EP0114062A2 - Procédé et dispositif pour la combustion de combustibles solides, en particulier du charbon, de la tourbe etc. - Google Patents

Procédé et dispositif pour la combustion de combustibles solides, en particulier du charbon, de la tourbe etc. Download PDF

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Publication number
EP0114062A2
EP0114062A2 EP84100243A EP84100243A EP0114062A2 EP 0114062 A2 EP0114062 A2 EP 0114062A2 EP 84100243 A EP84100243 A EP 84100243A EP 84100243 A EP84100243 A EP 84100243A EP 0114062 A2 EP0114062 A2 EP 0114062A2
Authority
EP
European Patent Office
Prior art keywords
fuel
inlet opening
air
inlet
combustion chamber
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.)
Ceased
Application number
EP84100243A
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German (de)
English (en)
Other versions
EP0114062A3 (fr
Inventor
Kurt Dipl.-Ing. Skoog
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.)
STUBINEN UTVECKLING AB
Original Assignee
STUBINEN UTVECKLING 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
Priority claimed from DE19833309905 external-priority patent/DE3309905C2/de
Priority claimed from DE19833309906 external-priority patent/DE3309906A1/de
Application filed by STUBINEN UTVECKLING AB filed Critical STUBINEN UTVECKLING AB
Publication of EP0114062A2 publication Critical patent/EP0114062A2/fr
Publication of EP0114062A3 publication Critical patent/EP0114062A3/fr
Ceased legal-status Critical Current

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Classifications

    • 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
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning 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 
    • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
    • F23C9/003—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber for pulverulent fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D1/00—Burners for combustion of pulverulent fuel
    • F23D1/005—Burners for combustion of pulverulent fuel burning a mixture of pulverulent fuel delivered as a slurry, i.e. comprising a carrying liquid
    • 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
    • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

  • the invention relates to a method and a device for burning solid fuels, in particular coal, peat or the like, in powdered form, which are introduced into a combustion chamber with the formation of a recirculating flow profile, this flow profile being limited by a rotating external air flow.
  • the outer air flow is blown into the combustion chamber via an air inlet concentrically surrounding the fuel inlet, the air inlet comprising swirl elements which set the air flow in rotation.
  • the aim of the present invention is in particular to obtain the most complete and emission-free combustion of the solid fuels mentioned when they are injected into the combustion chamber mixed with a carrier liquid such as water and / or oil or the like to form an emulsion.
  • a carrier liquid such as water and / or oil or the like
  • Such a fuel emulsion is usually injected into the combustion chamber through a nozzle-like opening, with training of a full cone which opens only insignificantly, with the result that the combustion takes place in a relatively long flash and is correspondingly incomplete due to the relatively small free fuel surface resulting therefrom.
  • very long combustion chambers or combustion chambers are required.
  • the device comprises a central coal dust line through which coal is pneumatically (with air) brought into the ignition zone of the device.
  • a hollow conical diffuser is arranged at the outlet end of the coal dust line, through which the emerging coal dust receives a hollow cone-like flow profile.
  • the coal dust line is arranged within a secondary air line and extends co-axially to the latter in such a way that a secondary air ring channel is formed.
  • the secondary air line is provided in the area of the coal dust diffuser with a diverging mouth section, which represents the outer boundary of the combustion chamber.
  • Swirl elements are arranged in the secondary air line, which impart a rotation about the central axis of the device to the secondary air flow.
  • the external secondary air flow causes a recirculation of hot combustion gases and unburned fuel particles, i.e. backflow of the same back to fuel entry. This gives you a more stable flame.
  • the present invention is therefore based on the object of modifying the known method or the known device so that in all conceivable operating states (ignition, part load, full load) a highly stable flame is obtained which at the same time ensures maximum combustion in the shortest possible way, i.e. in extremely short combustion chambers.
  • the recirculated rest of unburned fuel particles are burned at the same time. Both effects lead to increased flame stability and shortening of the flame and to a higher degree of combustion.
  • the flame mantle is approximately apple-shaped.
  • the flow velocities of the partial flows mentioned preferably decrease from the inside to the outside.
