EP0769655A2 - Buse de pulvérisation par air comprimé - Google Patents

Buse de pulvérisation par air comprimé Download PDF

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Publication number
EP0769655A2
EP0769655A2 EP96810646A EP96810646A EP0769655A2 EP 0769655 A2 EP0769655 A2 EP 0769655A2 EP 96810646 A EP96810646 A EP 96810646A EP 96810646 A EP96810646 A EP 96810646A EP 0769655 A2 EP0769655 A2 EP 0769655A2
Authority
EP
European Patent Office
Prior art keywords
nozzle
atomizer
airblast
burner
liquid fuel
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
EP96810646A
Other languages
German (de)
English (en)
Other versions
EP0769655B1 (fr
EP0769655A3 (fr
Inventor
Franz Joos
Marcel Stalder
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.)
General Electric Switzerland GmbH
Original Assignee
ABB Asea Brown Boveri Ltd
Alstom SA
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Alstom SA, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0769655A2 publication Critical patent/EP0769655A2/fr
Publication of EP0769655A3 publication Critical patent/EP0769655A3/fr
Application granted granted Critical
Publication of EP0769655B1 publication Critical patent/EP0769655B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23D11/005—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means
    • F23D11/007—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising means combination of means covered by sub-groups F23D11/10 and F23D11/24
    • 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
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • 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
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • the invention relates to the field of combustion technology. It relates to an atomizer nozzle for atomizing liquid fuel in a burner, which works on the air-blast principle, is suitable both for operating the burner with liquid and gaseous fuels and can be used in particular in low-pollutant premix burners of the double-cone type.
  • the fuel For low pollutant premix combustion, the fuel must be mixed with the combustion air as homogeneously as possible before combustion. If liquid fuel is used, it must be atomized beforehand. The liquid fuel jet is split into individual droplets so that the fuel has the largest possible evaporation surface.
  • So-called airblast atomizers are also used to atomize liquid fuels in combustion chambers (see AH Lefebvre, Airblast Atomization, Prog. Energy Combust. Sci. Vol. 6, pp. 233-261, 1980), which are particularly useful for operation of gas turbines are suitable.
  • This are designed so that the relatively slow moving liquid fuel is atomized by a high speed air stream.
  • the fuel does not have its own impulse.
  • the liquid to be atomized is applied, for example, as a thin film with an approximately constant thickness to an atomizer edge. An air flow flows around this atomizer edge on both sides, ie an outer and an inner air flow, the atomization of the liquid fuel then taking place at the atomizer lip in the shear field of the two air flows (prefilming atomization).
  • the liquid fuel is applied either via central pressure atomizers or via so-called film layers, which are integrated in the lead of the atomizer edge in this component and therefore require a relatively thick component.
  • the internal air flow is either swirled and / or directed outwards via a central body.
  • a disadvantage of this known prior art is the relatively large component diameter or the high pressure drop in the nozzle due to the narrow cross section.
  • the twist of the internal air flow makes the nozzle diameter relatively large.
  • the airblast atomizer is designed with a displacement body.
  • the disadvantage of this displacement body is that it causes an increased susceptibility to coke and gum formation in the wake. Due to the proximity to the flame, the cooling of this part is usually a difficult problem to solve.
  • the invention tries to avoid all these disadvantages. It is based on the task of developing an airblast nozzle for atomizing liquid fuel, which can also be used for gas operation and is characterized by small dimensions and is therefore, for example, well suited for use in a premixing burner of the double-cone type, the nozzle being characterized by reduced susceptibility to coking and gum formation. Furthermore, there should only be a slight loss of pressure in the nozzle. Finally, it is the object of the invention to propose a mechanism with which it is possible to throttle off the atomizing air during gas operation and to meter the required atomizing air during operation with liquid fuel.
  • an airblast nozzle according to the preamble of claim 1 in that the intermediate wall between the inner and outer air duct is held via inner and outer support elements, the inner support elements between the intermediate wall and the fuel pipe and the outer support elements between the intermediate wall and the nozzle outer body are arranged, and that the atomizer edges are angled in the direction of the nozzle axis.
  • the advantages of the invention consist in the compact design of the airblast nozzle and its minimal diameter, so that they can be used particularly well in a premix burner of the double-cone type. Another advantage results from the fact that there is no longer any need to arrange components at the nozzle outlet that tend to build up or overheat. In addition, there is only a slight pressure loss in the nozzle and the design pressure drop is at the atomizer lip.
  • the fuel is advantageously applied via commercially available pressure atomizers, in particular hollow-cone atomizers.
  • Simple bores which are provided radially or obliquely at the closed end of the fuel line, are also suitable for applying the fuel. It is advantageous here if the fuel film is evened out by means of weirs additionally arranged in the atomizer edge.
  • the inner and / or outer support elements are designed as swirl blades. By swirling the air, better atomization is achieved.
  • the swirl of the inner air flow serves to improve the flow around the atomizing lip, while the outer swirl influences the spray angle a.
  • the fuel application can also be swirled (radially or obliquely against the nozzle axis).
  • FIG. 1 shows a schematic representation of the arrangement of a premix burner of the double-cone type equipped with an airblast nozzle.
  • An airblast nozzle 2 is arranged in the upstream end of the burner 1. It is supplied with liquid fuel 4 and compressed air 5, which is used to atomize the fuel 4, via a fuel lance 3 connected to the double-cone burner 1.
