EP0742411B1 - Alimentation en air pour une chambre de combustion à prémélange - Google Patents

Alimentation en air pour une chambre de combustion à prémélange Download PDF

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Publication number
EP0742411B1
EP0742411B1 EP96810258A EP96810258A EP0742411B1 EP 0742411 B1 EP0742411 B1 EP 0742411B1 EP 96810258 A EP96810258 A EP 96810258A EP 96810258 A EP96810258 A EP 96810258A EP 0742411 B1 EP0742411 B1 EP 0742411B1
Authority
EP
European Patent Office
Prior art keywords
burner
perforated
air
flow
component
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 - Lifetime
Application number
EP96810258A
Other languages
German (de)
English (en)
Other versions
EP0742411A3 (fr
EP0742411A2 (fr
Inventor
Tino-Martin Dr. Marling
Burkhard Dr. Schulte-Werning
Thomas Dr. Zierer
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.)
ABB AG Germany
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP0742411A2 publication Critical patent/EP0742411A2/fr
Publication of EP0742411A3 publication Critical patent/EP0742411A3/fr
Application granted granted Critical
Publication of EP0742411B1 publication Critical patent/EP0742411B1/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
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • 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
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • 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

Definitions

  • the invention relates to a premix burner with an axial or radial air inflow for gas turbine operation, in which the combustion air from a plenum into the burner flows and fuel is added to it on its way through the burner becomes.
  • premix burners are usually axial or radial flowed with the combustion air.
  • Double-cone design flows the combustion air from one of a plenum surrounded by a hood via tangential air inlet slots into the burner interior. Becomes gaseous fuel burned, the mixture formation occurs directly at the end of the Air inlet slots.
  • the nozzle becomes a cone-shaped inside the burner Liquid fuel column formed by a tangential enclosed combustion air stream flowing into the burner becomes. The mixture is ignited at the burner outlet, the flame passing through a backflow zone in the area the burner mouth is stabilized.
  • the invention tries to avoid all these disadvantages. you the task is based on a premix burner To create device for flow rectification with which the flow profile of the incoming combustion air evened out, the degree of turbulence increased and the air flow can be adapted to the burner, so that a homogeneous Mixing of air and fuel is achieved.
  • this is done in a premix burner with an axial or radial air inflow, in which the combustion air from one in the flow direction in front or one around the burner arranged plenum flows into the burner and you fuel is mixed in on the way through the burner, thereby achieved that between the plenum and the burner a perforated component with a certain wall thickness and Openings with a certain diameter and a certain Distance from each other, which is the flowing through Divides combustion air into small defined jets, that reunite after a certain run length, where the ratio of wall thickness to diameter the openings are greater than or equal to one, preferably 1.5 and where the ratio between the flow area of the perforated Component and the possible inflow area in the Burners also larger / equal depending on the type of burner is one.
  • the advantages of the invention include that a uniform speed profile after the perforated component with increased turbulence level as inflow for the burner is reached. This will mix the Improved and intensified fuel and combustion air, so that the emission values of CO and NOx are reduced.
  • the premix burners have a wider range of applications because they now operate well even under unfavorable inflow conditions can be.
  • the ratio of barrel length the distance between the openings is greater than or equal to 5.
  • Fig. 1a initially shows how the how a flow rectifier acting perforated component 24 with an ideal, uniform inflow of air 15, while in Fig. 1b the mode of operation of the perforated component 24 with a non-uniform inflow of air 15 is shown.
  • the component 24 with a wall thickness s has a number of Openings 25 each with a diameter d. These openings 25 are arranged at a constant distance t from one another. 1a and 1b is through the openings 25 of the component 24 flowing air 15 defined in small Beams split up according to a certain one Combine barrel length 1 behind the hole. It is the barrel length 1 depending on the distance t and the diameter d of the openings 25, and of the beam divergence. As in Fig. 1b can be clearly seen, takes place with a non-uniform Inflow the beam expansion before the perforated Component. After flowing through the wall it becomes uniform Speed profile with an increased small-scale Turbulence level achieved, leading to a favorable inflow leads for the burner, not shown in Fig. 1.
  • FIG. 1c shows a schematic representation of the speed profile of the inflowing air when the perforated component 24 flows at an angle.
  • its speed is composed of a vertical component v 1 and a horizontal component u 1 , whereby an angle ⁇ 1 is enclosed by the resultant and by v 1 .
