EP0623786B1 - Chambre de combustion - Google Patents

Chambre de combustion Download PDF

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Publication number
EP0623786B1
EP0623786B1 EP94103551A EP94103551A EP0623786B1 EP 0623786 B1 EP0623786 B1 EP 0623786B1 EP 94103551 A EP94103551 A EP 94103551A EP 94103551 A EP94103551 A EP 94103551A EP 0623786 B1 EP0623786 B1 EP 0623786B1
Authority
EP
European Patent Office
Prior art keywords
channel
combustion chamber
vortex
vortex generators
chamber according
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
EP94103551A
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German (de)
English (en)
Other versions
EP0623786A1 (fr
Inventor
Rolf Dr. Althaus
Alexander Dr. Beeck
Yau-Pin Dr. Chyou
Adnan Eroglu
Burkhard Dr. Schulte-Werning
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 Asea Brown Boveri Ltd
Asea Brown Boveri AB
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Filing date
Publication date
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Publication of EP0623786A1 publication Critical patent/EP0623786A1/fr
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Classifications

    • 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
    • F23D11/408—Flow influencing devices in the air tube
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/30—Injector mixers
    • B01F25/31—Injector mixers in conduits or tubes through which the main component flows
    • B01F25/313—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit
    • B01F25/3131—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced in the centre of the conduit with additional mixing means other than injector mixers, e.g. screens, baffles or rotating elements
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/4317—Profiled elements, e.g. profiled blades, bars, pillars, columns or chevrons
    • B01F25/43171—Profiled blades, wings, wedges, i.e. plate-like element having one side or part thicker than the other
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/43197—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor characterised by the mounting of the baffles or obstructions
    • B01F25/431971—Mounted on the wall
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/434—Mixing tubes comprising cylindrical or conical inserts provided with grooves or protrusions
    • 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
    • F15D1/02—Influencing flow of fluids in pipes or conduits
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/40—Static mixers
    • B01F25/42—Static mixers in which the mixing is affected by moving the components jointly in changing directions, e.g. in tubes provided with baffles or obstructions
    • B01F25/43—Mixing tubes, e.g. wherein the material is moved in a radial or partly reversed direction
    • B01F25/431—Straight mixing tubes with baffles or obstructions that do not cause substantial pressure drop; Baffles therefor
    • B01F25/4317—Profiled elements, e.g. profiled blades, bars, pillars, columns or chevrons

Definitions

  • the invention relates to a combustion chamber according to the preamble of patent claim 1.
  • a delta wing that is employed in a channelized flow can be regarded as a vortex generator in the broadest sense. If such wings are flown from the tip, a dead water area is created on the one hand downstream of the wing, and on the other hand the flow through the employed surface experiences a not inconsiderable drop in pressure.
  • the arrangement of such a delta wing in a channel must be carried out using flow-restricting aids such as struts, ribs or the like.
  • problems arise with the cooling of such elements in a hot gas flow for example.
  • Such delta wings cannot be used as mixing elements of two or more flows.
  • the mixing of a secondary flow with a main flow present in a channel usually takes place by radial injection of the secondary flow into the channel.
  • the momentum of the secondary flow is so small, however, that an almost complete mixing only takes place after a distance of approx. 100 channel heights.
  • a combustion chamber of the type mentioned at the outset is known from EP-0 521 788 A1.
  • a main flow is led outside around vortex generators, several of which are arranged next to one another over the circumference of the flowed-through channel. These vortex generators expand in the direction of flow and their height is at least 50% of the height of the flowed channel.
  • a secondary flow is conducted into the vortex generators at the upstream end and mixed with fuel therein.
  • a first combustion takes place within the vortex generators.
  • the smoke gases emerge into the channel and swirl in the main flow around the vortex generators to form a lean combustion mixture.
  • the invention is therefore based on the object of equipping a combustion chamber of the type mentioned at the outset with a device with which longitudinal vortices can be generated in the flowed-through channel without a recirculation area.
  • the new static mixer which is represented by the 3-dimensional vortex generators, it is possible to achieve extraordinarily short mixing distances in the combustion chamber with a low pressure drop.
  • a coarse mixing of the two streams takes place after just one full vortex revolution, while a fine mixing due to turbulent flow and molecular diffusion processes occurs after a distance that corresponds to a few channel heights.
  • the advantage of such an element can be seen in its particular simplicity in every respect.
  • the element consisting of three walls with flow around it is completely problem-free.