  • the fuel lance 3 supplies the gaseous fuel 6 for the double-cone burner 1 while it receives its main burner air 7 from the space inside the burner hood 8.
  • the air 5 for the airblast nozzle 2 can also be supplied from a plenum (not shown) located outside the burner hood 8.
  • additional gaseous fuel pilot gas 9 is injected into the burner 1 in order to enrich the fuel gases near the axis of the double-cone burner 1 via the fuel lance 3.
  • the burner 1 opens into the combustion chamber 10 downstream.
  • FIG. 2 shows the airblast nozzle 2 in an enlarged partial longitudinal section. It has a fuel pipe 12 for the liquid fuel 4 arranged around the nozzle axis 11 and in each case an inner 13 and an outer air duct 14 arranged concentrically therewith.
  • the two air channels 13, 14 are upstream with an air supply line 15 in which the Atomizing air 5 is led to the nozzle, connected and opening at the atomizing cross section 16 into the burner interior 17.
  • the channels 13, 14 are through an intermediate wall 18, which according to the invention is angled at its downstream end in the direction of the nozzle axis 11 and there the atomizing edge 19 with the atomizing lip 20 forms, separated from each other, so that the atomizing air 5 is divided into an outer 5a and an inner airflow 5b.
  • the intermediate wall 18, including the atomizer edge 19, is held between the fuel tube 12 and the outer nozzle body 23 with the aid of inner and outer support elements 21, which are preferably arranged at uniform intervals over the circumference.
  • the inner support elements 21 are arranged between the fuel pipe 12 and the intermediate wall 18, while the outer support elements 21 are arranged between the intermediate wall 18 and the nozzle outer body 23.
  • a pilot gas channel 22 is provided in the burner 1, which provides pilot gas 9, which serves to enrich the gaseous fuel 6 in the interior of the burner, thereby expanding the stability range of the burner.
  • the pilot gas channel 22 is delimited by the outer nozzle body 23 and by the wall of the burner 1.
  • the connection of the nozzle 2 to the burner 1 and the feed of the pilot gas channel 22 are not shown in FIG. 2.
  • the latter can be implemented, for example, by a feed bore for the pilot gas which is arranged in the burner wall and is not shown here.
  • the nozzle 2 can be connected, for example, via a cover, not shown, which is welded over the entire circumference at the upstream end of the pilot gas channel 22 to the outer nozzle body 23 and on the wall of the burner 1 and closes off the pilot gas channel 22.
  • a pilot gas channel can also be dispensed with in other exemplary embodiments.
  • the liquid fuel 4, preferably oil, is made thinner by means of an exchangeable, commercially available pressure atomizer 24 Film applied to the atomizer edge 19.
  • Hollow-cone atomizers are optimal, but full-cone atomizers with a well atomized fuel core can also be used.
  • the atomizer edges 19 are narrowed inward in order to obtain a maximum air velocity in the atomization cross section 16 or at the atomizer lip 20.
  • the outer air flow 5a brought up in the outer air duct 14 is likewise brought to the atomizer lip 20 via a narrowing at the atomizer edge 19, where the fuel film is atomized finely by the shear forces of the two air streams 5a, 5b.
  • the high air speed has a positive effect on improved atomization quality.
  • the spray angle ⁇ can be influenced by the division of the two air mass flows 5a, 5b and by the geometry of the outlet cross section.
  • the inner support elements 21 are not firmly connected to the intermediate wall 18 in the upper part of the figure, so that a sliding point 28 is present at this point.
  • This enables the liquid fuel tube 12 including the oil pressure atomizer 24 to be displaced, so that the thermal expansion of the fuel lance 3 can be absorbed and the position of the atomizer edge 19 relative to the double-cone burner 1 does not change, which is a great advantage.
  • this version also saves a problematic seal between the pilot gas channel 22 and the atomizer in the burner 1, since the outer atomizer part would become part of the burner 1.
  • Another advantage is that the sensitive atomizer part remains in the double-cone burner 1 during assembly of the fuel lance 3 and is therefore not damaged.
  • FIG 3 shows an embodiment variant in which the liquid fuel 4 is applied to the atomizer edge 19 via simple bores 25. These are arranged radially or obliquely at the closed end of the liquid fuel line 12. For the purpose of uniformizing the fuel film and thereby improving the atomization quality, weirs 26 can be arranged in the atomization edge.
  • FIG. 4 Another embodiment variant is shown in FIG. 4.
  • the support elements 21 are designed as swirl blades 27. It is possible to arrange only the inner support elements 21 as swirl blades, so that only the inner air flow 5b is swirled in order to achieve a better flow around the atomizer lip 20. If only the outer air flow 5a is swirled, the spray angle ⁇ can be influenced. Of course, as can be seen from FIG. 4, both air streams 5a, 5b can also be swirled by designing both the inner and the outer support elements 21 as swirl generators.
  • FIG. 7 which uses the different thermal expansion of the fuel line 12 in oil and gas operation.
  • the upper part of Fig. 7 relates to gas operation, the lower part, however, to oil operation. 7, the airblast nozzle 2 is at the downstream end of the oil line 12 not shown.
  • the atomizing air 5 is throttled, since the oil line 12 is heated by the air coming from the compressor and accordingly the entry area of the atomizing air 5 into the burner part is reduced or completely closed by the thermal expansion of the oil line.
  • the required atomizing air 5 is metered during oil operation or when water is added due to the lower thermal expansion of the colder oil line 12 under these operating conditions (see open entry area of air 5 in the lower part of FIG. 7).
  • the prerequisite for this is that the liquid fuel line 12 is fixedly attached to the housing and the burner 1 is arranged firmly on the combustion chamber 10, which is not shown in FIG. 7.
  • throttling mechanisms such as throttling the air 5 by displacement by means of pilot gas 9, can also be used to throttle the atomizing air 5 of the airblast nozzle according to the invention in gas operation.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Spray-Type Burners (AREA)
EP96810646A 1995-10-21 1996-09-30 Buse de pulvérisation par air comprimé Expired - Lifetime EP0769655B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19539246A DE19539246A1 (de) 1995-10-21 1995-10-21 Airblast-Zerstäuberdüse
DE19539246 1995-10-21

