EP0742411A2 - 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
EP0742411A2
EP0742411A2 EP96810258A EP96810258A EP0742411A2 EP 0742411 A2 EP0742411 A2 EP 0742411A2 EP 96810258 A EP96810258 A EP 96810258A EP 96810258 A EP96810258 A EP 96810258A EP 0742411 A2 EP0742411 A2 EP 0742411A2
Authority
EP
European Patent Office
Prior art keywords
burner
air
perforated
flow
ratio
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
EP96810258A
Other languages
German (de)
English (en)
Other versions
EP0742411A3 (fr
EP0742411B1 (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
ABB Management 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 ABB Management AG filed Critical ABB Management 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 axial or radial air inflow for gas turbine operation, in which the combustion air flows from a plenum into the burner and fuel is added to it on the way through the burner.
  • premix burners For reasons of environmental protection, modern burner systems, which are used in gas turbine plants, are designed as premix burners because they significantly reduce pollutant emissions compared to diffusion burners.
  • the premix burners are generally flowed axially or radially with the combustion air.
  • the combustion air flows from a plenum surrounded by a hood into the burner interior via tangential air inlet slots. If gaseous fuel is burned, the mixture is formed directly at the end of the air inlet slots.
  • liquid fuel is injected through a nozzle located centrally in the initial part of the burner, a conical liquid fuel column is formed in the interior of the burner and is enclosed by a combustion air stream flowing tangentially into the burner. The mixture is ignited at the burner outlet, the flame being stabilized by a backflow zone in the area of the burner mouth.
  • the invention tries to avoid all these disadvantages. It is the object of the invention to provide a device for rectifying the flow in a premix burner, with which the flow profile of the incoming combustion air is evened out, the degree of turbulence is increased and the air flow can be adapted to the burner so that a homogeneous mixing of air and fuel is achieved.
  • this is achieved in a premix burner with axial or radial air inflow, in which the combustion air flows into the burner from a plenum arranged upstream or around the burner and fuel is mixed in on the way through the burner, in that between the plenum and the burner are arranged a perforated component with a certain wall thickness and openings with a certain diameter and a certain distance from each other, which divides the combustion air flowing through into small defined jets, which reunite after a certain length, the ratio of wall thickness to the diameter of the openings is greater than / equal to one, preferably 1.5, and the ratio between the flow area of the perforated component and the possible inflow area into the burner is also greater / equal to one depending on the type of burner.
  • the advantages of the invention include that, after the perforated component, a uniform speed profile with an increased level of turbulence is achieved as an inflow for the burner. This improves and intensifies the mixture of fuel and combustion air, so that the emissions of CO and NOx are reduced.
  • the premix burners have a wider range of applications because they can now be operated well even under unfavorable inflow conditions.
  • the perforated component is a perforated basket arranged around the burner and, in the case of a burner with axial air inflow, a wall arranged in front of the burner perpendicular to the direction of flow of the combustion air.
  • the ratio of the barrel length to the distance between the openings is greater than or equal to 5.
  • the ratio between the flow area of the perforated wall and the inflow area into the burner is equal to one in the case of an axially flowing premix burner.
  • the ratio between the through-flow area of the perforated basket and the inflow area into the burner is greater than one, preferably four is. This ensures that an uneven air distribution along the inflow length of the burner can be rectified both in the mass distribution and in the flow profile.
  • the fuel design along the air inlet slot can be optimally designed, so that the mixture of fuel and air is improved and the NOx values during combustion are reduced.
  • FIG. 1a initially shows in general the mode of operation of the perforated component 24 acting as a flow straightener with an ideal, uniform inflow of air 15, while in FIG. 1b the mode of operation of the perforated component 24 is shown with a non-uniform inflow of air 15.
  • 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.
  • the air 15 flowing through the openings 25 of the component 24 is divided into small, defined jets which unite behind the bore after a certain run length 1.
  • the barrel length 1 is dependent on the distance t and the diameter d of the openings 25 and on the beam divergence.
  • FIG. 1b in the case of a non-uniform inflow, the beam is expanded before the perforated component. After flowing through the wall, a uniform speed profile with an increased small-scale turbulence level is achieved, which leads to a favorable inflow for the burner (not shown in FIG. 1).
  • a constant exit angle of the flow from the basket can be predetermined and thus adapted to the burner.
