EP0745809B1 - Générateur de tourbillons pour chambre de combustion - Google Patents

Générateur de tourbillons pour chambre de combustion Download PDF

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Publication number
EP0745809B1
EP0745809B1 EP96810314A EP96810314A EP0745809B1 EP 0745809 B1 EP0745809 B1 EP 0745809B1 EP 96810314 A EP96810314 A EP 96810314A EP 96810314 A EP96810314 A EP 96810314A EP 0745809 B1 EP0745809 B1 EP 0745809B1
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EP
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Prior art keywords
combustion chamber
chamber according
duct
flow
vortex
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EP96810314A
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German (de)
English (en)
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EP0745809A1 (fr
Inventor
Burkhard Dr. Schulte-Werning
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General Electric Technology GmbH
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Alstom Technology AG
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    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/20—Heat transfer, e.g. cooling
    • F05B2260/221—Improvement of heat transfer
    • F05B2260/222—Improvement of heat transfer by creating turbulence
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes

Definitions

  • the present invention relates to a combustion chamber according to the preamble of claim 1. It also relates to a method for operating such a combustion chamber.
  • the flow over the respective burners and in the mixing zone in front of the turbine must be adjusted to the temperature profile suitable for the turbine by admixing the mass flow not flowing through the burners.
  • the quality of this admixture is usually controlled by the dimensioning of the cross section and the number of air inlet openings.
  • These air inlet openings which also act as mixed air nozzles, simultaneously provide both the necessary penetration depth of the air flowing through and colder into the hot gas flow and thus produce the necessary for rapid mixing macroscopic turbulence and for a sufficient uniform distribution of colder air supply through the combustion chamber wall.
  • the invention aims to remedy this situation.
  • the invention as characterized in the claims, the object is based on a combustion chamber and a method of the type mentioned to improve the Zumischungsproof and reducing the caloric load of the combustion chamber to achieve at the same time should be task of the invention, minimizing the pollutant Emissions and maximizing efficiency.
  • vortex-generating elements hereinafter referred to as vortex generators, which are preferably fixed to the combustion chamber wall or the combustion chamber walls in the mixing section, downstream of the primary zone.
  • vortex generators serve to generate the necessary intensive, large-scale mixing movement between hot gases and the mixing air to be mixed in the form of a secondary flow, which, in contrast to the usual procedure, behave independently of the mixed air jet.
  • the mixed air is now uniformly supplied to the hot gas via a number of small holes in the combustion chamber wall, that a supercritical blow-off rate is sought, which simultaneously ensures effusion cooling. Due to the desired supercritical blow-off rate, the mixed air penetrates into the edge zones of the vortexes which are induced by the vortex generators, is carried away by the vortexes from the wall and accordingly mixes rapidly with the hot gases. Since the vortex generators are exposed directly to the hot gases, the achievable sufficient cooling is an indispensable prerequisite of such a mixing section.
  • the effusion cooling effect is mainly due to the internal convective cooling during the passage of the mixed air through the flow openings and the possible formation of a cooling air film on the hot gas side. If the ratio between the pulse of the mixed air jet and that of the hot gas flow is small enough, the flow boundary layer of the mixed air will not be pierced on the hot gas side and a cooling air film may be formed optimally. If this blow-off rate exceeds a critical value, then the mixed-air jet penetrates into the hot-gas flow without the formation of a cooling-air film. With a suitable design, the wall-internal cooling effect increases at the same time as the blow-off rate increases, so that the overall cooling effect can be kept approximately constant.
  • the penetration depth of the mixed air jet into the hot gas flow near the vortex generators can be kept small, at least an order of magnitude smaller than in the conventional air inlet openings, since they only have to be so large that the mixed air penetrates into the vortex, but not the mixed air jet itself must provide for the necessary large-scale turbulence. Therefore, no large diameter are required and the supply of mixed air can be made over a large area.
  • the proposed mixing section can also be adapted to different load conditions of the gas turbine. If the pressure gradient available for intervention is made variable, for example by means of an adjustable pre-throttle, then the mixed-air flow to be admixed can also be controlled. If the discharge rate changes from over- to the sub-critical range, a constant effect of the effusion cooling over a large load range is given despite large variation of the mixed air flow. In this way, both the air to be admixed is supplied over a large area to the mixing process and thus overall the mixing quality is increased, as well as the wall of the mixing section is protected from excessively high temperatures, regardless of the mixing performance.
  • variable mixing section can be used both in the conventional diffusion and Vormischbrennhuntn as well as in combustion chamber concepts with staged combustion.
  • Fig. 1 shows, as is apparent from the indicated shaft axis 15, that it is a combustion chamber to an annular combustion chamber 100, which has substantially the shape of a contiguous annular or quasi-annular cylinder.
  • a combustion chamber can also consist of a number of axially, quasi-axially or helically arranged and individually self-contained combustion chambers.
  • the combustion chamber can also consist of a single Tube exist.
  • this combustion chamber may be the sole combustion stage of a gas turbine or a combustion stage of a sequentially fired gas turbine.
