EP0743490B1 - Combustion chamber having a multitude of cooling holes which are inclined in varying axial and tangential directions - Google Patents

Combustion chamber having a multitude of cooling holes which are inclined in varying axial and tangential directions Download PDF

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Publication number
EP0743490B1
EP0743490B1 EP96400863A EP96400863A EP0743490B1 EP 0743490 B1 EP0743490 B1 EP 0743490B1 EP 96400863 A EP96400863 A EP 96400863A EP 96400863 A EP96400863 A EP 96400863A EP 0743490 B1 EP0743490 B1 EP 0743490B1
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EP
European Patent Office
Prior art keywords
orifices
zones
wall
axial
angle
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EP96400863A
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German (de)
French (fr)
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EP0743490A1 (en
Inventor
Denis Roger Henri Ansart
Patrick Samuel André Ciccia
Michel André Albert Desaulty
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Safran Aircraft Engines SAS
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Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/002—Wall structures
    • 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
    • F05B2250/30—Arrangement of components
    • F05B2250/32—Arrangement of components according to their shape
    • F05B2250/322—Arrangement of components according to their shape tangential
    • 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
    • F05B2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to a combustion chamber, in particular of a turbomachine, which is delimited by at least one wall axial provided with a plurality of through holes constituting a "multi-perforation" intended, in particular, for the passage of a refrigeration of said axial wall, and provided with a plurality of holes for dilution regularly distributed in a transverse plane compared to the general direction of the flow of burnt gases from the combustion, each orifice having a geometric axis inclined at an angle A relative to the normal to said wall, said genometric axis being arranged in a plane containing said normal which makes an angle B by relation to the plan defined by said normal and the general direction flue gas flow.
  • the cooling mode by multiperforation is known.
  • the orifices are generally staggered with a network of equidistant meshes.
  • EP-A-0 486 133 discloses a wall of this type, in which the orifices are inclined in axial planes.
  • EP-A-0 492 864 further reveals that the orifices are also inclined by a tangential angle B which generally coincides with the angle of the flue gas vortex along the internal surface of the wall.
  • EP-A-0 592 161 shows in FIG. 6 an annular wall multi-perforated combustion chamber in which the orifices are defined by an axial inclination A and a tangential angle B of in such a way that the flow of fresh air introduced into the room creates a protective crown of air which swirls around the flow of burnt gases.
  • 3D calculations show that the flow of gases in the combustion chamber is not always longitudinal, but only in some areas it is slightly tilted or even opposed to flow, especially downstream of the dilution holes. It can be produce detachments of cooling air in these areas.
  • the purpose of the present invention is to prevent the air from the multiperforation does not take off from the wall.
  • the present invention therefore proposes to locally orient the orifices according to the local flow of the burnt gases.
  • the wall is subdivided into several zones, in each of which the orifices are defined by inclinations A and angles B respectively having identical values and calculated as a function characteristics of the flue gas flow in each of said zones.
  • said wall is subdivided in particular into first zones located respectively downstream of the dilution holes, and in which the orifices are directed against the current of the general direction of the flue gas flow, second and third zones arranged on either side of said first zones with respect to axial planes passing through the corresponding dilution holes, and a fourth zone covering the rest of said wall.
  • the holes in the fourth zone have an inclination axial greater than 30. Their angle B is substantially equal to 0 °. The flow of fresh air from these holes licks the surface internal wall in the direction of the axial flow of the burnt gases.
  • the orifices made in the first zones diffuse a cooling air against the current of the general direction of flue gas flow.
  • Their tilt A is between 0 ° and -60 °, and their angle B is substantially equal to 0 °.