  • the primary part of the radially inner partial flow or the flow closest to the fuel inlet has the task of breaking open the fuel cone in order to enlarge the free fuel surface.
  • the partial flows lying somewhat further radially primarily have the task of limiting the fuel flow profile or the flame and causing them to rotate, so that immediately behind the fuel inlet there is a sufficiently high negative pressure which makes the mentioned recirculation of a part hotter Combustion gases and small residues of unburned fuel particles.
  • the partial flows lying somewhat further radially have the task of building up a negative pressure in the area of the end wall of the combustion chamber that includes the fuel inlet, which results in a spontaneous fanning out of the fuel emulsion injected into the combustion chamber and thus an additional shortening of the flame.
  • the shape of the fuel flow profile or the flame is determined by the equilibrium of the centrifugal forces acting on the fuel emulsion or flame and external and central “negative pressure” forces.
  • the formation of an external negative pressure can be additionally increased by the measure according to claim 5.
  • the recirculation of a part of hot combustion gases which is sought according to the invention has the additional great advantage that part of the dissociated water and thus released oxygen flow back centrally to the fuel inlet, whereby the combustion additionally from the inside of the hollow fuel spray cone is initiated.
  • the importance of the invention becomes apparent when one considers how long the burning time of e.g. Coal compared to the burning time of oil or wood.
  • the particle path must be correspondingly long in order to obtain a relatively complete combustion. This usually results in the long combustion chambers mentioned at the beginning.
  • the required long particle path is achieved by spontaneously fanning out the hollow fuel spray cone, conveying the fuel particles along a helical flow path and partially recirculating back to the fuel inlet immediately at all load levels over the shortest distance in the direction of the central axis of the fuel inlet or Combustion chamber reached.
  • pure oil is first introduced through the inlet opening is injected, which is then increasingly mixed with pulverized solid fuels, such as pulverized coal, and optionally water.
  • pulverized solid fuels such as pulverized coal
  • the oil can then be completely replaced by water. This also depends in part on the consistency of the coal to be burned or the like.
  • the oil injection at the start facilitates the ignition.
  • the reverse is true when the combustion is switched off.
  • the powdered fuel is increasingly removed until finally only oil remains as fuel. This avoids clumping or clogging of the fuel inlet opening or ring nozzle when switching off.
  • the solid fuel used is primarily coal, for example hard coal, bituminous coal, gas-rich coal or a mixture thereof.
  • Figure 1 shows that the burning time of coal particles is significantly longer than the burning time of wood particles or oil droplets, the burning time characteristics of coal, wood and oil depending on the particle size or droplet size and thus depending on the free surface per unit volume is always the same.
  • the combustion chambers of conventional coal burners are built to be very long in order to be able to absorb the long flame.
  • the measures according to the invention allow complete combustion of pulverized coal even over the shortest distance, i.e. with an extremely short overall length of the combustion chamber.
  • the coal burner shown in schematic longitudinal section in FIG. 2 has an annular nozzle mouthpiece 38 with an approximately annular inlet opening 10 opening into the combustion chamber 22, the gap width of which can be varied by changing the relative position of the side walls 46, 48 delimiting the annular inlet opening 10.
  • the side walls 46, 48 are conical in the illustrated embodiment, so that the fuel emulsion exits the annular inlet Opening 10 receives a hollow cone-like flow profile, which experiences a strong fanning out or widening to a bell-like or apple-like profile in the further course.
  • the nozzle mouthpiece 38 is concentrically surrounded by a first gas channel 50 (see FIG. 3), the inlet opening 12 of which opens into the combustion chamber 22 is adjacent to the inlet opening 10 for the fuel emulsion.
  • a so-called "primary primary air” flows through the gas channel 50, which can be enriched with combustion gases of higher temperature, the gas emerging from the opening 12 having a flow velocity of 100 to 200 m / s, preferably approximately 130 m / s.
  • the side walls 46 'and 48' delimiting the opening 12 are also conical in shape, similar to the side walls 46, 48 delimiting the annular inlet opening 10 for the fuel emulsion.
