EP0108361B1 - Brûleur de prémélange avec brûleur à diffusion intégré - Google Patents

Brûleur de prémélange avec brûleur à diffusion intégré Download PDF

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Publication number
EP0108361B1
EP0108361B1 EP83110824A EP83110824A EP0108361B1 EP 0108361 B1 EP0108361 B1 EP 0108361B1 EP 83110824 A EP83110824 A EP 83110824A EP 83110824 A EP83110824 A EP 83110824A EP 0108361 B1 EP0108361 B1 EP 0108361B1
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EP
European Patent Office
Prior art keywords
burner
fuel
premixing
fuel nozzle
diffusion
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
Application number
EP83110824A
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German (de)
English (en)
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EP0108361A1 (fr
Inventor
Wolfram Dipl.-Ing. Krockow
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Kraftwerk Union AG
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Kraftwerk Union AG
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Publication of EP0108361A1 publication Critical patent/EP0108361A1/fr
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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
    • F23R3/36—Supply of different fuels
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/005—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D23/00—Assemblies of two or more burners
    • 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
    • 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

Definitions

  • the invention relates to a premix burner with an integrated diffusion burner for gas turbine combustion chambers according to the preamble of claim 1.
  • NO x When gaseous or liquid fuels are burned in gas turbine combustion chambers, the nitrogen oxides NO and NO z , which are collectively referred to as NO x , are among the pollutants in the exhaust gas.
  • the NO x content in the exhaust gas is to be kept as low as possible, for example in the USA a limit value of 75 ppm at 15% by volume 0 2 may not be exceeded due to environmental protection regulations. Compliance with these regulations is particularly difficult when conventional diffusion burners are used in the gas turbine combustion chambers. In such diffusion burners, the fuel is introduced directly into the combustion zone via a fuel nozzle and mixed there with the combustion air, the combustion being controlled by turbulent diffusion processes between the fuel, the combustion air and the exhaust gas products. Since there are large temperature differences with high temperature peaks due to the locally different mixing ratios of fuel and combustion air during combustion, there is a relatively high NO x content in the exhaust gas.
  • premix burners for gas turbine combustion chambers, in whose premixing chambers the premixing and pre-evaporation of the liquid fuel supplied by fuel nozzles and / or the premixing of the gaseous fuel supplied by fuel nozzles with the combustion air takes place with a large excess of air .
  • Premixing means that locally different mixing ratios of fuel and combustion air are avoided during combustion.
  • such premix burners have a much smaller working range than the conventional diffusion burners, ie the mixing ratios of fuel and combustion air must be kept within relatively narrow limits. If the fuel content is too high, too much NO X is formed and if there is too little fuel, the combustion goes out.
  • the fuel lines of the individual premix burners are therefore equipped with valves so that, depending on the load of the gas turbine, only so many premix burners are supplied with fuel for the operation of which the narrow limits of the mixing ratios can be maintained.
  • some conventional diffusion burners are also provided, which are only used to start the gas turbine and are then switched off again.
  • hybrid burners for gas turbine combustion chambers consist of premix burners with integrated diffusion burners.
  • the premix burner has a premixing chamber delimited at the downstream end by a flame holder, into which a main fuel nozzle and a feed device for combustion air open.
  • the diffusion burner has a pilot fuel nozzle arranged in the central area of the flame holder, the combustion air for the operation of the diffusion burner being supplied partly through the premixing chamber of the premixing burner and partly through holes arranged in the flame tube of the gas turbine combustion chamber.
  • a fuel control device which regulates the total amount and the partial amounts of the fuel supplied to the main fuel nozzle and the pilot fuel nozzle in dependence on the load of the gas turbine in such a way that only the diffusion burner can be operated until the idling speed or a low partial load has been reached and then the diffusion burner and the premix burner can be operated together.
  • Such hybrid burners therefore have the advantage that separate start-up burners designed as diffusion burners can be dispensed with in a space-saving, compact design.