  • the roof surface can be joined with the two side surfaces in a variety of ways.
  • the element can also be fixed to flat or curved channel walls in the case of weldable materials by simple weld seams. From a fluidic point of view, the element has a very low pressure drop when flowing around and it creates vortices without a dead water area.
  • the element due to its generally hollow interior, the element can be cooled in a variety of ways and with various means.
  • the two side surfaces enclosing the arrow angle ⁇ form an at least approximately sharp connecting edge with one another, which together with the longitudinal edges of the roof surface forms a tip, the flow cross-section is hardly impaired by blocking.
  • the sharp connecting edge is the exit-side edge of the vortex generator and it runs perpendicular to the channel wall with which the side surfaces are flush, the non-formation of a wake area achieved thereby is advantageous.
  • a vertical connecting edge also leads to side surfaces that are also perpendicular to the channel wall, which gives the vortex generator the simplest possible form that is most favorable in terms of production technology.
  • the angle of attack ⁇ of the roof surface and / or the arrow angle ⁇ of the side surfaces are selected such that the vortex generated by the flow bursts in the region of the vortex generator.
  • FIGS. 1, 5 and 6 do not show the actual channel through which a main flow symbolized by a large arrow flows.
  • a vortex generator essentially consists of three free-flowing triangular surfaces. These are a roof surface 10 and two side surfaces 11 and 13. In their longitudinal extent, these surfaces run at certain angles in the direction of flow.
  • the two side surfaces 11 and 13 are perpendicular to the channel wall 21, it being noted that this is not mandatory.
  • the side walls which consist of right-angled triangles, are fixed with their long sides on this channel wall 21, preferably gas-tight. They are oriented so that they form a joint on their narrow sides, including an arrow angle ⁇ .
  • the joint is designed as a sharp connecting edge 16 and is also perpendicular to the channel wall 21 with which the side surfaces are flush.
  • the two side surfaces 11, 13 including the arrow angle ⁇ are symmetrical in shape, size and orientation and are arranged on both sides of an axis of symmetry 17 (FIGS. 3b, 4b). This axis of symmetry 17 is rectified like the channel axis.
  • the roof surface 10 lies against the same channel wall 21 as the side walls 11, 13 with an edge 15 which runs across the channel and is very pointed.
  • the vortex generator can also be provided with a bottom surface with which it is fastened in a suitable manner to the channel wall 21.
  • a floor area is not related to the mode of operation of the element.
  • the connecting edge 16 of the two side surfaces 11, 13 forms the downstream edge of the vortex generator.
  • the edge 15 of the roof surface 10 which runs transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • the vortex generator works as follows: When flowing around edges 12 and 14, the main flow is converted into a pair of opposing vortices. Their vortex axes lie in the axis of the main flow. The number of swirls and the location of the vortex breakdown (if the latter is desired at all) are determined by appropriate selection of the angle of attack ⁇ and the arrow angle ⁇ . With increasing angles, the vortex strength or the number of swirls is increased and the location of the vortex bursting moves upstream into the area of the vortex generator itself. Depending on the application, these two angles ⁇ and ⁇ are predetermined by the structural conditions and by the process itself. Only the length L of the element (FIG. 3b) and the height h of the connecting edge 16 (FIG. 3a) then have to be adjusted.
  • FIGS. 3a and 4a in which the channel through which flow is indicated is 20, it can be seen that the vortex generator can have different heights compared to the channel height H.
  • the height h of the connecting edge 16 will be coordinated with the channel height H in such a way that the vortex generated immediately downstream of the vortex generator already has such a size that the full channel height H is filled, which results in a uniform velocity distribution in the applied Cross section leads.
  • Another criterion that can influence the ratio h / H to be selected is the pressure drop that occurs when the vortex generator flows around. It goes without saying that the pressure loss coefficient also increases with a larger ratio h / H.
  • the sharp connecting edge 16 in FIG. 2 is the point which is first acted upon by the channel flow.
  • the element is rotated by 180 °.
  • the two opposite vortices have changed their sense of rotation.
  • Fig. 3 it is shown how several, here 3 vortex generators are arranged side by side without gaps across the width of the flow channel 20.
  • the channel 20 has a rectangular shape in this case, but this is not essential to the invention.
  • FIG. 4 An embodiment variant with two full and two half vortex generators adjoining it on both sides is shown in FIG. 4.
  • the elements differ in particular by their greater height h. If the angle of attack remains the same, this inevitably leads to a greater length L of the element and consequently - because of the same division - to a smaller arrow angle ⁇ .
