EP0252315A1 - Dispositif de chambre de combustion avec une chambre de précombustion pour une combustion sous-stoechiométrique - Google Patents

Dispositif de chambre de combustion avec une chambre de précombustion pour une combustion sous-stoechiométrique Download PDF

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Publication number
EP0252315A1
EP0252315A1 EP87108265A EP87108265A EP0252315A1 EP 0252315 A1 EP0252315 A1 EP 0252315A1 EP 87108265 A EP87108265 A EP 87108265A EP 87108265 A EP87108265 A EP 87108265A EP 0252315 A1 EP0252315 A1 EP 0252315A1
Authority
EP
European Patent Office
Prior art keywords
combustion
housing
fuel
combustion chamber
air
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
EP87108265A
Other languages
German (de)
English (en)
Other versions
EP0252315B1 (fr
Inventor
Jakob Dr. Keller
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.)
BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
Original Assignee
BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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 BBC Brown Boveri AG Switzerland, BBC Brown Boveri France SA filed Critical BBC Brown Boveri AG Switzerland
Publication of EP0252315A1 publication Critical patent/EP0252315A1/fr
Application granted granted Critical
Publication of EP0252315B1 publication Critical patent/EP0252315B1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • 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 
    • F23C3/00—Combustion apparatus characterised by the shape of the combustion chamber
    • 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 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • 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 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/02—Disposition of air supply not passing through burner