Publications (3)

Publication Number Publication Date
EP0769655A2 true EP0769655A2 (fr) 1997-04-23
EP0769655A3 EP0769655A3 (fr) 1999-01-20
EP0769655B1 EP0769655B1 (fr) 2003-04-09

Family

ID=7775446

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810646A Expired - Lifetime EP0769655B1 (fr) 1995-10-21 1996-09-30 Buse de pulvérisation par air comprimé

Country Status (5)

Country Link
US (1) US5782626A (fr)
EP (1) EP0769655B1 (fr)
JP (1) JP3810491B2 (fr)
CN (1) CN1126909C (fr)
DE (2) DE19539246A1 (fr)

Cited By (2)

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Publication number Priority date Publication date Assignee Title
WO2010054798A1 (fr) 2008-11-11 2010-05-20 Dieter Wurz Buse à deux composants, groupe de buses et procédés de pulvérisation de fluides
DE102022105076A1 (de) 2022-03-03 2023-09-07 Deutsches Zentrum für Luft- und Raumfahrt e.V. Zufuhreinrichtung, Brennersystem und Verfahren

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RU2661993C1 (ru) 2015-03-31 2018-07-23 Мицубиси Хитачи Пауэр Системз, Лтд. Горелка для сжигания и котел, оснащенный такой горелкой для сжигания
JP6642912B2 (ja) 2015-09-11 2020-02-12 三菱日立パワーシステムズ株式会社 燃焼バーナ及びこれを備えたボイラ
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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010054798A1 (fr) 2008-11-11 2010-05-20 Dieter Wurz Buse à deux composants, groupe de buses et procédés de pulvérisation de fluides
CN102272524A (zh) * 2008-11-11 2011-12-07 迪特尔·沃尔兹 双组分喷嘴、集束喷嘴以及用于使流体雾化的方法
US8590812B2 (en) 2008-11-11 2013-11-26 Dieter Wurz Two-substance nozzle, cluster nozzle and method for the atomization of fluids
CN102272524B (zh) * 2008-11-11 2014-03-26 迪特尔·沃尔兹 双组分喷嘴、集束喷嘴以及用于使流体雾化的方法
RU2511808C2 (ru) * 2008-11-11 2014-04-10 Дитер ВУРЦ Двухкомпонентная форсунка и способ распыления текучих сред посредством такой форсунки
DE102022105076A1 (de) 2022-03-03 2023-09-07 Deutsches Zentrum für Luft- und Raumfahrt e.V. Zufuhreinrichtung, Brennersystem und Verfahren
WO2023166126A1 (fr) 2022-03-03 2023-09-07 Deutsches Zentrum für Luft- und Raumfahrt e.V. Dispositif d'alimentation, système de brûleur et procédé

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JP3810491B2 (ja) 2006-08-16
CN1156804A (zh) 1997-08-13
EP0769655B1 (fr) 2003-04-09
EP0769655A3 (fr) 1999-01-20
US5782626A (en) 1998-07-21
JPH09133326A (ja) 1997-05-20
DE19539246A1 (de) 1997-04-24
CN1126909C (zh) 2003-11-05
DE59610329D1 (de) 2003-05-15

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