  • the gas channel 50 is surrounded concentrically by a further gas channel 52 (see FIG. 3), the annular inlet opening 14 opening into the combustion chamber 22 is likewise delimited by conical side walls 46 "and 48" (see FIG. 3).
  • the side walls 46 ", 48" are directed such that they impart a cone-like flow profile to the gas flow emerging from the ring opening 14, which constricts the cone-like flow profile of the fuel emulsion emerging from the ring opening 10 or gas flow emerging from the ring opening 12.
  • secondary primary air Before the so-called “secondary primary air” flowing through the gas channel 52 emerges, it is also deflected by guide vanes 26 arranged in the area of the ring opening 14, specifically by about 40 to 45 ° to the longitudinal axis 40 of the nozzle mouthpiece 38, that is to say in rotation about the longitudinal axis 40.
  • the exit velocity of the "secondary primary air” is approximately 120 to 180 m per second, preferably 140 m per second.
  • the annular gap width of the opening 14 can in turn be changed by changing the relative position of the side walls 46 ′′, 48 ′′ delimiting it.
  • the exit velocity of the "secondary primary air” is of course variable in a corresponding manner.
  • the "secondary primary air” is also blown into the annular duct 52 at a pressure of approximately 1000 to 1200 mm water column.
  • the “secondary primary air” is deflected by the guide vanes or guide plates 26 in the same direction as the “primary primary air” is deflected by the guide vanes or guide plates 24 arranged in the region of the opening 12.
  • the "secondary primary air” is preferably not enriched with hot combustion gases, since it serves less as a carrier medium for the fuel emulsion injected into the combustion chamber 22 than rather to enlarge the free surface thereof and to enrich or supply the fuel particles with oxygen.
  • the nozzle mouthpiece 38, the ring channel 50 directly surrounding it and that of the "secondary primary air" Component 54 ′ through which annular channel 52 flows can be inserted as a whole into the end wall 42 of the combustion chamber 22 or into the gas register 54, 56, 58 to be described (see FIG. 3) and thus also easily by a corresponding, somewhat modified component interchangeable.
  • the gas channel 52 for the “secondary primary air” is in turn surrounded by a concentric gas channel 54, this is surrounded by a further gas channel 56 and, finally, by a gas channel 58.
  • the corresponding ring openings opening into the combustion chamber 22 are identified in FIGS. 2 and 3 with the reference numbers 16, 18 and 20.
  • the ring channels 54, 56, 58 are flowed through selectively, preferably by air, the injection being carried out under a pressure of about 200 to 300 mm water column.
  • the guide vanes or guide plates 28 deflect the gas flow by approximately 70 °.
  • the guide blades or guide plates 30 and 32 deflect the gas flow by approximately 40 to 50 ° and 0 to 40 °. All of the guide vanes or guide plates, in particular the outermost guide vanes or guide plates 32, can be changed with regard to their angular position and can therefore be adapted to the fuel to be burned.
  • the flow velocity of the air emerging from the ring opening 16 is approximately 40 m per second at the start of combustion, and approximately 70 m per second at full load.
  • the flow rate from the ring openings 18 and 20 escaping air varies between 0 m per second at the start of combustion to 70 m per second at full load.
  • the ring mouthpiece 78 is connected to the tube jacket 80 separating the two primary air channels 50, 52, so that the axial displacement of the ring mouthpiece 78 takes place by corresponding action on the tubular jacket 80.
  • the ring mouthpiece 78 is shifted to the right in FIG. 3, so that the gap widths of the ring openings or gaps 12 and 14 and thus the amount of primary air escaping are a minimum
  • the ring mouthpiece is shifted to the left in Figure 3, so that the ring openings or gaps 12 and 14 max are always open.
  • the outlet quantity of the "primary" and "secondary" primary air is correspondingly maximum.
  • the gas flow causing the emulsion or individual gas flows becomes a negative pressure of approximately 400 to 500 mm water column in relation to the atmospheric pressure in the area of the longitudinal axis 40 directly behind the inlet opening 10 for the fuel emulsion and a negative pressure in the area of the front-side gas register 16, 18, 20 of about 40 to 50 mm water column in relation to atmospheric pressure.