  • the flame of the diffusion burner supports the combustion of the mixture of fuel and combustion air generated in the premixing chamber, ie the flame of the premix burner can also be ignited reliably with extremely lean mixture ratios with regard to low NO x formation.
  • the hybrid burner can thus be operated over a wide load range with a low NO x content in the exhaust gas, although an undesirable increase in NO x formation can be observed in the upper load range and in particular under limit load.
  • the invention has for its object to provide a premix burner with an integrated diffusion burner for gas turbine combustion chambers, which enables operation with low NO x formation over the entire load range.
  • the invention is based on the knowledge that when the premix burner is operated solely in the upper load range, the NO x formation can be significantly reduced and that the premix burner can only be operated in the upper load range if the entire available combustion air is exclusive is fed via the premixing chamber.
  • the fuel control device reduces the partial quantity of the fuel supplied to the pilot fuel nozzle as the load increases as soon as the idling speed or a low partial load is reached.
  • the NO x formation caused by the operation of the diffusion burner is then reduced more than the NO x formation additionally caused by the operation of the premix burner with a correspondingly increased amount of fuel, the support of the However, the flame of the premix burner is fully guaranteed by the flame of the diffusion burner.
  • the fuel control device can also be assigned to further premix burners with integrated diffusion burners, as a result of which, in particular, the overall effort required for valves in a gas turbine combustion chamber can be significantly reduced.
  • the premix burner has a first main fuel nozzle for gaseous fuel and a second main fuel nozzle for liquid fuel.
  • the diffusion burner can then also have a first pilot fuel nozzle for gaseous fuel and a second pilot fuel nozzle for liquid fuel.
  • the integration of the diffusion burner into the premix burner can be accomplished with particularly little effort in that the fuel supply line to the pilot fuel nozzle passes through the premix chamber centrally and in the axial direction. If the diffusion burner can be operated with gaseous and / or liquid fuel, it is correspondingly provided that the fuel feed lines to the first pilot fuel nozzle and the second pilot fuel nozzle penetrate the premixing chamber centrally and in the axial direction as concentric tubes.
  • premix burner can also be operated with gaseous and / or liquid fuel, a particularly compact design can be achieved in that the fuel feed lines to the two main fuel nozzles and the two pilot fuel nozzles are designed as concentric tubes.
  • the feed device for combustion air opening into the premixing chamber is designed as a swirl device. This further promotes the intensive mixing of combustion air and fuel in the premixing chamber.
  • the swirl device can then also be designed simultaneously as a main fuel nozzle, with several fuel injection bores being made in each case in vanes designed as hollow blades.
  • a particularly intensive atomization and pre-evaporation of liquid fuel in the combustion air can also be achieved in that the premixing chamber has a venturi-like contour with a section converging at the upstream end and a section diverging at the downstream end.
  • both the premix burner and the diffusion burner can be operated with gaseous and / or liquid fuel
  • the fuel feed lines, the main fuel nozzles and the two pilot fuel nozzles can be combined to form a component which can be pulled out of the premixing chamber in the axial direction.
  • the hybrid burner 1 shows a highly simplified schematic illustration of a longitudinal section through a hybrid burner, designated overall by 1, which can be operated as a premix burner and / or diffusion burner.
  • the hybrid burner 1 has a burner housing 10 which carries a flame holder 11 at one end and a swirl device 12 at its other end.
  • a main fuel nozzle 13 is arranged in the central region of the swirl device 12, while the fuel feed line is designated by 14.
  • a pilot fuel nozzle 15 is arranged in the central area of the flame holder 11, the fuel feed line 16 passing through the main fuel nozzle 13 and the burner housing 10 centrally and in the axial direction.
  • the liquid main fuel indicated by an arrow HB arrives from a fuel tank BT via a main fuel pump HBP and a main fuel control valve HBRV into the fuel feed line 14 of the main fuel nozzle 13.
  • the main fuel HB is then injected in finely divided form into a premixing chamber 100 which is delimited by the burner housing 10, the flame holder 11 and the swirl device 12.
  • the main fuel HB is evaporated in this premixing chamber 100 and mixed with the combustion air VL supplied via the swirl device 12, this mixing and the pre-evaporation being favored by the venturi-like contour of the burner housing 10.