  • the annular combustion chamber 100 according to Fig.
  • a secondary stage 3 which is preferably designed as an inflow to a turbine.
  • the burner and the fuel supply and the primary air supply are placed substantially at the beginning of the primary zone 1 and are present in the present Fig. 1 symbolized with arrow 13.
  • the primary zone 1 is covered with a spaced concentric tube 11; In between flows in the counterflow direction, a cooling air amount 12, which ensures a convective cooling of the primary zone 1. This air can then pass through the burners after completion of the run, for example.
  • the various forms, effects and arrangements of the vortex generators 200 will be discussed in more detail below.
  • the mixing section 2 is surrounded by a chamber 10, in which a mixed air 8 flows through control elements 9 and then there distributed over the various openings in the inner wall 6 and outer wall 5 and by the vortex generators 200 to subsequently in to flow the mixing section 2.
  • the openings mentioned are, for example, in FIGS. 8, 10, 12, 14 and 15 visible; These figures will be explained below in more detail.
  • the mixed air 8 is in itself of a larger amount, for example up to 50% or more of the total mass flow.
  • the blow-off rate in the mixing section 2 is supercritical, which is why a cooling film can not form along the walls 5, 6 per se.
  • the possible mixed air 8 drops significantly, which is why the amount of hot gas stream 4 then increases.
  • a supercritical blow-off rate is intended as intended, because then the mixed air 8 penetrates into the edge zones of the vertebrae triggered by the vortex generators 200 arranged there. As a result of these vortices, the incoming mixed air 8 is carried away by the walls 5, 6, whereby it mixes rapidly with the hot gases 4 flowing through the combustion chamber 100. All-round openings through the vortex generators 200 (See below Fig. 15 In addition, a sufficient cooling of the latter against the hot gases 4. The supercritical blow-out rate also ensures that the penetration depth of the mixed air 8 into the hot gases 4 in the area of the vortex generators 200 can be kept small.
  • the openings also have no large cross section resp. Diameter, wherein the introduction of the mixed air 8 within the mixing section 2 can be made over a large area.
  • the vertical connecting edge (see 4-7, pos. 216) of the vortex generators 200 also forms the transition from the mixing section 2 to the secondary stage 3, whereby here a constriction of the mixing zone 2 results, which then leads to an immediate jump in cross section 14 at the beginning of the secondary stage. 3 leads.
  • the variable distribution of the mass flows 4, 8 causes depending on the load condition of the system, the cooling effect of the mixed air 8 when passing through the wall either by the heat transfer in the interior Openings alone or by a combination with the cooling film is achieved.
  • the first case is a supercritical case with high mass flow and high admission pressure
  • the second case is a subcritical case with low mass flow and low admission pressure.
  • the mixing configuration thus formed is variable in the sense that the mixed air stream 8 may be heavily load-dependent, without overheating of the material, in particular the vortex generators 200 and the walls 5, 6, occurs.
  • the design criterion for the injection geometry is accordingly a cooling efficiency that is only slightly dependent on the mixed air flow 8 over a relatively large range.
  • Such a so concepulated mixing section 2 finds both their application in staged combustion and in burners, which is about being able to drive despite a changed load with constant fuel-air ratio.
  • Fig. 2 is a section of the section plane II-II of Fig. 1 and shows a configuration of vortex generators 200 which are fixed to both the outer wall 5 and the inner wall 6. They are adjacent to each other in the circumferential direction, wherein the flow of the hot gases 4 is given by the free space from the radial spacing of the opposite tips of the vortex generators 200 and from the spaces between the free-flowing surfaces.
  • the curved lines shown in this figure are intended to depict the vortices induced by the vortex generators 200.
  • Fig. 3 corresponds largely Fig. 2 , where here the vortex generators 200 are fixed only to the inner wall 6.
  • a vortex generator 200, 201, 202 consists essentially of three freely flowing around triangular surfaces. These are a roof surface 210 and two side surfaces 211 and 213. In their longitudinal extent, these surfaces extend at certain angles in the flow direction.
  • the side walls of the vortex generators 200, 201, 202, which preferably consist of right-angled triangles, are fixed with their longitudinal sides at least on the already mentioned channel wall 6, preferably gas-tight. They are oriented so that they form a shock on their narrow sides, including a sweep angle ⁇ .
  • the joint is designed as a sharp connecting edge 216 and is perpendicular to each channel wall 5, 6, with which the side surfaces are flush.
  • the two side surfaces 211, 213 enclosing the sweep angle ⁇ are in Fig. 4 symmetrical in shape, size and orientation, they are arranged on both sides of a symmetry axis 217, which is rectified as the channel axis.
  • the roof surface 210 rests against the same channel wall 6 as the side surfaces 211, 213 with a very narrow edge 215 extending transversely to the through-flow channel. Its longitudinal edges 212, 214 are flush with the longitudinal edges of the side surfaces 211 projecting into the flow channel , 213.
  • the roof surface 210 extends at an angle of incidence ⁇ to the channel wall 6, the longitudinal edges 212, 214 together with the connecting edge 216 a tip 218.
  • the vortex generator 200, 201, 202 may also be provided with a bottom surface, with which he on suitable manner is attached to the channel wall 6.
  • a floor surface is not related to the mode of action of the element.
  • the operation of the vortex generator 200, 201, 202 is as follows: As the edges 212 and 214 flow around, the main flow is converted into a pair of opposing vortices, as schematically outlined in the figures.
  • the vortex axes lie in the axis of the main flow.