  • the horizontal component u 2 and the angle ⁇ 2 are zero, so that only a vertical velocity component v 2 is present, where: v 1 ⁇ v 2 .
  • the perforated component 24 With regard to the design of the perforated component 24 a fixed area ratio between the flow area of the component and the inflow surface into the premix burner observed. The pressure loss across the perforated component 24 is determined by these two surfaces. As well may have a fixed ratio between the diameter d of the Openings 25 and the wall thickness s must not be undercut, because this ratio also determines the amount of pressure loss. It has been shown that the ratio s / d ⁇ 1 to 1.5 should be. The distance t is determined by these requirements of the openings 25 to each other, which in turn Flow profile behind the component 24 determines the ratio 1 / t ⁇ 5, because of the beam divergence then the individual rays have grown together again and the speed profile is very even.
  • FIG. 2 shows as an embodiment of the invention in Perspective view of a burner 18 of the double cone type with integrated premixing zone, its principal Structure is described in EP 0 321 809 B1.
  • FIG. 2 and the sections shown in FIG. 3 to 5 can be used.
  • the burner 18 consists of two partial cone bodies 1, 2, which relate their longitudinal symmetry axes 1b, 2b radially offset from one another are arranged. This creates on both sides the partial cone body 1, 2 in the opposite inflow arrangement each tangential air inlet slots 19, 20, through which the combustion air 15 in the interior 14 of the Burner 18, i.e. in the two conical bodies 1, 2 formed cone cavity flows. Expand the partial cone bodies 1, 2 straight in the direction of flow, i.e. they point a constant angle with the burner axis.
  • the two Partial cone bodies 1, 2 each have a cylindrical initial part 1a, 2a, which also run offset.
  • the two partial cone bodies 1, 2 have along the air inlet slots 19, 20 each have a fuel feed line 8, 9, which are provided on the long side with openings 17 through which another fuel 13 flows.
  • This gaseous Fuel 13 becomes the through the tangential air inlet slots 19, 20 combustion air flowing into the burner interior 14 15 admixed, which is represented by the arrows 16 becomes.
  • Mixed operation of the burner 18 via the nozzle 3 and the fuel feeds 8, 9 is possible.
  • this air supply ensures that flame stabilization takes place at the exit of the burner. There poses there is a stable flame front 7 with a backflow zone 6 on.
  • a front plate 10 with openings is arranged on the combustion chamber side 11, through which, if necessary, dilution air or cooling air are fed to the combustion chamber 22.
  • baffles 21 a, 21 b can be around a pivot point, for example 23 can be opened or closed, so that the original gap size of the tangential air inlet slots 19, 20 is changed.
  • the Burners can also be operated without these baffles 21a, 21b.
  • the burner 18 described above is one Hood 26 surround a plenum 27 for the burner incoming combustion air 15 forms.
  • the Combustion air 15 on the one hand together from the cooling air 15a, which has previously convectively cooled the walls of the combustion chamber 5, and on the other hand from the air 15b, which does not have a the bypass line shown also flows into the plenum 27, so that additional swirls arise.
  • the hood 26 there is therefore a very complex flow situation.
  • a perforated one Basket 24 placed around the radially flowed burner 18, which causes a flow rectification.
  • the basket 24 is an optimal flow of Brenners allows.
  • the flow of the burner is controlled by the Invention of the complex flow situation in the hood decoupled.
  • the area ratio between the flow area of the perforated Basket 24 and the inflow surface into the burner 18th (Air inlet slots 19, 20) is in the illustrated embodiment 4. This ensures that the pressure loss corresponds approximately to a dynamic pressure above the perforated basket. If the flow area, i.e. the area of the openings 25 in the basket 24 essential under otherwise constant conditions lower, there would be too high a pressure loss.
  • the ratio of wall thickness s to hole diameter d is greater / equal 1, preferably 1.5 must be with this Claim in addition to the above Area ratio the distance t the Openings 25 are fixed to each other, which in turn is the flow profile determined behind the perforated basket 24.
  • the common flow profile can thus be precisely defined and tailored to the respective burner needs become.
  • the advantage is that it is uneven Air distribution along the inflow length of the burner 18 both in the mass distribution as well as in the flow profile can be rectified.
  • the invention is not limited to that just described Embodiment limited. 9 is therefore another embodiment shown, the one axially flowed premix burner 18 relates.
  • the combustion air 15 flows here from the plenum 27 through the openings 25 one in front of the burner perpendicular to the direction of flow arranged perforated wall 24 which e.g. a perforated sheet can be in the burner 18.
  • the system becomes pilot fuel via a central feed 29 passed into the burner. Because the air flow is evened out by the wall 24 and also that small-scale turbulence level after the wall 24 is increased, can be a homogeneous mixture of fuel and combustion air take place, what to the above Advantages leads.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)