  • the combustion of the homogeneous mixture of main fuel HB and combustion air VL formed in the premixing chamber 100 then takes place only in the flame tube F of a gas turbine combustor, which is not shown in any more detail mer, wherein the flame holder 11 serves to stabilize the flame, but still prevents the flame from kicking back into the premixing chamber 100.
  • the pilot fuel indicated by an arrow PB reaches the fuel feed line 16 of the pilot fuel nozzle 15 from the fuel tank BT via a pilot fuel pump PBP and a pilot fuel control valve PBRV. From the pilot fuel nozzle 15 15, the pilot fuel PB is then injected in finely divided form directly into the combustion zone of the flame tube F and mixed there with the combustion air VL supplied exclusively via the swirl device 12, the premixing chamber 100 and the flame holder 11, the combustion being effected by turbulent diffusion processes between the Pilot fuel PB, the combustion air VL and the exhaust products is controlled.
  • the total amount of fuel supplied and the partial amounts supplied as pilot fuel PB or as main fuel HB are regulated via a fuel control device BRE depending on the load of the gas turbine.
  • the fuel control device BRE to which a corresponding load signal LS is applied, regulates the flow through the pilot fuel control valve PRBV and the main fuel control valve HBRV via corresponding control lines AL1 and AL2 in such a way that only the diffusion burner until the idling speed or a low partial load is reached It can be operated that the diffusion burner and the premix burner can then be operated together and that only the premix burner can be operated in the upper load range.
  • the flame tube F shown in FIG. 1 can be, for example, the flame tube of a primary combustion chamber, the gas turbine combustion chamber having a large number of such primary combustion chambers opening into a common mixing chamber.
  • the fuel control device BRE, the pilot fuel control valve PRBV and the main fuel control valve HBRV can then be summarized for all hybrid burners 1 of the gas turbine combustion chamber, since the large working range of the hybrid burner 1 means that separate control and a load-dependent switching on and off of individual primary combustion chambers can be omitted .
  • Such a common fuel control device is also possible if a large number of hybrid burners open into the flame tube of a gas turbine combustion chamber. This case is shown in FIG. 2, but only three hybrid burners 1 are shown to simplify the drawing.
  • FIG. 2 three hybrid burners 1 can be seen in FIG. 2, which open into the flame tube designated F 'of a gas turbine combustion chamber, which is otherwise not shown in detail.
  • the flame tube F ' has no openings for the entry of combustion air in the region of the combustion zone, since all of the available combustion air VL is supplied exclusively to the mixing chambers 100 of the hybrid burner 1. However, this does not rule out the fact that openings for the entry of mixed air may be present in the flame tube F 'downstream of the combustion zone.
  • the pilot fuel PB reaches the fuel supply lines 16 to the pilot fuel nozzles 15 of the individual hybrid burners 1 via a common pilot fuel pump PBP ′, a common pilot fuel control valve PBRV and a distributor V1 shown as a circle.
  • the main fuel H B reaches the main fuel nozzles 13 of the individual hybrid burners 1 via a common main fuel pump HBP ', a common main fuel control valve HBRV' and a distributor V2 shown as a circle in the fuel supply lines 14.
  • the total quantity of fuel B supplied to hybrid burners 1 and the partial quantities supplied overall as pilot fuel PB or as main fuel HB are regulated by a fuel control device BRE 'depending on the load of the gas turbine.
  • the fuel control device BR E ' to which a corresponding load signal LS is applied, regulates the flow through the common pilot fuel control valve PBRV' and the common main fuel control valve HBRV 'via corresponding control lines AL1' and AL2 'in such a way that until the Idle speed or a low partial load, only the diffusion burners can be operated, that afterwards the diffusion burners and the premix burners can be operated together and that only the premix burners can be operated in the upper load range.
  • the mode of operation described above can be seen in more detail from the diagram in FIG. 3.
  • the power N of the gas turbine up to the limit load in percent is plotted on the right branch of the abscissa, the speeds n up to idling speed in rpm are plotted on the left branch of the abscissa and the fuel quantities m on the ordinate.
  • the solid curve shows the total amount m G of the fuel B supplied (see FIG. 2), the dashed curve, the amount mp of the total pilot fuel PB supplied (see FIG. 2) and the dashed curve, the amount m H of the total main fuel HB supplied (see FIG. 2).
  • the exclusive operation of the diffusion burners is continued for a short time after the idling speed has been reached, until the premix burners are switched on at a low partial load and are supplied with an increasing amount m H of main fuel HB (FIG. 2).
  • the amount mp of the pilot fuel PB (FIG. 2) fed to the diffusion burner is reduced.