  • the vortices generated will have a lower swirl strength, but will fill the channel cross section completely within a shorter interval. If in In both cases a vortex burst is intended, for example to stabilize the flow, this will take place later in the vortex generator according to FIG. 4 than in that according to FIG. 3.
  • the channels shown in FIGS. 3 and 4 represent rectangular combustion chambers. It is pointed out once again that the shape of the channel through which the flow passes is not essential for the mode of operation of the invention. Instead of the rectangle shown, the channel could also be a ring segment, i.e. the walls 21a and 21b would be curved. In such a case, the above statement that the side surfaces are perpendicular to the channel wall must of course be relativized. It is important that the connecting edge 16 lying on the line of symmetry 17 is perpendicular to the corresponding wall. In the case of annular walls, the connecting edge 16 would thus be aligned radially, as is shown in FIG. 7.
  • FIGS. 7 and 8 show in simplified form a combustion chamber with an annular flow through channel 20.
  • an equal number of vortex generators are lined up in the circumferential direction in such a way that the connecting edges 16 of two opposite vortex generators lie in the same radial .
  • FIG. 7 shows that the vortex generators on the inner channel ring 21b have a smaller arrow ⁇ .
  • ⁇ In the longitudinal section in FIG. 8 it can be seen that this could be compensated for by a larger angle of attack ⁇ if swirl-like vortices in the inner and outer ring cross-section are desired.
  • two vortex pairs are generated, each with smaller vertebrae, which leads to a shorter mixing length.
  • the fuel could be in this version according to the methods of 5 or 6 to be described later are introduced into the main flow.
  • the secondary flow in the form of a liquid fuel, for example, has a substantially smaller mass flow than the main flow. It is introduced vertically into the main flow in the immediate area of the vortex generators.
  • this injection takes place via individual bores 22a, which are made in the wall 21a.
  • the wall 21a is the wall on which the vortex generators are arranged.
  • the bores 22a are located on the line of symmetry 17 downstream behind the connecting edge 16 of each vortex generator. With this configuration, the fuel is fed into the already existing large-scale vortices.
  • FIG. 4 shows an embodiment variant of a combustion chamber in which the secondary flow is also injected via wall bores 22b. These are located downstream of the vortex generators in that wall 21b on which the vortex generators are not arranged, that is to say on the wall opposite the wall 21a.
  • the wall bores 22b are each made centrally between the connecting edges 16 of two adjacent vortex generators, as can be seen in FIG. 4. In this way, the fuel reaches the vortex in the same way as in the embodiment according to FIG. 3, but with the difference that it is no longer mixed into the vortex of a pair of vertebrae produced by the same vortex generator, but in one each Vortex of two neighboring vortex generators. Because the neighboring vortex generators Meanwhile, are arranged without a space and produce vortex pairs with the same direction of rotation, the injections according to FIGS. 3 and 4 have the same effect.
  • FIGS. 5 and 6 show further possible forms of introducing the secondary flow into the main flow.
  • the secondary flow is introduced here through means not shown through the channel wall 21 into the hollow interior of the vortex generator.
  • the secondary flow is injected into the main flow via a wall bore 22e, the bore being arranged in the region of the tip 18 of the vortex generator.
  • the injection takes place via wall bores 22d, which are located in the side surfaces 11 and 13 on the one hand in the region of the longitudinal edges 12 and 14 and on the other hand in the region of the connecting edge 16.
  • FIGS. 9 to 14 show different installation options for the vortex generators.
  • FIG. 9 shows an annular channel 20 in which an equal number of vortex generators 9 are lined up in the circumferential direction both on the outer ring wall 21a and on the inner ring wall 21b. 7, however, the connecting edges 16 of two opposite vortex generators are offset by half a division. This arrangement offers the possibility of increasing the height h of the individual element. Downstream of the vortex generators, the generated vortexes are combined with one another, which on the one hand improves the mixing quality and on the other hand leads to a longer lifespan of the vortex.
  • the ring channel is segmented by means of radially extending ribs 23.
  • a vortex generator 9 is arranged on the ribs 23 in each of the circular ring segments formed in this way.
  • the two vortex generators are designed to fill the entire channel height. This solution simplifies the fuel supply that can be made through the hollow ribs. This means that there is no impairment of the flow by centrally arranged fuel lances.
  • vortex generators are also attached to the ring walls 21a and 21b.
  • the connecting edges of the side elements run at half the channel height, those of the upper and lower in a radial at half the segment width. In terms of how it works, this is a very good solution.
