EP0789187A2 - Procédé et dispositif pour la combustion des combustibles - Google Patents

Procédé et dispositif pour la combustion des combustibles Download PDF

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Publication number
EP0789187A2
EP0789187A2 EP96810567A EP96810567A EP0789187A2 EP 0789187 A2 EP0789187 A2 EP 0789187A2 EP 96810567 A EP96810567 A EP 96810567A EP 96810567 A EP96810567 A EP 96810567A EP 0789187 A2 EP0789187 A2 EP 0789187A2
Authority
EP
European Patent Office
Prior art keywords
area
delta
region
vortex generator
swirl
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
EP96810567A
Other languages
German (de)
English (en)
Other versions
EP0789187A3 (fr
EP0789187B1 (fr
Inventor
Jürgen Dr. Haumann
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.)
Alstom SA
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Publication of EP0789187A2 publication Critical patent/EP0789187A2/fr
Publication of EP0789187A3 publication Critical patent/EP0789187A3/fr
Application granted granted Critical
Publication of EP0789187B1 publication Critical patent/EP0789187B1/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
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • 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
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/40—Mixing tubes or chambers; Burner heads
    • F23D11/402—Mixing chambers downstream of the nozzle
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability

Definitions

  • the invention relates to a method and a device for the combustion of fuels in a main flow from combustion air.
  • Such methods and apparatus are known, for example, from EP-B1-0 321 809.
  • the air is set in rotation by the premix burner designed as a swirl burner, which essentially consists of two conical half-shells.
  • the fuel is blown into the rotating air and mixed there with it.
  • At the burner outlet there is a defined dome-shaped recirculation zone, at the top of which the ignition takes place.
  • the flame itself is stabilized by the recirculation zone in front of the burner without the need for a mechanical flame holder.
  • the thermoacoustic behavior of such burners is stable and they are characterized by a simple and inexpensive construction.
  • the invention is based on the object of improving the combustion and reducing the exhaust gas emission in a method and a device for the combustion of fuels in a main flow from combustion air of the type mentioned at the outset.
  • this is achieved in that the combustion air is conducted in a duct via at least one delta-shaped body, the delta-shaped body consisting of at least one essentially triangular vortex generator area and a trapezoidal flame stabilization area located downstream that in the region of the vortex generator Range fuel is introduced into the swirled combustion air that the vortex generator area is adjusted by means of a half arrow angle and an angle of attack relative to the main flow so that the swirl of the longitudinal vortices induced in the main flow is smaller than the critical swirl to create a recirculation zone that the Flame stabilization area is adjusted by means of a half arrow angle and an angle of incidence in relation to the flow so that the Swirl of the longitudinal vortices induced in the flow is greater than the critical swirl for creating a recirculation zone, which creates a pair of dome-shaped recirculation zones for each delta-shaped body and that the ignited combustion air / fuel mixture is stabilized by the recirculation zones.
  • a device for carrying out the method is characterized in that a plurality of delta-shaped bodies are arranged in a channel and consist of at least one essentially triangular vortex generator region and a subsequent trapezoidal flame stabilization region located downstream.
  • the advantages of the invention can be seen, inter alia, in that the various functions, such as premixing and flame stabilization, are spatially divided accordingly by the method and the device. This allows the individual functions to be optimized.
  • the delta-shaped body creates small-scale eddy currents, which means that a very compact design can be achieved. Because of the short mixing and residence times required, this leads to low costs and low emissions, especially nitrogen oxides and carbon monoxide.
  • the structure of a delta-shaped body is also very simple, which further reduces the costs.
  • the mixture of combustion air and fuel is also almost perfect and can be achieved with minimal pressure drops.
  • By forming a pair of counter-rotating recirculation zones per delta-shaped body the recirculation zones stabilize each other. This minimizes the risk of the flame striking back into the burner and damaging it.
  • a further trapezoidal area is arranged between the vortex generator area and the flame stabilization area, which serves as a further mixing and evaporation area. This allows the mixture of combustion air and fuel to be further homogenized.
  • the delta-shaped body 40 consists of three flat areas 1, 2 and 3, which have the shape of delta wings and is symmetrical with respect to an axis of symmetry 9.
  • the delta-shaped body 40 is made from a heat-resistant material, for example from heat-resistant steel sheet, in accordance with the temperatures occurring.
  • the first area 1 serves as a vortex generator and as a mixing section and is designed as an equilateral triangle with two side edges 30 and a connecting edge 31.
  • a tip 36 is formed by the two side edges 30.
  • This tip 36 can of course also be designed as a front edge, in which case the first region 1 would be designed as a trapezoid.
  • This vortex generator 1 is defined by means of a half arrow angle ⁇ 1 and by means of an angle of attack ⁇ 1.
  • the second area 2 serves as a further mixing and evaporation section. It is designed as an equilateral trapezoid with equally long side edges 32 and connecting edges 31 and 33 and is connected to the area 1 by means of the connecting edge 31.
  • the mixing section 2 is defined by means of a half arrow angle ⁇ 2 and by means of an angle of attack ⁇ 2.
  • the third area 3 is used for flame stabilization. It is also designed as an equilateral trapezoid with side edges 34 of equal length, the connecting edge 33 and an edge 35 and is connected to the region 2 by means of the connecting edge 33.
  • the area 3 is defined by a half arrow angle ⁇ 3 and by an angle of attack ⁇ 3.