  • a second and a third zone are provided, of which the orifices diffuse cooling air towards the passing axial plane through the corresponding dilution hole and in the direction of the general flow of burnt gases.
  • the combustion chamber 1 of annular type, has a outer annular axial wall 2 and an annular axial wall interior 3, joined at their upstream ends by a chamber bottom 4 equipped with injection systems 5, and having between their ends downstream an annular opening 6 for the exhaust of the burnt gases G towards a turbine not shown in the drawings.
  • the burnt gases G circulate in the internal cavity 7 of the combustion chamber 1 according to an axial general direction represented by the arrow D.
  • outer 2 and inner 3 axial walls define with the outer casings 8 and inner 9 of the annular passages 10 and 11 in which circulates cooling air A coming from a compressor not shown in the drawings and located upstream of the combustion 1.
  • the two walls 2 and 3 are provided with a plurality of holes for dilution 12 regularly distributed in an axial plane 13 perpendicular to the axis of the turbomachine, and a plurality of through holes 14 constituting a multi-perforation.
  • Part of the cooling air A enters axially into the internal cavity 7 through the dilution holes 12 and participates in depletion and cooling of the combustion gases in the dilution zone of combustion chamber 1, while the rest of air A enters the internal cavity 7 through the orifices 14 in order to form a cooling film on internal faces 2a and 3a of the walls axial 2 and 3.
  • Figure 2 shows the gas velocity diagram at vicinity of the internal face 2a of the external wall 2, in the region of two dilution holes 12a and 12b, this diagram having been obtained by 3D calculations.
  • This diagram shows that in zone 15 which separates the two dilution holes 12a and 12b, the gases flow in the direction D.
  • zones 16 located immediately downstream of the dilution 12a and 12b the gases flow on the contrary towards the holes of dilution 12a and 12b, i.e. in a direction globally opposite to direction D.
  • each zone 16 On either side of each zone 16, the gases flow in a direction inclined towards the axial plane 18 passing through the dilution hole corresponding, and generally directed in the direction of flow general of burnt gases D.
  • the burnt gases circulate according to direction D.
  • the 3D temperature diagram in the vicinity of the dilution also shows significant differences depending on the area.
  • the region of the wall 2 is subdivided and 3 which comprises the orifices 14 in several zones, in each of which, the angles of inclination A of the axes 30 of the orifices 14 by compared to the normal 31 to the wall are identical as well as the angles B planes 32 containing said axes 30 and the normals 31 relative to to the axial planes 33 containing said normal.
  • FIG 3 there is shown an axial wall portion 34 comprising two dilution holes 12a and 12b.
  • the arrow D represents the general direction of the flue gas flow in the combustion 1.
  • References 16a and 16b represent first zones in which the burnt gases flow against the current.
  • the burnt gases In the second zones 17a and 17b situated to the left of the axial planes 18a and 18b, the burnt gases generally flow in the direction of the arrows 19.
  • the gases In the third zones 19a and 19b located to the right of axial plane 18a and 18b, the gases flow in the direction of the arrows 20.
  • the gases flow generally in the direction of the arrow D.
  • the orifices 14 formed in the fourth zone 21 are defined by an inclination A 4 greater than 30 ° and an angle B substantially equal to 0 °.
  • the cooling air diffused by these orifices 14 enters the combustion chamber 1, in the general flow direction D of the gases, but with an inclination A 4 .
  • the orifices 14 formed in the first zone 16a are inclined so as to allow a diffusion of cooling air against the current of the general direction D.
  • the axes 30 of these orifices 14 form an angle A 1 with the normals 31 which is between -60 ° and 0 °.
  • the axes 30 of these orifices 14 are also parallel to the axial plane 18a passing through the axis 35 of the dilution hole 12a.
  • FIG 5 there is shown a small part 36 of the outer wall 2 at a third area 19b.
  • the orifices are drilled at an inclination A 3 relative to the normal 31 and in a plane making an angle B 3 with respect to the direction of the main flow D.
  • the angle B 3 is calculated in function of the average direction of local gas flow in the third zone 19b.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