  • the elements here cannot fill the entire channel height. It is therefore not to be overlooked that the cooling that may be required is structurally complex, since cooling air supply from the ring walls is not readily possible for the lateral elements.
  • the vortex generators 9 in FIG. 12 are arranged off-center on the radial ribs 23 and on the ring walls 21a, 21b.
  • One side surface of each vortex generator lies against a corner of the circular ring segment, from where the lateral vortex generators can also be supplied with cooling air from the radially outer ring wall 21a, on the one hand, and from the inner ring wall 21b, on the other hand.
  • FIG. 13 Another embodiment according to FIG. 13 is also in respect of a simple cooling possibility Segment of the circular channel, the vortex generators 9 are arranged directly in the segment corners.
  • FIGS. 6, 11 and 14 show an additional central introduction of the secondary flow in a mixed arrangement of the variants dealt with in FIGS. 6, 11 and 14.
  • the fuel usually oil
  • vortex generators of different geometries are used in the rectangular channel, which of course could just as well be a circular ring segment.
  • the vortex generators that follow one another in the “circumferential direction” are slightly offset from one another. This, for example, to create the required space for the lance.
  • the secondary flow is partially injected via wall holes in the side surfaces of the vortex generators, as indicated by arrows.
  • the gas supply takes place via gas lines 25 running along the wall.
  • gas lines 25 running along the wall.
  • the mixture is ignited 26 at the point at which the vortex bursts (vortex break down).
  • a diffuser 27 is arranged in the plane behind the mixing zone at which the ignition takes place. The good temperature distribution downstream of the vortex generators achieved as a result of the mixing elements avoids the risk of reignition, which is possible without the measure for introducing cooling air into the combustion air mentioned at the beginning.
  • the combustion chamber just described could also be a self-igniting post-combustion chamber downstream of a high-temperature gas turbine.
  • the high energy content of their exhaust gases enables self-ignition. Effective, rapid mixing of the hot gas flow with the injected fuel is a prerequisite for optimizing the combustion process, particularly with regard to minimizing emissions.
  • the vortex generators are designed in such a way that recirculation zones are largely avoided.
  • the residence time of the fuel particles in the hot zones is very short, which has a favorable effect on the minimal formation of NO x .
  • the injected fuel is dragged along by the vortices and mixed with the main flow. It follows the helical course of the vertebrae and is evenly finely distributed in the chamber downstream of the vertebrae. This reduces the risk of impinging jets on the opposite wall and the formation of so-called "hot spots" - in the case of the radial injection of fuel into an undisturbed flow mentioned above.
  • the fuel injection can be kept flexible and adapted to other boundary conditions. In this way, the same injection pulse can be maintained throughout the load range. Since the mixing is determined by the geometry of the vortex generators and not by the machine load, in the example the gas turbine output, the afterburner configured in this way works optimally even under partial load conditions.
  • the combustion process is optimized by adjusting the ignition delay time of the fuel and mixing time of the vortices, which ensures a minimization of emissions.
  • the effective mixing results in a good temperature profile over the cross section through which the flow is flowing and also reduces the possibility of the occurrence of thermoacoustic instability. Due to their presence alone, the vortex generators act as a damping measure against thermoacoustic vibrations.
  • FIGS. 16 and 17 show a top view of an embodiment variant of the vortex generator and a front view of its arrangement in a circular channel.
  • the two side surfaces 11 and 13 enclosing the arrow angle ⁇ have a different length.
  • the vortex generator then naturally has a different angle of attack stell across its width.
  • Such a variant has the effect that vortices with different strengths are generated. For example, this can act on a swirl adhering to the main flow. Or else through the different eddies it becomes original a swirl-free main flow downstream of the vortex generators, as indicated in FIG. 17.
  • Such a configuration works well as an independent, compact burner unit.
  • the swirl imposed on the main flow can be used to improve the cross-ignition behavior of the burner configuration, for example at partial load.
  • the invention is not limited to the examples described and shown. With regard to the arrangement of the vortex generators in the network, many combinations are possible without leaving the scope of the invention.