  • 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 area into the premix burner must be maintained. The pressure loss across the perforated component 24 is determined by these two surfaces. Likewise, 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 level of the pressure loss. It has been shown that the ratio should be d / s ⁇ 1..1.5. These requirements determine the distance t of the openings 25 from one another, which in turn determines the flow profile behind the component 24, since the ratio should be 1 / t ⁇ 5, because due to the beam divergence, the individual beams then grow together again and the speed profile is very high evenly.
  • FIG. 2 shows, as an exemplary embodiment of the invention, a perspective view of a burner 18 of the double-cone type with an integrated premixing zone, the basic structure of which is described in EP 0 321 908 B1.
  • FIG. 2 and the sections shown in FIGS. 3 to 5 are used at the same time.
  • the burner 18 consists of two partial cone bodies 1, 2 which are arranged radially offset from one another with respect to their longitudinal symmetry axes 1b, 2b. This creates tangential air inlet slots 19, 20 on both sides of the partial cone bodies 1, 2 in the opposite inflow arrangement, through which the combustion air 15 into the interior 14 of the Burner 18, ie flows in the cone cavity formed by the two partial cone bodies 1, 2.
  • the partial cone bodies 1, 2 expand in a straight line in the direction of flow; ie they have a constant angle with the burner axis.
  • the two partial cone bodies 1, 2 each have a cylindrical initial part 1 a, 2 a, which likewise run offset.
  • this cylindrical starting part 1a, 2a there is an atomizing nozzle 3, the openings of which are arranged approximately in the narrowest cross section of the conical interior 14 of the burner 18.
  • the burner 18 can of course also be designed without a cylindrical initial part, that is to say purely conical.
  • Liquid fuel 12 is injected through the nozzle 3, so that a drop spray 4 is formed in the interior 14 of the burner 18.
  • the two partial cone bodies 1, 2 each have a fuel feed line 8, 9 along the air inlet slots 19, 20, which are provided on the long side with openings 17 through which a further fuel 13 flows.
  • This gaseous fuel 13 is mixed with the combustion air 15 flowing through the tangential air inlet slots 19, 20 into the burner interior 14, which is represented by the arrows 16.
  • a 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 burner outlet. There is a stable flame front 7 with a backflow zone 6.
  • a front plate 10 is arranged with openings 11, through which dilution air or cooling air can be supplied to the combustion chamber 22 if necessary.
  • guide plates 21 a, 21 b can be seen from FIGS. 3 to 5. These can be opened or closed, for example, about a pivot point 23, so that the original gap size of the tangential air inlet slots 19, 20 is changed. Of course, the burner can also be operated without these baffles 21a, 21b.
  • the burner 18 described above is surrounded by a hood 26 which forms a plenum 27 for the combustion air 15 flowing to the burner.
  • the combustion air 15 is composed on the one hand of the cooling air 15a, which has previously convectively cooled the walls of the combustion chamber 5, and on the other hand of the air 15b, which also flows into the plenum 27 via a bypass line, not shown, so that additional swirls occur. Accordingly, there is a very complex flow situation in the hood 26.
  • a perforated basket 24 is placed around the radially flowed burner 18, which causes a flow rectification.
  • An optimal flow to the burner is made possible by adapting the contour of the basket 24.
  • the flow of the burner is decoupled from the complex flow situation in the hood by the invention.
  • the area ratio between the throughflow area of the perforated basket 24 and the inflow area into the burner 18 (air inlet slots 19, 20) is 4 in the exemplary embodiment shown. This ensures that the pressure loss across the perforated basket corresponds approximately to a dynamic pressure.
  • the flow area ie the area of the openings 25 in the basket 24 under otherwise constant conditions would be significantly lower, an excessive pressure loss would result.
  • the ratio of wall thickness s to hole diameter d must be greater than or equal to 1, preferably 1.5, this requirement is in addition to the above.
  • Area ratio of the distance t of the openings 25 to each other is determined, which in turn determines the flow profile behind the perforated basket 24.
  • the air 15 is divided into small defined jets when flowing through the basket 24, which rejoin after the run length 1 behind the opening 25.
  • the common flow profile can thus be precisely defined and tailored to the respective burner needs.
  • the advantage is that an uneven air distribution along the inflow length of the burner 18 can be rectified both in the mass distribution and in the flow profile.
  • the fuel design along the air inlet in the burner 18 can be optimally designed, which, in addition to increasing the turbulence of the air, improves the mixture of fuel and combustion air and thus reduces the pollutant emissions.
  • the burner can therefore also be used under unfavorable flow conditions.
  • an optimal local flow to the burner is also possible.
  • FIG. 9 A further exemplary embodiment is therefore shown in FIG. 9, which relates to an axially flowing premix burner 18.
  • the combustion air 15 flows here from the plenum 27 through the openings 25 of a perforated wall 24 arranged in front of the burner perpendicular to the flow direction, which can be, for example, a perforated plate, into the burner 18.
  • Pilot fuel is supplied via a central feed to stabilize the system 29 passed into the burner. Since the air flow through the wall 24 is evened out and the small-scale turbulence level after the wall 24 is also increased, the fuel and combustion air can be mixed homogeneously, which leads to the advantages mentioned above.