  • the vacuum regions mentioned are identified in FIG. 2 by the reference numbers 60 and 62.
  • a recirculation 64 of a portion of hot combustion gases and a remainder of unburned fuel particles to the inlet opening 10 is triggered.
  • the recirculation 64 takes place over the entire circumference of the bell-shaped or apple-shaped flow profile 66 (flame part).
  • the centrally recirculating combustion gases which are around 1500 to 1700 ° C., are deflected at the central end face within the ring opening 10 and are carried back into the combustion chamber 22 by the injected fuel emulsion.
  • the hot combustion gases cause the same to ignite immediately after the relatively cold fuel emulsion emerges, so that the combustion process is started relatively close behind the fuel inlet 10.
  • the outer flow profile 66 (flame jacket) is determined by the equilibrium between the centrifugal forces caused by the rotation 68 as well as the forces caused by the negative pressure prevailing outside the flow profile 66 in the area 62 of the end wall 42 and by the central negative pressure in the area 60 within the Flow profile 66 caused opposing forces on the other hand.
  • the ring opening 16 is set so that the speed of the exiting air is about 40 m per second.
  • the ring mouth Piece 78 is - as explained - shifted towards the combustion chamber 22 so that the annular gaps between the side walls 46 ', 48' and 46 ", 48" are reduced, whereby the amount of discharge of the "primary" and "secondary” primary air at something increased exit speed is reduced. Due to the somewhat increased exit velocity, in particular of the “secondary primary air” from the ring opening 14, a high break-open effect is obtained.
  • the primary air is divided at the start such that approximately 60 to 70%, preferably 90%, of the same flow out of the ring opening 12 closest to the fuel inlet 10 and only about 30 to 40%, preferably 10%, of the same from the second next ring opening 14.
  • the central end face within the ring opening 10 is provided with a circumferential or ring-shaped deflection channel 44 to support the recirculation and admixture of the hot combustion gases to the injected fuel emulsion.
  • the central end face within the ring opening 10 can be coated with a heat-resistant material, for example ceramic.
  • the entire inner cone 70 of the nozzle mouthpiece 38 preferably consists of heat-resistant material, for example ceramic, in the region of the annular inlet opening 10.
  • the coal burner shown in schematic longitudinal section in FIG. 4, modified from the embodiment according to FIGS. 2 and 3, has an annular nozzle mouthpiece 38 with an approximately annular inlet opening 10 opening into the combustion chamber 22, the gap width of which by changing the relative position of the annular inlet opening 10 delimiting side walls 46, 48 can be varied.
  • the side walls 46, 48 are also conical in the illustrated embodiment, so that the fuel emulsion receives a hollow cone-like flow profile when exiting from the annular inlet opening 10, which experiences a strong fanning out or widening to a bell-like or apple-like profile in the further course.
  • the nozzle mouthpiece 38 is concentrically surrounded by a first gas channel 50, the inlet opening 12 'of which opens into the combustion chamber 22 so that the corresponding gas flow (“primary primary air”) flows in an inlet opening 10 perpendicular to the axis 40 of the inlet chamber 10 for the fuel emulsion extending plane is initiated.
  • primary primary air a gas flow introduced into the combustion chamber 22 through the inlet opening 12 ′ is identified by the flow arrow 84, the fuel flow profile 36 experiencing a local constriction or indentation 36 ′ through this flow.
  • a so-called “primary primary air” flows through the gas channel 50, which can be enriched with combustion gases of higher temperature.
  • the gas (air) emerging from the opening 12 ' has a flow velocity of approximately 100 to 200 m / sec, preferably approximately 130 m / sec.
  • the inlet opening 12 'for the "primary primary air” comprises several, e.g. twelve inlet openings 47 arranged evenly distributed over the circumference, which are each directed at the same angle ⁇ to the radial.
  • the angle ⁇ is approximately 10 to 25 °, preferably 15 °.
  • the "primary primary air” introduced into the combustion chamber 22 is impressed with a rotation about the longitudinal axis 40, which is then transferred to the fuel emulsion injected into the combustion chamber 22.