Definitions

  • the present invention relates to a combustion chamber device with a pre-combustion chamber for substoichiometric combustion, the combustion mixture which is incompletely burned in a housing of the pre-combustion chamber being completely burned in a post-combustion chamber with a large excess of air.
  • this disadvantage is to be avoided in that, by means of a special design of the pre-combustion chamber by means of an air and fuel layer, its wall is shielded from the ignited combustion mixture and the temperature near the wall is thereby reduced to values which are permissible for the material of the combustion chamber walls are.
  • the pre-combustion chamber according to the invention for substoichiometric combustion is characterized in that the housing of the pre-combustion chamber is essentially a rotating body which is formed by rotating a heart-shaped generator with a cut tip about its axis of symmetry or about an axis of rotation parallel to this axis of symmetry and lying outside the generator by cutting off the tip of the heart during the rotation of the generators, a circular-cylindrical or circular-cylindrical outlet duct results in a combustion air duct extending over the boundary of this outlet duct, the outlet openings of which are arranged along the aforementioned boundary of the outlet duct in such a way that the combustion air in the edge region of the outlet channel can flow into the housing at a tangent to the inner boundary, such that injection nozzles for a liquid fuel are present, the axes of the nozzles being oriented such that the fuel jets shield the combustion air flowing into the housing from the ignited combustion mixture, and that means for supplying additional air into the pre
  • the injection nozzles are arranged at the end of injection lines, which branch off from a fuel ring line surrounding the outlet duct and open directly radially inward of the outlet opening of the combustion air duct into the housing, the axes of the injection nozzles being essentially parallel to the tangent to the respective are directed adjacent wall part of the housing, and wherein for the supply of additional air, an annular additional air channel arranged at the end of the outlet channel is present.
  • the injection nozzles are arranged at the end of a fuel line which opens into the housing coaxially with the axis of symmetry thereof, the axes of the injection nozzles being directed in such a way that the fuel jets shield the combustion air blown into the housing from the ignited fuel mixture, and where the additional air is taken from the combustion air intended for the afterburning chamber.
  • the housing 2 of the pre-combustion chamber 1 shown schematically in FIG. 1 shows the shape of a heart with a cut-off tip in an axial section through the axis of rotation of the rotary body. In their place, the housing ends in an outlet channel 3 for the incompletely burned fuel mixture generated in the housing 2.
  • a fuel ring line 4 for the liquid fuel is provided in the lower part of the housing 2 at a distance from the same. This passes from a fuel tank (not shown) via a feed line 5 into the ring line 4. From this ring line, a number branches off, uniformly distributed over the circumference, hook-shaped curved injection lines 6, which end within the outlet channel 3 in injection nozzles 7, from which fuel jets 8 are approximately parallel emerge towards the inner surface of the housing 2. Radially inward of the injection lines 6 is a rotation Body-shaped baffle 9 which, together with the outer surface of the housing 2, defines an annular combustion air duct 10 in its lower part. The flow arrows 11 symbolize the combustion air, which is preheated in the channel 10 and, after a deflection at the lower end of the housing 2, flows upward approximately parallel to the housing wall and mixes with the fuel jet 8.
  • Another rotationally symmetrical baffle plate 12 which surrounds the injection lines 6, delimits with the first-mentioned baffle plate 9 an annular additional air duct 13 through which air, represented by the flow arrows 14, is admixed to the preburned fuel mixture in the region of the outlet duct 3 in a stoichiometric ratio.
  • This mixture then arrives in a post-combustion chamber 16, part of the housing of which is shown, for complete combustion.
  • the mechanism of shielding the wall of the housing 2 against the high combustion temperatures that occur during the substoichiometric pre-combustion is based on the tangential injection of the combustion air that takes place over the entire inner circumference of the housing 2, which creates a vortex ring with a toroidal vortex core 15, the Cross section in Fig. 1 is symbolized by the two circles with dashed double hatching.
  • this vortex core contains very hot gases, the centrifugal effect causing a stratification of the combustion gases of different temperatures or densities, which can only slowly balance out from the inside out.
  • Such a compensation of the temperature or density from the inside out is, however, in stationary operation suppressed by the constantly supplied fuel / air mixture.
  • the vortex core 15 also acts as an ignition source, by means of which the substoichiometric fuel / air mixture is ignited.
  • Fuel injection radially inward of the combustion air layer close to the wall isolates it from the core of the incompletely burned combustion mixture to approximately the lower half of the housing 2, so that the latter cannot continue to burn with air from the layer close to the wall and only becomes ignitable again after additional air has been mixed in from the additional air duct 13 , whereby it can be completely burned in the afterburning chamber 16.
  • the speed of the air injection into the pre-combustion chamber 1 should be significantly higher than the flame propagation speed, which creates a spiral flame front, which ideally does not hit the inner surface of the housing 2. At the time of ignition, the mixing process has progressed so far that lean mixture zones no longer occur.
  • Fig. 2 shows a pre-combustion chamber 17 of a simplified design, in which the liquid fuel through a Axis of symmetry of the housing 18 coaxial fuel line 19 is fed to the injection nozzles 20 arranged at the end thereof. While the air for the pre-combustion is blown into the housing 18 close to the wall from below, as in the embodiment according to FIG. 1, the fuel is injected in the opposite direction from above at high speed.
  • the nozzle axes are oriented in such a way that the air jets near the wall are also shielded from the burning mixture ignited in the center.
  • Such a pre-combustion chamber 17 can advantageously be combined with gas burners arranged uniformly distributed over the circumference, two of which are shown in FIG.
  • the fuel gas flowing in through the gas burner is indicated by the arrows 22, the combustion air by the arrows 23.
  • the combustion air flow is dimensioned such that it is sufficient at least for the complete combustion of the gas and for the post-combustion of the incompletely burned combustion mixture flowing out of the pre-combustion chamber in the after-combustion chamber 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP87108265A 1986-07-08 1987-06-08 Dispositif de chambre de combustion avec une chambre de précombustion pour une combustion sous-stoechiométrique Expired - Lifetime EP0252315B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2748/86 1986-07-08
CH2748/86A CH671449A5 (fr) 1986-07-08 1986-07-08

Publications (2)

Publication Number Publication Date
EP0252315A1 true EP0252315A1 (fr) 1988-01-13
EP0252315B1 EP0252315B1 (fr) 1992-10-07

Family

ID=4240721

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87108265A Expired - Lifetime EP0252315B1 (fr) 1986-07-08 1987-06-08 Dispositif de chambre de combustion avec une chambre de précombustion pour une combustion sous-stoechiométrique

Country Status (5)