  • the transitions between the areas 1, 2 and 3, at the connecting edges 31 and 33 can also be made continuously or with jumps. It is essential that the properties of the areas are set by the sweep angle ⁇ i and by an angle of attack ⁇ I.
  • a fuel nozzle 10 for injecting liquid or gaseous fuels can now be arranged on the tip 36 formed by the side edges 30 of area 1.
  • a fuel line 11 with a plurality of injection openings, not shown, is preferably arranged along the side edges 30. This fuel line can of course also extend over the side edges 32 when using a second region 2.
  • the main flow 4 is converted into a pair of opposing longitudinal vortices when it flows around the side edges 30 of the vortex generator 1.
  • the vortex axes of these longitudinal vortexes lie in the axis of the main flow.
  • the swirl number of the longitudinal vortices is set by means of the sweep angle ⁇ 1 and the angle of attack ⁇ 1 so that no vortex breakdown and thus no dome-shaped recirculation zone 5 occurs.
  • the swirl of the longitudinal vertebrae must therefore be smaller than the critical swirl in which a vertebrae burst entry. With increasing angles ⁇ 1 and ⁇ 1, the vortex strength or the number of swirls can be increased up to the area of the vortex burst.
  • the swirl of the longitudinal vortices sets the distance required to mix the main flow and the fuel flow.
  • Area 2 is optional and is only used if the mixing section formed by area 1 is not sufficient for homogeneous mixing.
  • longitudinal vortices are induced in the flow by means of the side edges 32.
  • the swirl number of the longitudinal vertebrae is set by means of the sweep angle ⁇ 2 and the angle of attack ⁇ 2 so that there is no vortex breakdown and thus no recirculation zone 5.
  • the area 3 serves to stabilize the flame by means of the longitudinal vortices generated by the side edges 34.
  • the swirl number of the longitudinal vertebrae is set by the sweep angle ⁇ 3 and the angle of attack ⁇ 3 so that vortex breakdown occurs.
  • a pair of recirculation zones 5 are created for each delta-shaped body 40.
  • the swirl of the longitudinal vertebrae must be greater than the critical swirl, in which a vertebral burst occurs.
  • the gradient in the swirl number from the upstream region 1 or 2 to the region 3 is chosen to be very large in order to achieve a thermoacoustically stable behavior.
  • the cross-section of the channel not shown, can also be expanded.
  • the delta-shaped body 40 has a thermo-acoustically stable behavior even when it is operated rich.
  • the delta-shaped bodies 40 can be arranged in rows.
  • the delta-shaped bodies 40 are arranged in large numbers in parallel rows or concentric rings, for example in an annular combustion chamber.
  • a fuel nozzle 10 is then not attached to each tip 36 of the delta-shaped body 40.
  • four delta-shaped bodies 40 are arranged in a rectangular channel 8 such that the tips 36 come to lie upstream in the center of the channel 8.
  • the four delta-shaped bodies 40 are connected to one another via their tips 36 and to the channel 8 via their edges 35.
  • At the tip 36 of the delta-shaped body 40 there is a fuel nozzle 10.
  • the fuel is blown into the longitudinal vortices generated in the combustion air 4 when the edges 30, 32 flow around and mixed there with the combustion air.
  • Area 2 is omitted here as a result of sufficient mixing by means of area 1.
  • the region 3 of the delta-shaped body 40 and a cross-sectional expansion at the burner outlet 7 to form a combustion chamber 6 result in eight dome-shaped recirculation zones 5, at the tip of which the ignition takes place.
  • the flame itself is stabilized by the recirculation zones 5 without the need for a mechanical flame holder.
  • the channel 8 can of course also be made round and the number of delta-shaped bodies 40 per channel 8 is arbitrary and must be adapted to the respective conditions
  • the delta-shaped bodies 40 are arranged in a round channel 20.
  • the arrangement is analogous to Fig.4 and Fig.5.
  • the delta-shaped bodies 40 must be made curved.
  • mixing tubes 21 are without Flame stabilization arranged. Combustion air is blown through the mixing tubes 21 and fuel is injected into the combustion air via the nozzles 10.
  • well-known mixing elements such as deflecting bodies with a wing profile can be arranged in the mixing tubes 21.
  • Such a burner arrangement is suitable for stepped (lean-lean) and stepped (rich-lean) operation.
  • the number of mixing tubes 21 which are arranged around the channel 20 is arbitrary and must be adapted to the respective conditions.
  • a round delta-shaped body is arranged in a burner system according to WO 92/06328.
  • a burner with very low nitrogen oxide emissions is described.
  • At the center of the burner system described there is a fuel-rich flame zone surrounded by one or more zones with a low fuel content.
  • the flame is layered radially, which creates a large radial density gradient in the flame.
  • the fuel-rich zone contains less than the stoichiometric content of oxygen.
  • the radial stratification protects the fuel-rich flame core from mixing with the remaining combustion air.
  • the recirculation of combustion gases into the outer, low-fuel layers can further reduce nitrogen oxide emissions.
  • the recirculated combustion gas reduces the oxygen content and the flame temperature.
  • An annular channel 20 with delta-shaped bodies 40 arranged therein is surrounded by two concentric, annular channels 22 and 23.
  • a fuel nozzle 10 is arranged at the tip 36 of the delta-shaped bodies.
  • the delta premix burner 40 is now operated stoichiometrically, ie fuel-rich.
  • a possibly swirled exhaust gas / air mixture is fed axially via the concentric channels 22, 23.
  • the number of concentric channels 22, 23 the Channel 20 is arbitrary and must be adapted to the respective conditions.
  • delta-shaped bodies can also be fastened in the channel in other ways, for example so that the downstream edge of the third region forms a slot with the channel and that the tips do not touch.
  • the delta premix burner can also be installed in any other burner configuration.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP96810567A 1995-09-30 1996-08-28 Procédé et dispositif pour la combustion des combustibles Expired - Lifetime EP0789187B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19536672A DE19536672A1 (de) 1995-09-30 1995-09-30 Verfahren und Vorrichtung zur Verbrennung von Brennstoffen
DE19536672 1995-09-30