  • the "primary primary air” is usually blown into the gas channel 50 at a pressure of about 1000 to 1200 mm water column. When burning somewhat tougher fuel emulsions, this pressure is preferably about 2000 to 4000 mm water column.
  • the gas channel 50 is surrounded concentrically by a further gas channel 52 (see FIGS. 2 and 3), the annular inlet opening 14 opening into the combustion chamber 22 is delimited by conical side walls 46 ′′ and 48 ′′.
  • the side walls 46 ", 48" are directed in such a way that they impart a cone-like flow profile to the gas flow emerging from the ring opening 14, which attempts to penetrate the hollow cone-like flow profile 36 of the fuel emulsion emerging from the ring opening 10 and opening in the direction of the combustion chamber 22.
  • the so-called “secondary primary air” flowing through the gas channel 52 emerges, it is deflected by guide vanes 26 arranged in the area of the ring opening 14, specifically by about 40 to 45 ° to the longitudinal axis 40 of the nozzle mouthpiece 38, that is to say in rotation about the longitudinal axis 40.
  • the exit velocity of the "secondary primary air” is approximately 120 to 180 m / sec, preferably 140 m / sec.
  • the annular gap width of the opening 14 can be changed by changing the relative position of the side walls 46 ′′, 48 ′′ delimiting it. In a corresponding manner, the amount of discharge (capacity) of the "secondary primary air” is of course variable, with the gas discharge velocity remaining approximately the same.
  • the "secondary primary air” is also blown into the annular duct 52 at a pressure of approximately 1000 to 1200 mm water column. With somewhat tougher fuel emulsions, this pressure can be higher, e.g. also about 2000 to 4000 mm water column.
  • the "secondary primary air” is deflected by the guide vanes or guide plates 26 in the same direction as the “primary primary air” is deflected by the openings 47 of the primary air inlet 12 ′ inclined to the radial.
  • the "secondary primary air” is preferably not enriched with hot combustion gases, since it serves less as a carrier medium for the fuel emulsion injected into the combustion chamber 22 than rather to increase the free or effective surface area thereof and to enrich or supply the fuel particles with oxygen.
  • the component 54 comprising the nozzle mouthpiece 38, the ring channel 50 directly surrounding it and the ring channel 52 through which the "secondary primary air” flows is as a whole in the end wall 42 of the combustion chamber 22 or in the gas register 54, 56 to be described below 58 (see FIG. 2) can be used and can therefore also be easily replaced by a corresponding, somewhat modified component.
  • the gas channel 52 for the “secondary primary air” is in turn surrounded by a concentric gas channel 54, this by another gas channel 56 and finally by a gas channel 58 each concentrically.
  • the corresponding ring openings opening into the combustion chamber 22 are identified in FIG. 2 by the reference numbers 16, 18 and 20.
  • the ring channels 54, 56, 58 are flowed through selectively, preferably by air, the blowing in taking place under a pressure of about 200 to 300 mm water column.
  • air Before the air exits the annular gas or air inlet openings 16, 18, 20, it is deflected by guide vanes or guide plates 28, 30, 32 arranged in the region of the openings 16, 18, 20 and thus about the longitudinal axis 40 in Rotation offset, in the same direction as the "primary primary air” or "secondary primary air".
  • the guide vanes or guide plates 28 deflect the gas flow by approximately 70 °.
  • the guide blades or guide plates 30 and 32 deflect the gas flow by approximately 40 to 50 ° and 0 to 40 °. All of the guide vanes or guide plates, in particular the outermost guide vanes or guide plates 32, can be changed with regard to their angular position and can therefore be adapted to the fuel to be burned.
  • the flow velocity of the air emerging from the ring opening 16 is approximately 40 m / sec at the start of the combustion and approximately 70 m / sec at full load.
  • the flow velocity of the air emerging from the ring openings 18 and 20 varies between 0 m / sec at the start of the combustion and 70 m / sec at full load.
  • ring mouthpiece 78 is connected to the tubular jacket 80 which separates the two primary air channels 50, 52, so that the axial displacement of the ring mouthpiece 78 in the direction of the double arrow 82 takes place by corresponding action on the tubular jacket 80.