Country Link
US (1) US4894005A (fr)
EP (1) EP0252315B1 (fr)
JP (1) JPS6325418A (fr)
CH (1) CH671449A5 (fr)
DE (1) DE3782097D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0982544A1 (fr) * 1998-08-27 2000-03-01 Asea Brown Boveri AG Brûleur pour une turbine à gaz
EP1766292A2 (fr) * 2004-06-10 2007-03-28 Georgia Technology Research Corporation Chambre de combustion a flux inverse au point d'arret pour systeme de combustion

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5114404A (en) * 1990-07-24 1992-05-19 Paxton Gerald R Multifunctional retractable needle type general purpose disabling syringe having enhanced safety features and related method of operation
DE59208364D1 (de) * 1992-10-23 1997-05-22 Asea Brown Boveri Brenner mit elektrischer Zündeinrichtung
DE4416650A1 (de) * 1994-05-11 1995-11-16 Abb Management Ag Verbrennungsverfahren für atmosphärische Feuerungsanlagen
DE19502796B4 (de) * 1995-01-30 2004-10-28 Alstom Brenner
US6874452B2 (en) * 2002-01-15 2005-04-05 Joseph S. Adams Resonant combustion chamber and recycler for linear motors
CN101573561B (zh) * 2006-10-18 2012-03-28 贫焰公司 与能量释放/转换装置组合使用的用于气体和燃料的预混合器
US8015814B2 (en) * 2006-10-24 2011-09-13 Caterpillar Inc. Turbine engine having folded annular jet combustor
JP5296320B2 (ja) * 2007-01-30 2013-09-25 ゼネラル・エレクトリック・カンパニイ 逆流噴射機構を有するシステム及び燃料及び空気を噴射する方法
EP2006606A1 (fr) * 2007-06-21 2008-12-24 Siemens Aktiengesellschaft Stabilisation sans tourbillonner de la flamme d'un brûleur à prémélange
JP5629321B2 (ja) 2009-09-13 2014-11-19 リーン フレイム インコーポレイテッド 燃焼装置用の入口予混合器
RU2633982C1 (ru) * 2016-06-29 2017-10-20 Акционерное общество "ОДК-Авиадвигатель" Жаровая труба камеры сгорания газотурбинного двигателя

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CH163686A (de) * 1932-09-08 1933-08-31 Fricker Fritz Brenner für flüssige Brennstoffe.
US2651913A (en) * 1951-03-13 1953-09-15 Solar Aircraft Co Gas turbine combustion chamber
US2715816A (en) * 1950-10-27 1955-08-23 Ruston & Hornsby Ltd Combustion chamber for use with internal combustion turbines
DE1021646B (de) * 1953-12-07 1957-12-27 Gen Elek C Company Brennkammer
FR2203023A1 (fr) * 1972-10-13 1974-05-10 Onera (Off Nat Aerospatiale)
FR2241005A1 (fr) * 1973-08-18 1975-03-14 Mtu Muenchen Gmbh

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Publication number Priority date Publication date Assignee Title
CH163686A (de) * 1932-09-08 1933-08-31 Fricker Fritz Brenner für flüssige Brennstoffe.
US2715816A (en) * 1950-10-27 1955-08-23 Ruston & Hornsby Ltd Combustion chamber for use with internal combustion turbines
US2651913A (en) * 1951-03-13 1953-09-15 Solar Aircraft Co Gas turbine combustion chamber
DE1021646B (de) * 1953-12-07 1957-12-27 Gen Elek C Company Brennkammer
FR2203023A1 (fr) * 1972-10-13 1974-05-10 Onera (Off Nat Aerospatiale)
FR2241005A1 (fr) * 1973-08-18 1975-03-14 Mtu Muenchen Gmbh

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
EP1766292A2 (fr) * 2004-06-10 2007-03-28 Georgia Technology Research Corporation Chambre de combustion a flux inverse au point d'arret pour systeme de combustion
EP1766292A4 (fr) * 2004-06-10 2011-07-27 Georgia Tech Res Inst Chambre de combustion a flux inverse au point d'arret pour systeme de combustion

Also Published As

Publication number Publication date
US4894005A (en) 1990-01-16
DE3782097D1 (de) 1992-11-12
JPS6325418A (ja) 1988-02-02
EP0252315B1 (fr) 1992-10-07
CH671449A5 (fr) 1989-08-31

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