  • the diffusion burners are then switched off completely and only the premix burners are operated, ie only main fuel HB (see FIG. 2) is supplied.
  • the upper load range in which the diffusion burners are switched off could also be defined as the range between the flame stability limit of the premix burners and the desired NO x limit at the limit load.
  • the diffusion burners are only switched off when the premix burners can burn alone without the support of the flame of the diffusion burners and without the risk of extinguishing.
  • the diagram of FIG. 4 shows the NO x emission during operation of the gas turbine combustion chamber shown in FIG. 2.
  • the NO x content in the exhaust gas in ppm at 15 vol.% O 2 is plotted on the ordinate.
  • the straight line G running parallel to the abscissa indicates a NO x limit value of 75 ppm at 15 vol.% O 2 , which must not be exceeded during operation of the gas turbine combustion chamber.
  • the hybrid burners 1 are operated exclusively as diffusion burners until a low partial load is reached, the NO x content in the exhaust gas being indicated by point A on curve D during this operating phase. Thereafter, the hybrid burners 1 are operated as a diffusion burner and at the same time as a premix burner, the NO x content in the exhaust gas being indicated by the thick curve AB during this operating phase.
  • the last vertical section of curve AB illustrates the drop in the NO x content in the exhaust gas after the diffusion burner has been completely switched off. Accordingly, the point B lies above the flame stability limit S v on the curve V.
  • the hybrid burners 1 are then operated in the upper load range exclusively as a premix burner, the NO x content in the exhaust gas during this operating phase being caused by the thickly drawn-out partial area BC curve V is given.
  • Point C corresponds to the maximum value of the NO x content in the exhaust gas reached at the limit load, although this maximum value is still significantly below the permissible NO x limit. Point C is therefore also the design point of the gas turbine combustion chamber, which is decisive for the total number of hybrid burners 1 required.
  • the hybrid burner which can be operated with gaseous and / or liquid fuel in the longitudinal section or in cross section only partially shown.
  • the hybrid burner designated as a whole by 1 ', has a burner housing which is indicated by the broken line 10' and which has a venturi-like contour.
  • the premixing chamber 100 'formed by the burner housing 10' is delimited at its downstream end by a flame holder 11 'only indicated in the drawing and at its upstream end by a swirl device 12'.
  • the swirl device 12 'simultaneously forms a first main fuel nozzle for gaseous fuel, a plurality of fuel injection bores 120' being made in each of the individual vanes designed as hollow blades.
  • the gaseous fuel indicated by an arrow H B " is supplied via a fuel feed line 14", on which the vanes of the swirl device 12 'designed as hollow blades are placed.
  • a second main fuel nozzle 13 'for liquid fuel is arranged at a short distance downstream of the swirl device 12' and also has vanes in the form of hollow blades, into each of which a plurality of fuel injection bores 130 'are made.
  • the supply of the liquid fuel indicated by arrows HB 'to the fuel injection bores 130' takes place via a fuel feed line 14 ', which is arranged concentrically within the fuel feed line 14 "and on which the vanes of the second main fuel nozzle 13', which are designed as hollow blades, are placed .
  • a first pilot fuel nozzle 15 "for gaseous fuel and a second pilot fuel nozzle 15 'for liquid fuel are arranged in the central region of the flame holder 11'.
  • the supply of the gaseous fuel indicated by an arrow PB" to the first pilot fuel nozzle 15 " takes place via a fuel feed line 16 ′′, which initially runs concentrically within the fuel feed line 14 ′ and then passes through the premixing chamber 100 ′ centrally and in the axial direction.
  • the liquid fuel, indicated by an arrow PB ′, is supplied to the second pilot fuel nozzle 15 ′ via a fuel feed line 16 ′, which is arranged concentrically within the fuel feed line 16 ′′.
  • the four fuel feed lines 14 ′′, 14 ′, 16 ′′, 16 ′, the swirl device 12 ′ that is simultaneously designed as the first main fuel nozzle, the second main fuel nozzle 13 ′, the first pilot fuel nozzle 15 ′′ and the second pilot fuel nozzle 15 ′ are combined into one component which can be pulled out of the burner housing 10 'and the flame holder 11' in the axial direction to facilitate maintenance and inspection.
  • the operation of the hybrid burner 1 'shown in FIGS. 5 and 6 corresponds to the operation of the hybrid burner 1 shown in FIGS. 1 and 2, but for the liquid fuels PB' and HB 'and for the gaseous fuels PB "and HB"
  • a fuel control device is provided in each case. If the hybrid burner 1 'is to be operated simultaneously with liquid and gaseous fuel, these two fuel control devices are to be linked to one another in accordance with the operating mode shown in FIG. 3.