  • the ring mouthpiece 78 comprises the radially inner side wall 46 "of the ring opening 14 for the exit of the" secondary primary air "and primary air inlet openings 45, which have a free cross section which is approximately elliptical, extending in a plane approximately perpendicular to the longitudinal axis 40 of the combustion chamber 22.
  • the ring mouthpiece 78 is mounted to slide back and forth in the axial direction, ie in the direction of the longitudinal axis 40 or in the direction of the double arrow 82 on a cup-shaped extension 86 of the nozzle mouthpiece 38, the cup-shaped extension 86 having openings 51 corresponding to the radial openings 45 in the nozzle mouthpiece 78
  • the two radial openings 45 and 51 can be made to coincide, in FIG. 5 when the ring mouthpiece 78 is shifted to the left.
  • the ring mouthpiece 78 is shifted to the right (position in FIG.
  • the longitudinal axis 40 becomes 40
  • a negative pressure of approximately 400 to 500 mm water column in relation to the atmospheric pressure and in the area of the front-side gas register 16, 18, 20 a negative pressure of approximately 40 to 50 mm water column in relation to the atmospheric pressure are built up.
  • the vacuum regions mentioned are identified in FIG. 4 by the reference numbers 60 and 62.
  • the hot combustion gases cause the same to ignite immediately after the relatively cold fuel emulsion emerges, so that the combustion process is relatively close behind the combustion material entry 10 is started.
  • the outer flow profile 66 (flame jacket) is determined by the equilibrium between the centrifugal forces caused by the rotation and the forces caused by the negative pressure prevailing outside the flow profile 66 in the area 62 of the end wall 42 and by the central negative pressure in the area 60 within the flow profile 66 contingent opposing forces on the other hand.
  • the two outer gas and air channels 56, 58 are closed.
  • the ring opening 16 is adjusted so that the speed of the exiting air is about 40 m / sec.
  • the annular mouthpiece 78 is - as explained - shifted towards the combustion chamber 22, so that the annular gap between the side walls 46 ", 48" and the free cross section of the primary air inlet 12 'are reduced (see position in FIG. 5, as a result of which the discharge quantity the "primary" and "secondary” primary air is reduced at a somewhat increased exit speed.
  • a high break-open effect is obtained due to the somewhat increased exit speed, in particular of the "secondary primary air" from the ring opening 14.
  • the primary air is divided at the start so that about 60 up to 70%, preferably 90%, of the same from the inlet 12 'closest to the fuel inlet 10 and only about 30 to 40%, preferably 10%, of the same from the ring opening 14.
  • the central end surface formed flat within the annular opening 10.
  • it can also -. ig as in the example of F 2 and 3 -. be provided with an approximately annular deflector emulsion of the hot combustion gases to the injected fuel to support the recirculation and mixing.
  • the central end face within the ring opening 10 can be coated with a heat-resistant material, for example ceramic, preferably the entire inner cone 70 of the nozzle mouthpiece 38 in the region of the annular inlet opening 10 is made of heat-resistant material, for example ceramic.
  • the deflection of the radially outermost individual gas flow around the axis 40 by the guide vanes or guide plates 32 is less and can even be zero.
  • the radial expansion of the flow profile or the flame jacket 66 is influenced considerably. In particular, this reliably prevents fuel particles from being deposited on the side wall 74 of the combustion chamber 22.
  • the outside diameter of the insertable component 54 ' is about 244 mm and the outside diameter of the outermost ring channel 58 is 800 to 900 mm.
  • the above-mentioned admixture of combustion gases to the "primary primary air” has two advantages. First, the fuel emulsion can be preheated along its path through channel 50. On the other hand, a certain amount of afterburning and thus higher efficiency can be achieved. These two advantages outweigh the disadvantage of a lower oxygen content. This disadvantage can easily be compensated for by oxygen enrichment of the other individual gas flows ("secondary air").
