow is shown against the thermal load of the engine / the gas turbine. The resulting straight line leads from the zero point through a full load point.
  • the burners are switched to the three different operating stages shown below.
  • a switching point is provided.
  • the burner modules or lean burn burners are switched off in such a way that the lean burn burners or modules remaining in operation reach a thermal load of approximately 100% at the switching point I.
  • the circuit is via valves, with switches or controllable valves can be used.
  • a middle switching point II which may be about half the thermal load of the first point I, groups of injectors of the previously left in operation lean burn burner or lean modules are turned off. This achieves a continued operation of the existing fuel injectors at 100% (at the switching point) of the individual fuel mass flow rate.
  • an asymmetrical arrangement of the fuel nozzles remaining in operation can be provided (asymmetric group circuit).
  • At the third switching point III is a further load reduction switching from the normal nozzles (fuel primary nozzles and fuel secondary nozzles) on clusters of mini nozzles or secondary Eindadorering before.
  • These mini nozzles have, as described, a significantly smaller diameter than the normal nozzles.
  • the mini nozzles / secondary nozzles lead to an acceptable fuel Zersteubungs at low load with comparatively better droplet evaporation behavior and yet locally produce a relatively rich air-fuel mixture.
  • the improved fuel atomization and better droplet evaporation behavior are also advantageous and important because in the low load range of the gas turbine, the delivery temperature of the compressor is low. According to the invention, a flameproof mixture is thus produced.
  • a grouping or interconnection of individual modules of lean premix burners takes place in an annular combustion chamber in order to combine the lean burn burners in operation into groups at low load.
  • By switching off other lean burn burner or modules results in the remaining modules or lean burn burner with a constant fuel quantity of the combustion chamber a richer or richer mixture.
  • additional secondary nozzles or mini-nozzles in order to select individual areas within a lean burn burner in which (seen in the circumferential direction) a single sector richer or richer fuel-air mixture is present.

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

Claims (10)

  1. Brûleur à prémélange pauvre pour une turbine à gaz avec au moins une rampe d'alimentation en combustible (4) pourvue de buses primaires de combustible (8), sur lequel sont arrangées des buses secondaires de combustible (9) additionnelles, sachant que l'alimentation en combustible des buses secondaires de combustible (9) est indépendante de d'alimentation en combustible des buses primaires de combustible (8), caractérisé en ce que les buses primaires de combustible (8) sont régulièrement réparties sur la circonférence de la rampe d'alimentation en combustible (4), alors que les buses secondaires de combustible (9) sont irrégulièrement réparties sur la circonférence.
  2. Brûleur à prémélange pauvre selon la revendication n° 1, caractérisé en ce que les buses secondaires de combustible (9) ne sont arrangées que dans certains secteurs de la rampe d'alimentation en combustible (4).
  3. Brûleur à prémélange pauvre selon la revendication n° 1, caractérisé en ce que des minibuses de combustible (13) sont prévues sur la rampe d'alimentation en combustible (4).
  4. Brûleur à prémélange pauvre selon la revendication n° 3, caractérisé en ce que les minibuses de combustible (13) sont arrangées en groupes.
  5. Brûleur à prémélange pauvre selon une des revendications n° 1 à 4, caractérisé en ce que les buses secondaires de combustible (9) et/ou les minibuses de combustible (13) fournissent un mélange air-combustible plus riche.
  6. Procédé pour le fonctionnement d'un brûleur à prémélange pauvre pour une turbine à gaz avec au moins une rampe d'alimentation en combustible (4) pourvue de buses primaires de combustible (8), sur lequel sont arrangées des buses secondaires de combustible (9) additionnelles, caractérisé en ce que sous charge faible ou inférieure de la turbine à gaz un mélange air-combustible plus riche est établi localement sur la rampe d'alimentation en combustible (4) moyennant les buses secondaires de combustible (9), alors qu'aucun combustible n'est injecté à d'autres endroits de la rampe d'alimentation en combustible (4) moyennant les buses primaires de carburant (8), sachant que la quantité globale de combustible amené dans le brûleur à prémélange pauvre reste inchangée pour l'essentiel.
  7. Procédé selon la revendication n° 6, caractérisé en ce que sous charge faible ou inférieure de la turbine à gaz des buses secondaires de combustible (9) sont activées à proximité d'au moins deux buses primaires de combustible (8) pour enrichir localement le mélange air-combustible.
  8. Procédé selon la revendication n° 6 ou 7, caractérisé en ce que les buses primaires de combustible (8) qui ne se trouvent pas à proximité des buses secondaires de combustible (9) sont mises hors service.
  9. Procédé selon une des revendications n° 6 à 8, caractérisé en ce que l'alimentation locale en mélange air-combustible plus riche s'effectue par l'intermédiaire de minibuses de combustible (13) additionnelles, si la charge de la turbine à gaz est de nouveau réduite.
  10. Procédé selon la revendication n° 9, caractérisé en ce que les buses primaires de combustible (8), les buses secondaires de combustible (9) et les minibuses de combustible (13) qui se trouvent en service respectif, sont combinées en groupes locaux sur la circonférence de la rampe d'alimentation en combustible (4).
EP02023428A 2001-12-12 2002-10-19 Brûleur à prémélange à combustion pauvre pour turbine à gaz et son procédé de fonctionnement Expired - Fee Related EP1319895B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10160997 2001-12-12
DE10160997A DE10160997A1 (de) 2001-12-12 2001-12-12 Magervormischbrenner für eine Gasturbine sowie Verfahren zum Betrieb eines Magervormischbrenners

Publications (3)

Publication Number Publication Date
EP1319895A2 EP1319895A2 (fr) 2003-06-18
EP1319895A3 EP1319895A3 (fr) 2004-01-07
EP1319895B1 true EP1319895B1 (fr) 2007-11-07

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EP02023428A Expired - Fee Related EP1319895B1 (fr) 2001-12-12 2002-10-19 Brûleur à prémélange à combustion pauvre pour turbine à gaz et son procédé de fonctionnement

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Country Link
US (1) US6945053B2 (fr)
EP (1) EP1319895B1 (fr)
DE (2) DE10160997A1 (fr)

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Also Published As

Publication number Publication date
US6945053B2 (en) 2005-09-20
DE50211162D1 (de) 2007-12-20
DE10160997A1 (de) 2003-07-03
EP1319895A3 (fr) 2004-01-07
US20030106321A1 (en) 2003-06-12
EP1319895A2 (fr) 2003-06-18

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