WO1997011782A2 - Ensemble ajutage pour combustible et procede de regulation du debit - Google Patents

Ensemble ajutage pour combustible et procede de regulation du debit Download PDF

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Publication number
WO1997011782A2
WO1997011782A2 PCT/DE1996/001860 DE9601860W WO9711782A2 WO 1997011782 A2 WO1997011782 A2 WO 1997011782A2 DE 9601860 W DE9601860 W DE 9601860W WO 9711782 A2 WO9711782 A2 WO 9711782A2
Authority
WO
WIPO (PCT)
Prior art keywords
fuel
fuel nozzle
return flow
area
inflow
Prior art date
Application number
PCT/DE1996/001860
Other languages
German (de)
English (en)
Other versions
WO1997011782A3 (fr
Inventor
Bernard Becker
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to EP96944567A priority Critical patent/EP0852516B1/fr
Priority to JP51308497A priority patent/JP3850881B2/ja
Priority to DE59609892T priority patent/DE59609892D1/de
Publication of WO1997011782A2 publication Critical patent/WO1997011782A2/fr
Publication of WO1997011782A3 publication Critical patent/WO1997011782A3/fr
Priority to US09/050,650 priority patent/US6092738A/en

Links

Classifications

    • 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
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F23D11/26—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed
    • F23D11/28—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space with provision for varying the rate at which the fuel is sprayed with flow-back of fuel at the burner, e.g. using by-pass
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
    • B05B—SPRAYING APPARATUS; ATOMISING APPARATUS; NOZZLES
    • B05B1/00—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means
    • B05B1/34—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl
    • B05B1/3405—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl to produce swirl
    • B05B1/341—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl to produce swirl before discharging the liquid or other fluent material, e.g. in a swirl chamber upstream the spray outlet
    • B05B1/3421—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl to produce swirl before discharging the liquid or other fluent material, e.g. in a swirl chamber upstream the spray outlet with channels emerging substantially tangentially in the swirl chamber
    • B05B1/3426—Nozzles, spray heads or other outlets, with or without auxiliary devices such as valves, heating means designed to influence the nature of flow of the liquid or other fluent material, e.g. to produce swirl to produce swirl before discharging the liquid or other fluent material, e.g. in a swirl chamber upstream the spray outlet with channels emerging substantially tangentially in the swirl chamber the channels emerging in the swirl chamber perpendicularly to the outlet axis