  • wetting agents are preferably added, which ensure a uniform distribution of the coal particles in the water and thus an emulsion.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
EP84100243A 1983-01-18 1984-01-11 Procédé et dispositif pour la combustion de combustibles solides, en particulier du charbon, de la tourbe etc. Ceased EP0114062A3 (fr)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
DE3301469 1983-01-18
DE3301469 1983-01-18
DE3309906 1983-03-18
DE3309905 1983-03-18
DE19833309905 DE3309905C2 (de) 1983-01-18 1983-03-18 Verfahren und Vorrichtung zum Verbrennen fester Brennstoffe in pulverisierter Form
DE19833309906 DE3309906A1 (de) 1983-03-18 1983-03-18 Verfahren und vorrichtung zum verbrennen fester brennstoffe, vorzugsweise kohle, torf oder dergleichen, in pulverisierter form

Publications (2)

Publication Number Publication Date
EP0114062A2 true EP0114062A2 (fr) 1984-07-25
EP0114062A3 EP0114062A3 (fr) 1986-02-19

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Application Number Title Priority Date Filing Date
EP84100243A Ceased EP0114062A3 (fr) 1983-01-18 1984-01-11 Procédé et dispositif pour la combustion de combustibles solides, en particulier du charbon, de la tourbe etc.

Country Status (6)

Country Link
US (2) US4569295A (fr)
EP (1) EP0114062A3 (fr)
AU (1) AU557542B2 (fr)
CA (1) CA1224089A (fr)
DK (1) DK19984A (fr)
FI (1) FI840166A7 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0233680A1 (fr) * 1986-01-08 1987-08-26 Hitachi, Ltd. Procédé et dispositif pour la combustion d'un mélange charbon/eau
EP0202443A3 (en) * 1985-05-20 1987-09-30 Stubinen Utveckling Ab Method and device for the combustion of liquid and/or solid pulverulent fuels
EP0248539A1 (fr) * 1986-05-07 1987-12-09 Hitachi, Ltd. Atomiseur et chaudière à boue de charbon et d'eau comportant un tel atomiseur
US4718359A (en) * 1983-01-18 1988-01-12 Stubinen Utveckling Ab Process and a means for burning solid fuels, preferably coal, turf or the like, in pulverized form
DE3738064A1 (de) * 1987-11-09 1989-05-24 Stubinen Utvecklings Ab Vorrichtung zum verbrennen fester brennstoffe, insbesondere kohle, torf oder dergleichen, in pulverisierter form
WO1992016794A1 (fr) * 1991-03-20 1992-10-01 Witteveen Gustaaf J Procede et dispositif de melange pour substances gazeuses, liquides ou solides et pulverisees
EP0957311A3 (fr) * 1998-05-09 2000-02-23 Alstom Gas Turbines Ltd Chambre de combustion pour une turbine à gaz
EP1045203A1 (fr) * 1999-04-16 2000-10-18 Entreprise Generale De Chauffage Industriel Pillard Brûleur à plusieurs combustibles

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3520781A1 (de) * 1985-06-10 1986-12-11 Stubinen Utveckling AB, Stockholm Verfahren und vorrichtung zum verbrennen fluessiger und/oder fester brennstoffe in pulverisierter form
US4644878A (en) * 1985-11-05 1987-02-24 The United States Of America As Represented By The United States Department Of Energy Slurry burner for mixture of carbonaceous material and water
GB2187835B (en) * 1986-03-14 1989-12-20 Laurie Edward Helyer Pulverised fuel burner
WO1990003538A1 (fr) * 1988-09-19 1990-04-05 Regents Of The University Of Minnesota Enceinte de confinement dynamique
JP2776572B2 (ja) * 1989-07-17 1998-07-16 バブコツク日立株式会社 微粉炭バーナ
US5178533A (en) * 1989-10-04 1993-01-12 Enterprise Generale De Chauffage Industries Pillard Process for exploiting a burner and burners for a rotary tubular furnance
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FI840166A0 (fi) 1984-01-17
DK19984D0 (da) 1984-01-17
CA1224089A (fr) 1987-07-14
EP0114062A3 (fr) 1986-02-19
FI840166A7 (fi) 1984-07-19
US4569295A (en) 1986-02-11
DK19984A (da) 1984-07-19
US4718359A (en) 1988-01-12
AU557542B2 (en) 1986-12-24
AU2356084A (en) 1984-07-19

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