  • the swirl number and the location of vortex breakdown, if the latter is desired, are determined by appropriate choice of the angle of attack e and the arrow angle ⁇ . With increasing angles, the vorticity or swirl number is increased, and the location of the vortex shedding shifts upstream into the area of the vortex generator 200, 201, 202 itself.
  • these two angles ⁇ and ⁇ are determined by structural conditions and by the Process itself specified.
  • the connecting edge 216 of the two side surfaces 211, 213 forms the downstream edge of the vortex generator 200.
  • the edge 215 of the roof surface 210 extending transversely to the through-flow channel is thus the edge first acted on by the channel flow.
  • Fig. 5 is a so-called half "vortex generator" based on a vortex generator Fig. 4 shown.
  • the vortex generator 201 shown here only one of the two side surfaces is provided with the sweep angle ⁇ / 2. The other side surface is straight and aligned in the flow direction.
  • the symmetrical vortex generator here only a vortex is generated on the swept side, as symbolized in the figure. Accordingly, downstream of this vortex generator no vortex-neutral field is present, but the flow is forced to a total spin.
  • Fig. 6 is different Fig. 4 in so far as the sharp connecting edge 216 of the vortex generator 202 is the point which is first acted upon by the channel flow. The element is therefore rotated by 180 °. As can be seen from the illustration, the two opposing vortices have changed their sense of rotation.
  • Fig. 7 shows the basic geometry of a built-in mixing section 2 vortex generator 200.
  • the height h of the connecting edge 216 with the channel height H, or the height of the channel part, which is associated with the vortex generator vote so that the generated vortex immediately downstream the vortex generator 200 already reached such a size, such that thus the full channel height H is filled.
  • Another criterion that can influence the ratio of the two heights h / H to be selected is the pressure drop which occurs when the vortex generator 200 flows around. It is understood that with a higher ratio h / H and the pressure loss coefficient increases.
  • the vortex generators 200, 201, 202 are mainly and preferably used where it comes to mixing two streams together.
  • the main flow 4 as hot gases attacks the transverse edge 215 in the direction of the arrow, and the connecting edge 216, respectively.
  • the mixed air 8 (cf. Fig. 1 ) has an amount up to 50% and more of the main flow 4. This mixed air flow 8 is introduced in the present case upstream and downstream of the vortex generator and by the vortex generators themselves in the main flow 4, as is apparent from Fig. 1 especially good.
  • the vortex generators are placed flush with each other; Of course, these vortex generators can be distributed at a distance from each other over the circumference of the mixing section 2. For the choice of geometry, number and arrangement of the vortex generators, the vortex to be generated is decisive.
  • FIGS. 8-15 show more vortex generators with different configurations in terms of flow openings or holes for the inflow of mixed air into the Mainstream.
  • these passages may also be used to introduce a further or different medium, for example a fuel, into the mixing section.
  • Fig. 10 shows channel wall bores 220, which are located downstream of the vortex generators, and further wall bores 221, which are located immediately adjacent to the side surfaces 211, 213 and in the longitudinal extent in the same channel wall 6, to which the vortex generators are fixed.
  • the introduction of the mixed air flow through the wall bores 221 gives the generated vortices an additional impulse and cooling effect, which prolongs the life of the vortex generator.
  • the mixed air flow is injected via a slot 222 or via wall bores 223, both provisions being located directly in front of the edge 215 of the roof surface 210 running transversely to the flow-through channel and in its longitudinal extent in the same duct wall 6 on which the vortex generators are arranged.
  • the geometry of the wall bores 223 or of the slit 222 is selected such that the mixed air, if necessary another medium, is introduced into the main flow 4 at a certain injection angle and largely shields the downstream vortex generator as a protective film against the hot main flow 4 by flow around.
  • the mixed air flow is as shown Fig. 1 visible, introduced into the hollow interior of the vortex generators. This provides, without providing further dispositives, the desired mixing mechanism with respect to the main flow 4 as well as the eminently important cooling possibility for the vortex generators themselves.
  • Fig. 11 the mixed air flow is injected through holes 224 which occupy the roof surface 210, wherein the inflow of the mixed air flow transversely to the channel through which flows. to the edge 215 happens.
  • the cooling of the vortex generator takes place here more externally than internally.
  • the exiting mixed air flow unfolds at subcritical blow-off rate when flowing around the roof surface 210 a shielding this against the hot main flow 4 protective layer, otherwise, at supercritical Ausblasrate, the mixing effect, as under Fig. 1 has been described.
  • the mixed air flow is injected via bores 225, which are arranged staggered within the roof surface 210 at least along the symmetry line 217.
  • the channel walls 6 are particularly well protected from the hot main flow 4, since the mixed air flow is first introduced at the outer periphery of the vortex.
  • the mixed air flow is injected via bores 226 located at least in the longitudinal edges 212, 214 of the roof surface 210.
  • This solution ensures good cooling of the vortex generator, since the mixed air flow exits at the extremities and thus completely surrounds the inner walls of the element.
  • the mixed air flow is here introduced directly into the resulting vortex, which leads to a defined mixture within the main flow at supercritical blow-off rate.
  • Fig. 14 happens the injection of the mixed air flow through holes 227, which are located in the side surfaces 211 and 213, on the one hand in the region of the longitudinal edges 212 and 214, on the other hand, in the region of the connecting edge 216.
  • This variant is similar effect as those from Fig. 8 (Holes 221) and off Fig. 13 (Holes 226).