Definitions

  • the invention relates to a fuel nozzle arrangement for a fluid fuel burner with a main axis and a return flow area, an inflow area and a fuel nozzle, wherein a swirl flow of fuel can be generated in the flow area.
  • the invention further relates to the use of such a fuel nozzle arrangement and a method for regulating the fuel supply to a fluid fuel burner.
  • the fluid fuel is injected into a combustion chamber via a fuel nozzle arrangement.
  • a fuel nozzle arrangement Depending on the heat output to be generated and the amount of hot gas generated by the combustion of the fluid fuel, it is necessary to control the amount of fuel supplied. This regulation of the amount of fuel can be achieved with a constant amount of fuel fed into the fuel nozzle arrangement by backflow of fuel from the fuel nozzle arrangement without introduction into the combustion chamber.
  • DD-PS 22 076 describes an atomizer with a return control for liquid fuels, for example for gas turbine systems, in which an improvement in the closing process of its outlet opening is to be achieved.
  • fuel is fed to a swirl chamber via tangential feed channels. Openings not specified in detail are provided in the bottom of the swirl chamber, through which the amount of fuel to be returned is passed through one or more return channels and a return line into a combustion chamber. cloth tank is recycled.
  • DE 32 35 080 A1 also discusses the configuration of an outlet opening of an injection nozzle.
  • the described return injection nozzle for a gas turbine burner has a cylindrical return needle in the flow return.
  • the object of the invention is to provide a fuel nozzle arrangement with a backflow region for the backflow of fuel, which is easy to produce and even over a longer period under mechanical and thermal loads
  • Another object of the invention is to specify the use of such a fuel nozzle arrangement and a method for regulating the fuel supply of a fluid fuel burner.
  • the object directed to a fuel nozzle arrangement for a fluid fuel burner is achieved by a fuel nozzle arrangement which has a main axis, along which a return flow area, a fuel nozzle and an inflow area are arranged, the inflow area lying between the fuel nozzle and the return flow area
  • a swirl flow of fuel can be generated in the inflow region and the backflow region has an annular gap which adjoins the inflow region and tapers away in the direction away from the inflow region and merges into a backflow line.
  • the return flow area with the annular gap which tapers into a return flow line, can be produced mechanically in a simple manner, for example by turning and / or drilling, can be geometrically aligned exactly in the fuel nozzle arrangement and, owing to the simple geometry and Feasibility fixed in its geometrical arrangement even with high thermomechanical loads.
  • a core is formed by the annular gap, which is preferably directed along the main axis and has the shape of a needle. sits. This core is also geometrically fixed and can serve to stabilize an eddy current of the fuel which leads out of the fuel nozzle.
  • This vortex flow is achieved, for example, by a tangential flow of fuel into the inflow region, the inflow taking place in the tangential direction to a circle running perpendicular to the main axis.
  • the fuel flow supplied is divided in the inflow area, part of which can be returned to a fuel storage device via the annular gap and the return flow line.
  • the swirl of the fuel flow is reduced in the annular gap, so that there is an essentially swirl-free or at least with reduced swirl fuel flow in the return flow line.
  • the flow resistance in the return flow line therefore has a small value.
  • the simple geometric structure also ensures that the core formed by the annular gap is dimensionally stable.
  • the flow losses in the backflow area are also low.
  • the swirl reduction in the backflow area begins far upstream, i.e. m in the vicinity of the inflow area and, depending on the degree of taper, takes place in a more or less long axial area.
  • the swirl reduction also occurs with a weak effect, as a result of which the rotational symmetry of the swirling fuel flow in the fuel nozzle is not disturbed.
  • the backflow area can be constructed from a maximum of two parts, in particular from a single part.
  • the annular gap is preferably largely circular and symmetrical with respect to the main axis, as a result of which an influencing of the rotational symmetry of the vortex flow in the fuel nozzle is reliably avoided.
  • the annular gap has a cross section which alternately consists of narrow areas and wide areas. These alternately narrow areas and wide areas are preferably realized in that the annular gap merges continuously into a plurality of flow channels, which flow into the at least one return flow line.
  • Each flow channel has a preferably circular cross-section with a diameter which preferably remains constant in the axial direction and thus forms a wide range in the cross-section of the annular gap from a certain degree of tapering of the annular gap.
  • the flow channels are preferably bores which are directed in particular axially to the main axis. Thus, the flow channels and the annular gap can be drilled and / or
  • the flow channels are preferably symmetrical, in particular arranged on a circle with a center on the main axis.
  • three or more flow channels are preferably provided, in particular five to ten.
  • the flow channels preferably overlap axially with the return flow line, which can be produced as an axial bore.
  • the return flow line can have a diameter of about 2 cm. Due to the overlap of the flow channels with the return flow line, an inflow of the fuel into the return flow line is achieved with a low flow resistance.
  • the center line of the flow channels in particular designed as axial bores, is preferably on the outer circumference of the return flow line.
  • the back flow area of the fuel nozzle arrangement is preferably produced by turning and / or drilling. Because of the simple geometry, it can be made from a single part. Of course, a return flow area made up of several components is also possible.
  • the return flow area is preferably connected to the component containing the return flow line by means of welding. Other fastening options, for example using pins, are also conceivable. It is also possible to integrate the return flow line from a single part of the return flow area, in particular by drilling.
  • the use in an oil burner is particularly advantageous due to the exact, reproducible geometry of the return flow area, precise central alignment, and the stable design, which is robust even with a pulsating fuel flow. In particular, it is impossible for larger parts to fall out, so that a disturbance in the fuel flow in the fuel nozzle can be ruled out, thereby ensuring particularly effective operation of the oil burner.
  • the maintenance effort is also low due to the low wear in the backflow area.
  • the object directed to a method for regulating the fuel supply of a fluid fuel burner is achieved according to the invention in that in a fuel nozzle arrangement a constant amount of fuel is fed in and the amount of fuel flowing back via a return line is regulated by a control valve provided in the return line. This also regulates the amount of fuel flowing through the fuel nozzle.
  • the fuel nozzle arrangement preferably has a main axis, a backflow area, an inflow area and a fuel nozzle, which are arranged in this order along the main axis, with a swirl flow in the inflow area, in particular by tangential feeding of the fuel, can be generated.
  • the return flow area has an annular gap adjoining the inflow area, which tapers in the direction away from the inflow area and m merges with the return flow line.
  • FIG. 1 shows a longitudinal section through a fuel nozzle arrangement and FIG. 2 to 4 each show a cross section through the fuel nozzle arrangement according to FIG. 1.
  • the fuel nozzle arrangement 1 shows a fuel nozzle arrangement 1 in a longitudinal section, which is directed along a main axis 5 and is largely rotationally symmetrical with respect to this main axis 5.
  • the fuel nozzle arrangement 1 has a fuel nozzle 3 along the main axis 5 starting from the right-hand edge of the drawing, an adjoining inflow region 2 and an adjoining backflow region 4.
  • the backflow region 4 has an annular ring Gap 6, which tapers downstream in a tapering region (swirl reduction region) D1, D2.
  • the annular gap 6 merges continuously into a plurality of flow channels 11, which are designed as bores.
  • the annular gap 6 forms a metallic core 13 of the return flow area 4 on its side facing the inflow area 2, which is arranged centrally to the main axis 5.
  • the flow channels 11 run axially to the main axis 5 and open into a return flow line 7 arranged concentrically to the main axis 5. This return flow line 7 is likewise designed as a bore.
  • the flow channels 11 have a respective center 16, which is arranged on the outer circumference 15 of the return flow line 7.
  • a control valve 12 is arranged downstream of the flow channels 11 in the flow line 7.
  • FIG. 3 shows a cross section perpendicular to the main axis 5 in an area between the overlap area K and the swirl reduction area D1, D2 with six flow channels 11 with a circular cross section, the center points 16 of which are arranged on a circle centered on the main axis 5.
  • the tapering annular gap 6 has a cross section 8, which alternately has narrow areas 9 and wide areas 10.
  • the wide areas 10 are by the Flow channels 11 formed.
  • the annular gap 6 encloses a core 13 which is formed centrally to the main axis 5.
  • the fuel fed into the fuel nozzle assembly 1 enters the flow region 2 via an inflow channel 17 in the tangential direction em.
  • a swirling eddy current is formed in the inflow region 2, which is rotationally symmetrical to the main axis 5.
  • the return flow region 4 is guided in part of this flow according to the flow arrows 14 m.
  • Another part flows out in the form of a vortex from the fuel nozzle 3 into a combustion chamber (not shown).
  • This vortex-laden flow is stabilized by the core 13, so that a uniform injection of fuel into the combustion chamber is ensured. Due to the thermo-mechanically stable geomet ⁇ ische fixation of the remindström Geb 4 this uniform spraying is given over a longer period of time with high thermomechanical stresses.
  • the portion of the flow which also has a swirl and which enters the annular gap 6 experiences a reduction in the tapering area D1 or D2
  • the invention is distinguished by a particularly robust and easily producible return flow region of a fuel nozzle arrangement, in particular for an oil burner in a gas turbine.
  • the backflow region has an annular gap which forms a core (central body) which is central to the main axis of the fuel nozzle arrangement and is rotationally symmetrical and which serves to stabilize the flow of the fuel nozzle.
  • the annular gap tapers steadily in the direction of a return flow line and continuously changes into flow channels.
  • These flow channels smd are preferably formed axially to the main axis and axially overlap with the return flow line which also runs axially and centrally to the main axis.
  • the entire reverse flow range can be manufactured from a single part by turning and / or drilling. This ensures a precisely reproducible geometry, in particular a central arrangement, with low production costs and simple production. Even with a pulsating flow and high thermomechanical loads, the residual current area is stably fixed in its geometrical position. Tearing off or falling out of larger and smaller parts with an impairment of the flow in the fuel nozzle can be reliably avoided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Feeding And Controlling Fuel (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Silver Salt Photography Or Processing Solution Therefor (AREA)