  • the introduction of the secondary flow into the main flow can also be carried out in a variety of ways.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Dispersion Chemistry (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)

Claims (20)

  1. Chambre de combustion, dans laquelle on injecte un combustible gazeux ou liquide en écoulement secondaire dans un écoulement principal gazeux canalisé, l'écoulement secondaire présentant un courant massique sensiblement plus petit que le courant principal,
    - et dans laquelle l'écoulement principal est conduit sur des générateurs de tourbillons (9), dont plusieurs sont disposés l'un à côté de l'autre sur la largeur ou sur le périmètre du canal parcouru (20), de préférence sans espaces intermédiaires, et dont la hauteur vaut au moins 50 % de la hauteur du canal parcouru ou de la partie du canal associée aux générateurs de tourbillons,
    - et dans laquelle l'écoulement secondaire est introduit dans le canal (20) à proximité immédiate des générateurs de tourbillons (9),
    caractérisée en ce qu'un générateur de tourbillons (9) présente trois faces librement balayées, qui s'étendent dans le sens de l'écoulement et dont l'une forme la face de toit (10) et les deux autres les faces latérales (11, 13), et en ce que les faces latérales (11, 13) sont raccordées à une même paroi de canal (21) et forment l'une avec l'autre l'angle de flèche (α).
  2. Chambre de combustion suivant la revendication 1, caractérisée en ce que
    - la face de toit (10) s'applique, avec une arête (15) orientée transversalement au canal parcouru (20), sur la même paroi de canal (21) que les faces latérales, et en ce que
    - les arêtes orientées longitudinalement (12, 14) de la face de toit, qui sont raccordées aux arêtes orientées longitudinalement des faces latérales (11, 13) et pénétrant dans le canal d'écoulement, forment un angle d'attaque (θ) avec la paroi de canal (21).
  3. Chambre de combustion suivant la revendication 2, caractérisée en ce que les deux faces latérales (11, 13) du générateur de tourbillons (9), qui forment l'angle de flèche (α), sont disposées symétriquement par rapport à un axe de symétrie (17).
  4. Chambre de combustion suivant la revendication 2, caractérisée en ce que les deux faces latérales (11, 13) du générateur de tourbillons (9), qui forment l'angle de flèche (α), présentent une longueur différente, de telle façon que la face de toit (10) s'applique, par une arête (15) orientée obliquement au canal parcouru (20), sur la même paroi de canal (21) que les parois latérales et présente un angle d'attaque (θ) différent sur la largeur du générateur de tourbillons (9).
  5. Chambre de combustion suivant la revendication 3, caractérisée en ce que les deux faces latérales (11, 13), qui forment l'angle de flèche (α), définissent l'une avec l'autre une arête de jonction (16), qui forme une pointe (18) avec les arêtes (12, 14) orientées longitudinalement de la face de toit (10), et en ce que l'arête de jonction est de préférence orientée perpendiculairement à la paroi de canal (21), à laquelle les faces latérales (11, 13) sont raccordées.
  6. Chambre de combustion suivant la revendication 3, caractérisée en ce que l'arête de jonction (16) et/ou les arêtes (12, 14) orientées longitudinalement de la face de toit (10) sont au moins approximativement des arêtes vives.
  7. Chambre de combustion suivant la revendication 3 et 5, caractérisée en ce que l'axe de symétrie (17) du générateur de tourbillons (9) est parallèle à l'axe du canal, l'arête de jonction (16) des deux faces latérales (11, 13) formant l'arête aval du générateur de tourbillons (9) et l'arête (15) de la face de toit (10), orientée transversalement au canal parcouru (20), étant l'arête atteinte en premier lieu par l'écoulement principal.
  8. Chambre de combustion suivant la revendication 2, caractérisée en ce que le canal est annulaire, en ce que la paroi du canal, sur laquelle une pluralité de générateurs de tourbillons (9) sont disposés en ligne en direction périphérique, est la paroi annulaire intérieure ou extérieure (21a, 21b) et en ce que l'écoulement secondaire est injecté par des trous de paroi (22a), dont chacun se trouve dans la ligne de symétrie (17), en aval immédiatement derrière l'arête de jonction (16), dans la paroi annulaire (21a, 21b), sur laquelle les générateurs de tourbillons (9) sont disposés. (Fig. 3).
  9. Chambre de combustion suivant la revendication 2, caractérisée en ce que le canal (20) est annulaire, en ce que la paroi du canal, sur laquelle une pluralité de générateurs de tourbillons sont disposés en ligne en direction périphérique, est la paroi annulaire intérieure et/ou extérieure (21a, 21b), et en ce que l'écoulement secondaire est injecté par des trous de paroi (22b), qui sont disposés en aval des générateurs de tourbillons, dans la paroi annulaire (21a, 21b) sur laquelle les générateurs de tourbillons (9) ne sont pas disposés, les trous de paroi (22b) étant chacun ménagés à mi-distance entre les arêtes de jonction (16) de deux générateurs de tourbillons voisins. (Fig. 4).