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)
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 true EP0742411A2 (fr) 1996-11-13
EP0742411A3 EP0742411A3 (fr) 1999-04-14
EP0742411B1 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)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0899506A3 (fr) * 1997-08-30 1999-06-16 Abb Research Ltd. Dispositif de combustion
EP0982544A1 (fr) * 1998-08-27 2000-03-01 Asea Brown Boveri AG Brûleur pour une turbine à gaz
WO2004079264A1 (fr) * 2003-03-07 2004-09-16 Alstom Technology Ltd Bruleur de premelange

Families Citing this family (10)

* 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
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
AU2003238524A1 (en) * 2002-05-16 2003-12-02 Alstom Technology Ltd Premix burner
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

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus
DE1401835A1 (de) * 1962-11-16 1968-10-24 Schmitz & Apelt Industrieofenb Zweistoffbrenner
US4559275A (en) * 1982-06-23 1985-12-17 Bbc Brown, Boveri & Company, Limited Perforated plate for evening out the velocity distribution
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

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
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

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1401835A1 (de) * 1962-11-16 1968-10-24 Schmitz & Apelt Industrieofenb Zweistoffbrenner
US3169367A (en) * 1963-07-18 1965-02-16 Westinghouse Electric Corp Combustion apparatus
US4559275A (en) * 1982-06-23 1985-12-17 Bbc Brown, Boveri & Company, Limited Perforated plate for evening out the velocity distribution
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

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0899506A3 (fr) * 1997-08-30 1999-06-16 Abb Research Ltd. Dispositif de combustion
EP0982544A1 (fr) * 1998-08-27 2000-03-01 Asea Brown Boveri AG Brûleur pour une turbine à gaz
US6209327B1 (en) 1998-08-27 2001-04-03 Asea Brown Boveri Ag Burner arrangement for a gas turbine including an inlet-air impingement plate
WO2004079264A1 (fr) * 2003-03-07 2004-09-16 Alstom Technology Ltd Bruleur de premelange
US7424804B2 (en) 2003-03-07 2008-09-16 Alstom Technology Ltd Premix burner

Also Published As

Publication number Publication date
JPH08303776A (ja) 1996-11-22
EP0742411A3 (fr) 1999-04-14
EP0742411B1 (fr) 2003-05-28
US5738509A (en) 1998-04-14
DE59610467D1 (de) 2003-07-03
DE19516798A1 (de) 1996-11-14
CN1158958A (zh) 1997-09-10

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