Claims (6)

  1. Brûleur à prémélange (18) avec alimentation axiale ou radiale en air, dans lequel l'air de combustion (15) pénètre dans le brûleur (18) en provenance d'un collecteur (27) disposé en amont du brûleur (18) dans la direction d'écoulement ou selon le cas autour de ce dernier, du combustible (12, 13) étant mélangé avec lui sur son parcours à travers le brûleur (18), caractérisé en ce qu'entre le collecteur (27) et le brûleur (18) est disposé un composant perforé (24) d'une épaisseur de paroi (s) et doté d'ouvertures (25) qui présentent chacune un diamètre (d) et un écart mutuel (t), lequel composant divise l'air de combustion (15) qui le traverse en petits jets définis qui se rejoignent de nouveau après une longueur d'avancement (1) définie, le rapport entre l'épaisseur (s) de la paroi et le diamètre (d) des ouvertures (25) étant supérieur ou égal à un et le rapport entre la surface de traversée du composant perforé (24) et la surface d'entrée possible dans le brûleur (18) étant supérieur ou égal à un, en fonction du type de brûleur.
  2. Brûleur à prémélange (18) à alimentation radiale en air selon la revendication 1, caractérisé en ce que le composant perforé (24) est un panier perforé disposé autour du brûleur (18).
  3. Brûleur à prémélange (18) à alimentation axiale en air selon la revendication 1, caractérisé en ce que le composant perforé (24) est une paroi perforée disposée en amont du brûleur (18) et perpendiculairement à la direction d'écoulement de l'air de combustion (15), de préférence une tôle perforée.
  4. Brûleur à prémélange (18) selon l'une quelconque des revendications 1 à 3, caractérisé en ce que le rapport entre la longueur d'avancement (1) et la distance (t) entre les ouvertures (25) est supérieur ou égal à 5.
  5. Brûleur à prémélange (18) selon l'une quelconque des revendications 1 à 3, caractérisé en ce que le rapport entre l'épaisseur (s) de la paroi et le diamètre (d) des ouvertures (25) est de 1,5.
  6. Brûleur à prémélange (18) selon la revendication 3, caractérisé en ce que le rapport entre la surface de traversée de la paroi perforée (24) et la surface d'entrée dans le brûleur (18) est égal à un.
EP96810258A 1995-05-08 1996-04-23 Alimentation en air pour une chambre de combustion à prémélange Expired - Lifetime EP0742411B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19516798 1995-05-08
DE19516798A DE19516798A1 (de) 1995-05-08 1995-05-08 Vormischbrenner mit axialer oder radialer Luftzuströmung

Publications (3)

Publication Number Publication Date
EP0742411A2 EP0742411A2 (fr) 1996-11-13
EP0742411A3 EP0742411A3 (fr) 1999-04-14
EP0742411B1 true EP0742411B1 (fr) 2003-05-28