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Claims (15)

  1. Chambre de combustion, constituée essentiellement d'une zone primaire (1), d'un étage secondaire (3) monté en aval dans la direction d'écoulement, les deux étages (1, 3) étant parcourus par un écoulement principal (4) et étant en liaison fonctionnelle l'un avec l'autre en vue de la combustion, caractérisée en ce qu'entre la zone primaire et l'étage secondaire est disposée une section de mélange (2), en ce que la section de mélange est munie de générateurs de tourbillons (200, 201, 202) qui pénètrent dans la section de mélange (2) en réduisant sa section transversale, et en ce que la section de mélange et les générateurs de tourbillons présentent des ouvertures de passage (220, 221, 223 ; 225, 226, 227) par le biais desquelles une quantité d'air de mélange (8) peut être injectée dans l'écoulement principal (4).
  2. Chambre de combustion selon la revendication 1, caractérisée en ce qu'un générateur de tourbillon (200) présente trois surfaces librement parcourues par l'écoulement, qui s'étendent dans la direction de l'écoulement, dont une forme la surface de recouvrement (210) et les deux autres les surfaces latérales (211, 213), en ce que les surfaces latérales (211, 213) sont en affleurement avec un même segment de paroi du canal (2) et forment ensemble l'angle de flèche (α), en ce que la surface de recouvrement (210) s'applique avec une arête (215) s'étendant transversalement au canal (2) parcouru par l'écoulement, contre le même segment de paroi (5, 6) du canal (2) que les surfaces latérales (211, 213), et en ce que les arêtes orientées longitudinalement (212, 214) de la surface de recouvrement (210) sont en affleurement avec les arêtes orientées longitudinalement des surfaces latérales (211, 213), pénétrant dans le canal, et s'étendent suivant un angle d'inclinaison (θ) par rapport au segment de paroi (5) du canal.
  3. Chambre de combustion selon la revendication 2, caractérisée en ce que les deux surfaces latérales (211, 213) du générateur de tourbillon (200) formant l'angle de flèche (α) sont disposées symétriquement par rapport à un axe de symétrie (217).
  4. Chambre de combustion selon la revendication 2, caractérisée en ce que les deux surfaces latérales (211, 213) formant l'angle de flèche (α, α/2) forment l'une avec l'autre une arête de connexion (216) qui forme avec les arêtes (212, 214) orientées longitudinalement de la surface de recouvrement (210), une pointe (218) et en ce que l'arête de connexion (216) se situe dans la radiale du canal (2).
  5. Chambre de combustion selon la revendication 4, caractérisée en ce que l'arête de connexion (216) et/ou les arêtes (212, 214) orientées longitudinalement de la surface de recouvrement (210) sont au moins approximativement vives.
  6. Chambre de combustion selon les revendications 1, 2, 3, 4, caractérisée en ce que l'axe de symétrie (217) du générateur de tourbillon (200) s'étend parallèlement à l'axe du canal, en ce que l'arête de connexion (216) des deux surfaces latérales (211, 213) forme l'arête aval du générateur de tourbillon (200), et en ce que l'arête (215) de la surface de recouvrement (210) s'étendant transversalement au canal (2) parcouru par l'écoulement est l'arête sollicitée en premier par l'écoulement principal (4).
  7. Chambre de combustion selon les revendications 1 et 4, caractérisée en ce que l'arête de connexion (216) forme la transition entre la section de mélange (2) et l'étage secondaire (3).