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

Claims (12)

1. Brûleur à prémélange avec brûleur à flamme de diffusion intégré pour des chambres de combustion de turbine à gaz, dans lequel:
- le brûleur à prémélange possède une chambre de prémélange délimitée par un accrocheur de flamme à l'extrémité en aval, dans laquelle débouchent une buse pour le combustible principal et un dispositif d'amenée pour de l'air de combustion,
- le brûleur à flamme de diffusion possède une buse pour le combustible pilote disposée dans la région centrale de l'accrocheur de flamme et dans lequel:
- un dispositif de réglage de combustible règle la quantité totale et les quantités partielles du combustible envoyé à la buse pour le combustible principal et à la buse pour le combustible pilote en fonction de la charge de la turbine, de manière que, jusqu'à ce que le nombre de tours en marche à vide ou sous une faible charge partielle soit atteint, seul le brûleur à flamme de diffusion puisse fonctionner et qu'ensuite le brûleur à flamme de diffusion et le brûleur à prémélange puissent fonctionner ensemble,
remarquable par les caractéristiques suivantes:
a) tout l'air de combustion (VL) nécessaire au fonctionnement du brûleur à flamme de diffusion peut être amené exclusivement par la chambre de prémélange (100; 100'),
b) le dispositif de réglage du combustible (BRE; BRE') règle la quantité totale (mG) et les quantités partielles (mp, mH) du combustible amené (B), de manière que seul le brûleur prémélange puisse fonctionner dans la plage supérieure des charges.
2. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant la revendication 1, caractérisé en ce que le dispositif de réglage du combustible (BRE; BRE') réduit, pour des charges croissantes, la quantité partielle (mp) du combustible (PB; PB', PB") envoyée à la buse pour du combustible pilote (15; 15', 15"), dès que l'on atteint le nombre de tours en marche à vide ou sous une faible charge partielle.
3. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant la revendication 1 ou 2, caractérisé en ce que le dispositif de réglage du combustible (BRE') est associé à d'autres brûleurs à prémélange avec brûleurs à flamme de diffusion intrégrés.
4. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant l'une des revendications précédentes, caractérisé en ce que le brûleur à prémélange possède une première buse pour du combustible principal destinée à du combustible gazeux (HB") et une seconde buse pour du combustible principal (13') destinée à du combustible liquide (HB').
5. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant l'une des revendications précédentes, caractérisé en ce que le brûleur à flamme de diffusion possède une première buse pour du combustible pilote (15') destinée à du combustible gazeux (PB") et une seconde buse pour du combustible pilote (15') destinée à du combustible liquide (PB').
6. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant l'une des revendications 1 à 4, caractérisé en ce que le conduit d'amenée du combustible (16) allant à la buse pour du combustible pilote (15) passe, au centre et suivant la direction axiale, dans la chambre de prémélange (100).
7. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant la revendication 5, caractérisé en ce que les conduits d'amenée du combustible (16", 16') à la première buse pour du combustible pilote (15") et à la seconde buse pour du combustible pilote (15') passent, au centre et suivant la direction axiale, dans la chambre de prémélange (100') sous forme de tubes concentriques.
8. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant les revendications 4 et 6, caractérisé en ce que les conduits d'amenée du combustible (14", 14', 16", 16') menant aux deux buses pour le combustible principal (13') et aux deux buses pour le combustible pilote (15", 15') sont agencés en tubes concentriques.
9. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant l'une des revendications précédentes, caractérisé en ce que le dispositif d'amenée de l'air de combustion qui débouche dans la chambre de prémélange (100') est agencé en dispositif à tourbillonnement (12').
10. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant la revendication 9, caractérisé en ce que le dispositif à tourbillonnement (12') constitue en même temps une buse pour le combustible principal, plusieurs perçages d'injection du combustible (120') étant percés dans des ailes agencées en pales creuses.
11. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant l'une des revendications précédentes, caractérisé en ce que la chambre de prémélange (100; 100') possède un contour semblable à un venturi, avec une section convergente à l'extrémité en amont, et une section divergente à l'extrémité en aval.
12. Brûleur à prémélange avec brûleur à flamme de diffusion intégré suivant la revendication 8, caractérisé en ce que les conduits d'amenée du combustible (14", 14', 16", 16'), les deux buses pour le combustible principal (13') et les deux buses pour le combustible pilote (15", 15') sont rassemblés en une pièce qui peut être extraite de la chambre de prémélange (100') suivant la direction axiale.
EP83110824A 1982-11-08 1983-10-28 Brûleur de prémélange avec brûleur à diffusion intégré Expired EP0108361B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19823241162 DE3241162A1 (de) 1982-11-08 1982-11-08 Vormischbrenner mit integriertem diffusionsbrenner
DE3241162 1982-11-08

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EP0108361A1 EP0108361A1 (fr) 1984-05-16
EP0108361B1 true EP0108361B1 (fr) 1985-08-14

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US (1) US4589260A (fr)
EP (1) EP0108361B1 (fr)
JP (1) JPS59101551A (fr)
DE (2) DE3241162A1 (fr)

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DE19618058A1 (de) * 1996-05-06 1997-11-13 Abb Research Ltd Brenner
DE19839085C2 (de) * 1998-08-27 2000-06-08 Siemens Ag Brenneranordnung mit primärem und sekundärem Pilotbrenner

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EP0488556B1 (fr) * 1990-11-27 1997-07-16 General Electric Company Injecteur secondaire de carburant à prémélange avec dispositif de tourbillonnement incorporé
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JPH0159414B2 (fr) 1989-12-18
EP0108361A1 (fr) 1984-05-16
JPS59101551A (ja) 1984-06-12
DE3360574D1 (en) 1985-09-19
DE3241162A1 (de) 1984-05-10
US4589260A (en) 1986-05-20

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