Abstract

L'invention concerne un ensemble ajutage (1) pour combustible destiné à un brûleur à combustible liquide, comportant un axe principal (5) et une zone de reflux (4), un ajutage (3) pour combustible et une zone d'afflux (2) située le long de l'axe principal (5) entre l'ajutage (3) et la zone de reflux (4). Un courant hélicoïdal de combustible peut être produit dans la zone d'afflux (2). La zone de reflux (4) présente un espace annulaire (6) adjacent à la zone d'afflux (2), qui se rétrécit dans la direction opposée la zone d'afflux (2) et se prolonge par une conduite de reflux (7). L'invention concerne également une utilisation dudit ensemble (1) dans un brûleur à mazout pour une turbine à gaz et un procédé de régulation de l'alimentation en combustible d'un brûleur à combustible liquide.
PCT/DE1996/001860 1995-09-29 1996-09-27 Ensemble ajutage pour combustible et procede de regulation du debit WO1997011782A2 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP96944567A EP0852516B1 (fr) 1995-09-29 1996-09-27 Ensemble ajutage pour combustible et procede de regulation du debit
JP51308497A JP3850881B2 (ja) 1995-09-29 1996-09-27 流体燃料バーナーの燃料ノズル装置、この燃料ノズル装置の使用方法並びに流体燃料バーナーの燃料供給調節方法
DE59609892T DE59609892D1 (de) 1995-09-29 1996-09-27 Brennstoffdüsenanordnung und verfahren zur durchflussregulierung
US09/050,650 US6092738A (en) 1995-09-29 1998-03-30 Fuel nozzle configuration for a fluid-fuel burner, oil burner using the fuel nozzle configuration and method for regulating the fuel supply of a fluid-fuel burner