  8. Chambre de combustion selon l'une quelconque des revendications 1 à 7, caractérisée en ce que le générateur de tourbillon (220, 201, 202) présente des ouvertures de passage (225, 226, 227) intégralement sur toutes les surfaces (210, 211, 213) et sur l'arête de connexion (216).
  9. Chambre de combustion selon la revendication 1, caractérisée en ce que le rapport entre la hauteur (h) du générateur de tourbillon (200) et la hauteur (H) du canal (2) est choisi de telle sorte que le tourbillon produit remplisse directement en aval du générateur de tourbillon (200) toute la hauteur (H) du canal (2) et toute la hauteur (h) de la partie du canal associée au générateur de tourbillon (200).
  10. Chambre de combustion selon la revendication 1, caractérisée en ce que la chambre de combustion est une chambre de combustion annulaire.
  11. Chambre de combustion selon la revendication 1, caractérisée en ce que la section du côté de la sortie de l'écoulement des générateurs de tourbillons (200, 201, 202) est réalisée en forme de venturi, et en ce qu'un combustible supplémentaire peut être injecté dans la région de la constriction maximale de la section en forme de venturi.
  12. Chambre de combustion selon la revendication 1, caractérisée en ce que les générateurs de tourbillon (200, 201, 202) sont fixés au moins à une paroi de canal (5, 6) de la section de mélange (2).
  13. Chambre de combustion selon la revendication 1, caractérisée en ce que la zone primaire (1) est disposée en aval des turbomachines et l'étage secondaire (3) en amont.
  14. Chambre de combustion selon la revendication 13, caractérisée en ce que la turbomachine en aval de l'étage secondaire (3) est une turbine.
  15. Procédé pour faire fonctionner une chambre de combustion selon la revendication 1, qui se compose essentiellement d'une zone primaire, d'un étage secondaire monté en aval dans la direction de l'écoulement, les deux étages étant en liaison fonctionnelle l'un avec l'autre en vue de la combustion, caractérisé en ce qu'un air de mélange (8) est injecté dans un écoulement principal (4) dans une section de mélange (2) disposée entre la zone primaire (1) et l'étage secondaire (3), en ce que la quantité de cet air de mélange (8) par rapport à l'écoulement principal (4) dans le cas d'un taux de soufflage sur-critique ne pénètre que dans le tourbillon produit par les générateurs de tourbillons (200, 201, 202), et en ce que dans le cas d'un taux de soufflage sous-critique, un refroidissement par film est déclenché au moins le long de la section de mélange (2).
EP96810314A 1995-06-02 1996-05-17 Générateur de tourbillons pour chambre de combustion Expired - Lifetime EP0745809B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19520291A DE19520291A1 (de) 1995-06-02 1995-06-02 Brennkammer
DE19520291 1995-06-02

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EP0745809A1 EP0745809A1 (fr) 1996-12-04
EP0745809B1 true EP0745809B1 (fr) 2008-11-12

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US (1) US5735126A (fr)
EP (1) EP0745809B1 (fr)
JP (1) JPH0914603A (fr)
CN (1) CN1244766C (fr)
DE (2) DE19520291A1 (fr)

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US5850732A (en) * 1997-05-13 1998-12-22 Capstone Turbine Corporation Low emissions combustion system for a gas turbine engine
EP0999367B1 (fr) 1998-11-06 2003-02-12 ALSTOM (Switzerland) Ltd Conduit d'écoulement à discontinuité de section transversale
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JPH0914603A (ja) 1997-01-17
CN1244766C (zh) 2006-03-08
DE59611488D1 (de) 2008-12-24
US5735126A (en) 1998-04-07
EP0745809A1 (fr) 1996-12-04
CN1160150A (zh) 1997-09-24

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