  10. Chambre de combustion suivant la revendication 2, caractérisée en ce que le canal (20) est annulaire, et en ce qu'un même nombre de générateurs de tourbillons (9) sont disposés en ligne en direction périphérique aussi bien à la paroi annulaire extérieure (21a) qu'à la paroi annulaire intérieure (21b), les arêtes de jonction (16) de deux générateurs de tourbillons (9) qui se font face mutuellement se trouvant sur la même radiale. (Fig. 7).
  11. Chambre de combustion suivant la revendication 2, caractérisée en ce que le canal (20) est annulaire, et en ce qu'un même nombre de générateurs de tourbillons (9) sont disposés en ligne en direction périphérique aussi bien à la paroi annulaire extérieure (21a) qu'à la paroi annulaire intérieure (21b), les arêtes de jonction (16) de deux générateurs de tourbillons (9) qui se font face mutuellement étant décalées d'un demi-pas l'une par rapport à l'autre. (Fig. 9).
  12. Chambre de combustion suivant la revendication 2, caractérisée en ce que le canal (20) est un canal annulaire circulaire segmenté au moyen de nervures radiales (23), au moins dans le plan dans lequel se trouvent les générateurs de tourbillons (9), un générateur de tourbillons (9) étant disposé dans chaque segment annulaire circulaire aux nervures radiales (23) et/ou aux parois annulaires (21a, 21b). (Fig. 10, 11).
  13. Chambre de combustion suivant la revendication 12, caractérisée en ce que les générateurs de tourbillons (9) sont disposés au milieu aux nervures radiales (23) et aux parois annulaires (21a, 21b). (Fig. 11).
  14. Chambre de combustion suivant la revendication 12, caractérisée en ce que les générateurs de tourbillons (9) sont disposés en position décentrée aux nervures radiales (23) et aux parois annulaires (21a, 21b), une face latérale (11, 13) de chaque générateur de tourbillons (9) étant placée dans un coin du segment annulaire circulaire. (Fig. 12).
  15. Chambre de combustion suivant la revendication 2, caractérisée en ce que le canal (20) est un canal annulaire circulaire segmenté au moyen de nervures radiales (23), au moins dans le plan dans lequel se trouvent les générateurs de tourbillons (9), un générateur de tourbillons (9) étant disposé dans chacun des coins dans chaque segment annulaire circulaire. (Fig. 13).
  16. Chambre de combustion suivant la revendication 2, caractérisée en ce que, parmi les générateurs de tourbillons (9) disposés en ligne avec leurs faces latérales à une paroi du canal, deux générateurs de tourbillons (9) voisins sont décalés l'un par rapport à l'autre dans la direction longitudinale du canal (20). (Fig. 14).
  17. Chambre de combustion suivant la revendication 5, caractérisée en ce que l'écoulement secondaire est injecté par des trous de paroi (22c, 22d), qui se trouvent dans les faces latérales (11, 13) du générateur de tourbillons (9) dans la région des arêtes orientées longitudinalement (12, 14) de la face de toit et/ou de l'arête de jonction (16). (Fig. 6).
  18. Chambre de combustion suivant la revendication 2, caractérisée en ce que l'écoulement secondaire est injecté par des trous de paroi (22e), qui se trouvent dans la région de la pointe (18) du générateur de tourbillons (9). (Fig. 5).
  19. Chambre de combustion suivant la revendication 2, caractérisée en ce que l'écoulement secondaire est injecté par des lances à combustible (24), dont les embouchures se trouvent en aval du générateur de tourbillons (9), dans la région de la pointe (18) de celui-ci. (Fig. 15).
  20. Chambre de combustion suivant la revendication 2, caractérisée en ce qu'il s'agit d'une chambre de combustion à combustion avec prémélange, dans laquelle un diffuseur (27) est disposé en aval des générateurs de tourbillons (9), dans le plan où se produit l'allumage par étincelles (26), pour la stabilisation de la flamme. (Fig. 15).
EP94103551A 1993-04-08 1994-03-09 Chambre de combustion Expired - Lifetime EP0623786B1 (fr)

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JP3527280B2 (ja) 2004-05-17
US5513982A (en) 1996-05-07
DE59402803D1 (de) 1997-06-26
EP0623786A1 (fr) 1994-11-09
JPH06323540A (ja) 1994-11-25

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