Family

ID=7761333

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810258A Expired - Lifetime EP0742411B1 (fr) 1995-05-08 1996-04-23 Alimentation en air pour une chambre de combustion à prémélange

Country Status (5)

Country Link
US (1) US5738509A (fr)
EP (1) EP0742411B1 (fr)
JP (1) JPH08303776A (fr)
CN (1) CN1158958A (fr)
DE (2) DE19516798A1 (fr)

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19720786A1 (de) 1997-05-17 1998-11-19 Abb Research Ltd Brennkammer
DE19737998A1 (de) * 1997-08-30 1999-03-04 Abb Research Ltd Brennervorrichtung
US6176087B1 (en) * 1997-12-15 2001-01-23 United Technologies Corporation Bluff body premixing fuel injector and method for premixing fuel and air
DE19817995C1 (de) * 1998-04-22 1999-09-09 Stoeckert Instr Gmbh Vorrichtung zur Überwachung des Füllstands eines Blutreservoirs
DE59808762D1 (de) * 1998-08-27 2003-07-24 Alstom Switzerland Ltd Brenneranordnung für eine Gasturbine
AU2003238524A1 (en) * 2002-05-16 2003-12-02 Alstom Technology Ltd Premix burner
EP1601913A1 (fr) * 2003-03-07 2005-12-07 Alstom Technology Ltd Bruleur de premelange
WO2006094939A1 (fr) * 2005-03-09 2006-09-14 Alstom Technology Ltd Bruleur a premelange pour une chambre de combustion
US8627775B1 (en) 2010-03-02 2014-01-14 David L. Wilson Burning apparatus for a solid wood-fueled process heating system
CH703655A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Vormischbrenner für eine gasturbine.
EP2685160B1 (fr) * 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
EP2685161B1 (fr) * 2012-07-10 2018-01-17 Ansaldo Energia Switzerland AG Agencement de chambre de combustion, en particulier pour turbine à gaz
CN110388643A (zh) * 2019-07-26 2019-10-29 合肥工业大学 富氢燃料气低污染燃烧的燃气空气预混器

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1401835B2 (de) * 1962-11-16 1970-02-19 Dr. Schmitz & Apelt, Industrieofenbau GmbH, 5600 Wuppertal-Langerfeld Zweistoffbrenner
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus
US3905192A (en) * 1974-08-29 1975-09-16 United Aircraft Corp Combustor having staged premixing tubes
GB1552132A (en) * 1975-11-29 1979-09-12 Rolls Royce Combustion chambers for gas turbine engines
JPS548139U (fr) * 1977-06-20 1979-01-19
GB2119077B (en) * 1982-04-22 1985-08-14 Rolls Royce Fuel injector for gas turbine engines
CH659864A5 (de) * 1982-06-23 1987-02-27 Bbc Brown Boveri & Cie Lochplatte zur vergleichmaessigung der geschwindigkeitsverteilung in einem stroemungskanal.
JPS62204128U (fr) * 1986-06-12 1987-12-26
JPS6349608A (ja) * 1986-08-20 1988-03-02 Toa Nenryo Kogyo Kk 超音波霧化装置付燃焼器
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
GB9106085D0 (en) * 1991-03-22 1991-05-08 Rolls Royce Plc Gas turbine engine combustor
GB9112324D0 (en) * 1991-06-07 1991-07-24 Rolls Royce Plc Gas turbine engine combustor
EP0518072A1 (fr) * 1991-06-14 1992-12-16 Asea Brown Boveri Ag Brûleur pour un moteur à combustion interne, une chambre de combustion d'une installation pour turbine à gaz ou un foyer

Also Published As

Publication number Publication date
JPH08303776A (ja) 1996-11-22
EP0742411A3 (fr) 1999-04-14
US5738509A (en) 1998-04-14
DE59610467D1 (de) 2003-07-03
EP0742411A2 (fr) 1996-11-13
DE19516798A1 (de) 1996-11-14
CN1158958A (zh) 1997-09-10

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