Publications (3)

Publication Number Publication Date
EP0789187A2 true EP0789187A2 (fr) 1997-08-13
EP0789187A3 EP0789187A3 (fr) 1998-10-14
EP0789187B1 EP0789187B1 (fr) 2003-02-26

Family

ID=7773816

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96810567A Expired - Lifetime EP0789187B1 (fr) 1995-09-30 1996-08-28 Procédé et dispositif pour la combustion des combustibles

Country Status (3)

Country Link
US (1) US5791891A (fr)
EP (1) EP0789187B1 (fr)
DE (2) DE19536672A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10128063A1 (de) * 2001-06-09 2003-01-23 Alstom Switzerland Ltd Brennersystem

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0619133A1 (fr) * 1993-04-08 1994-10-12 ABB Management AG Chambre de mélanges
EP0620403A1 (fr) * 1993-04-08 1994-10-19 ABB Management AG Dispositif de mélange et de stabilisation de la flamme dans une chambre de combustion avec mélange préalable du combustible.
GB2288010A (en) * 1994-04-02 1995-10-04 Abb Management Ag Premixing burner

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1912730A (en) * 1932-04-11 1933-06-06 Harold D Schrader Gas burner and mixing chamber therefor
US2520388A (en) * 1946-11-21 1950-08-29 Power Jets Res & Dev Ltd Apparatus for supporting combustion in fast-moving air streams
US2823519A (en) * 1950-02-14 1958-02-18 Dudley B Spalding Revolving fuel vaporizer and combustion stabilizer
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
DE9003781U1 (fr) * 1990-03-31 1990-06-13 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
WO1992006328A1 (fr) * 1990-10-05 1992-04-16 Massachusetts Institute Of Technology Systeme de combustion a emission reduite d'oxydes azotes
DE59402803D1 (de) * 1993-04-08 1997-06-26 Asea Brown Boveri Brennkammer
DE4408136A1 (de) * 1994-03-10 1995-09-14 Bmw Rolls Royce Gmbh Verfahren und Vorrichtung zur Kraftstoff-Aufbereitung für eine Gasturbinen-Brennkammer
US5554022A (en) * 1994-10-14 1996-09-10 Xothermic, Inc. Burner apparatus and method

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0619133A1 (fr) * 1993-04-08 1994-10-12 ABB Management AG Chambre de mélanges
EP0620403A1 (fr) * 1993-04-08 1994-10-19 ABB Management AG Dispositif de mélange et de stabilisation de la flamme dans une chambre de combustion avec mélange préalable du combustible.
GB2288010A (en) * 1994-04-02 1995-10-04 Abb Management Ag Premixing burner

Also Published As

Publication number Publication date
DE19536672A1 (de) 1997-04-03
DE59610173D1 (de) 2003-04-03
US5791891A (en) 1998-08-11
EP0789187A3 (fr) 1998-10-14
EP0789187B1 (fr) 2003-02-26

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