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19536534 1995-09-29
DE19536534.8 1995-09-29

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US09/050,650 Continuation US6092738A (en) 1995-09-29 1998-03-30 Fuel nozzle configuration for a fluid-fuel burner, oil burner using the fuel nozzle configuration and method for regulating the fuel supply of a fluid-fuel burner

Publications (2)

Publication Number Publication Date
WO1997011782A2 true WO1997011782A2 (fr) 1997-04-03
WO1997011782A3 WO1997011782A3 (fr) 1997-08-14

Family

ID=7773718

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE1996/001860 WO1997011782A2 (fr) 1995-09-29 1996-09-27 Ensemble ajutage pour combustible et procede de regulation du debit

Country Status (5)

Country Link
EP (1) EP0852516B1 (fr)
JP (1) JP3850881B2 (fr)
DE (1) DE59609892D1 (fr)
RU (1) RU2160413C2 (fr)
WO (1) WO1997011782A2 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB649970A (en) * 1948-06-22 1951-02-07 Dowty Equipment Improvements in liquid-fuel burners
FR1025118A (fr) * 1949-09-10 1953-04-10 Babcock & Wilcox France Brûleur atomiseur pour combustibles liquides
US2721765A (en) * 1952-03-27 1955-10-25 Hobson Ltd H M Nozzles
GB819042A (en) * 1956-09-27 1959-08-26 Dowty Fuel Syst Ltd Improvements relating to liquid fuel burners
DE1138987B (de) * 1959-04-04 1962-10-31 Bosch Gmbh Robert Kraftstoffeinspritzduesen, insbesondere fuer Gasturbinen- und Strahltriebwerke
GB918411A (en) * 1958-03-13 1963-02-13 Babcock & Wilcox Ltd Improvements in or relating to liquid fuel burners
DE1179421B (de) * 1963-02-14 1964-10-08 Daimler Benz Ag Brennstoffeinspritzduese fuer Brennkammern von Gasturbinentriebwerken
FR2452667A1 (fr) * 1979-03-28 1980-10-24 Penke Herbert Dispositif de reglage de la pression dans un bruleur a mazout ou similaire
DE3235080A1 (de) * 1982-09-22 1984-03-22 Kraftwerk Union AG, 4330 Mülheim Ruecklaufeinspritzduese fuer die zerstaeubung von fluessigkeiten

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB649970A (en) * 1948-06-22 1951-02-07 Dowty Equipment Improvements in liquid-fuel burners
FR1025118A (fr) * 1949-09-10 1953-04-10 Babcock & Wilcox France Brûleur atomiseur pour combustibles liquides
US2721765A (en) * 1952-03-27 1955-10-25 Hobson Ltd H M Nozzles
GB819042A (en) * 1956-09-27 1959-08-26 Dowty Fuel Syst Ltd Improvements relating to liquid fuel burners
GB918411A (en) * 1958-03-13 1963-02-13 Babcock & Wilcox Ltd Improvements in or relating to liquid fuel burners
DE1138987B (de) * 1959-04-04 1962-10-31 Bosch Gmbh Robert Kraftstoffeinspritzduesen, insbesondere fuer Gasturbinen- und Strahltriebwerke
DE1179421B (de) * 1963-02-14 1964-10-08 Daimler Benz Ag Brennstoffeinspritzduese fuer Brennkammern von Gasturbinentriebwerken
FR2452667A1 (fr) * 1979-03-28 1980-10-24 Penke Herbert Dispositif de reglage de la pression dans un bruleur a mazout ou similaire
DE3235080A1 (de) * 1982-09-22 1984-03-22 Kraftwerk Union AG, 4330 Mülheim Ruecklaufeinspritzduese fuer die zerstaeubung von fluessigkeiten

Also Published As

Publication number Publication date
DE59609892D1 (de) 2003-01-02
WO1997011782A3 (fr) 1997-08-14
EP0852516B1 (fr) 2002-11-20
RU2160413C2 (ru) 2000-12-10
JPH11511547A (ja) 1999-10-05
JP3850881B2 (ja) 2006-11-29
EP0852516A1 (fr) 1998-07-15

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