La présente invention concerne une chambre de combustion, notamment de turbomachine, qui est délimitée par au moins une paroi axiale munie d'une pluralité d'orifices traversant constituant une "multiperforation" destinée, notamment, au passage d'un fluide de réfrigération de ladite paroi axiale, et munie d'une pluralité de trous de dilution régulièrement répartis dans un plan transversal par rapport à la direction générale de l'écoulement des gaz brûlés provenant de la combustion, chaque orifice ayant un axe géométrique incliné d'un angle A par rapport à la normale à ladite paroi, ledit axe génmétrique étant disposé dans un plan contenant ladite normale qui fait un angle B par rapport au plan défini par ladite normale et la direction générale d'écoulement des gaz brûlés.The present invention relates to a combustion chamber, in particular of a turbomachine, which is delimited by at least one wall axial provided with a plurality of through holes constituting a "multi-perforation" intended, in particular, for the passage of a refrigeration of said axial wall, and provided with a plurality of holes for dilution regularly distributed in a transverse plane compared to the general direction of the flow of burnt gases from the combustion, each orifice having a geometric axis inclined at an angle A relative to the normal to said wall, said genometric axis being arranged in a plane containing said normal which makes an angle B by relation to the plan defined by said normal and the general direction flue gas flow.

Le mode de refroidissement par multiperforation est connu. Les orifices sont généralement disposés en quinconce avec un réseau de mailles équidistantes.The cooling mode by multiperforation is known. The orifices are generally staggered with a network of equidistant meshes.

Ces orifices sont alimentés par de l'air de refroidissement issu du compresseur. Les échanges de chaleur mises en jeu sont alors, la convection forcée à l'intérieur des orifices, la conduction au sein même de la paroi. L'alimentation en air de refroidissement de ces orifices génère, en aval de l'écoulement, sur la partie interne de la paroi, un film protecteur entre la paroi de chambre et les gaz brûlés provenant de la combustion. Afin de limiter la dégradation de l'efficacité de ce film, on fait en sorte que l'air de refroidissement ne se mélange pas trop tôt aux gaz brûlés. Pour cela les orifices sont inclinés d'un angle A par rapport à la normale à la paroi interne, de sorte que l'air de refroidissement vienne lécher cette paroi à refroidir.These orifices are supplied with cooling air from the compressor. The heat exchanges involved are then, the forced convection inside the orifices, conduction within the same of the wall. The cooling air supply to these orifices generates, downstream of the flow, on the internal part of the wall, a film protector between the chamber wall and the burnt gases from the combustion. In order to limit the degradation of the effectiveness of this film, we ensures that the cooling air does not mix with the burnt gases. For this, the orifices are inclined at an angle A relative to normal to the inner wall, so the cooling air comes in lick this wall to cool.

EP-A-0 486 133 dévoile une paroi de ce type, dans lequel les orifices sont inclinés dans des plans axiaux.EP-A-0 486 133 discloses a wall of this type, in which the orifices are inclined in axial planes.

EP-A-0 492 864 révèle, en outre, que les orifices sont également inclinés d'un angle tangentiel B qui coïncide globalement avec l'angle du tourbillon des gaz de combustion le long de la surface interne de la paroi.EP-A-0 492 864 further reveals that the orifices are also inclined by a tangential angle B which generally coincides with the angle of the flue gas vortex along the internal surface of the wall.

EP-A-0 592 161 montre en figure 6 une paroi annulaire multiperforée d'une chambre de combustion dans laquelle les orifices sont définis par une inclinaison axiale A et un angle tangentiel B de telle manière que le flux d'air frais introduit dans la chambre crée une couronne d'air protecteur qui tourbillonne autour du flux des gaz brûlés.EP-A-0 592 161 shows in FIG. 6 an annular wall multi-perforated combustion chamber in which the orifices are defined by an axial inclination A and a tangential angle B of in such a way that the flow of fresh air introduced into the room creates a protective crown of air which swirls around the flow of burnt gases.

Dans tous les documents précédents, les inclinaisons A et les angles B qui définissent la direction des axes de chaque orifice par rapport à la direction générale d'écoulement des gaz brûlés, sont respectivement égaux à des valeurs déterminées.In all the preceding documents, the inclinations A and the angles B which define the direction of the axes of each orifice by relative to the general direction of flow of the burnt gases, are respectively equal to determined values.

Or, les calculs 3D montrent que l'écoulement des gaz dans la chambre de combustion n'est pas toujours longitudinal, mais que dans certaines zones, il est légèrement incliné, voire même opposé à l'écoulement, notamment en aval des trous de dilution. Il peut se produire des décollements de l'air de refroidissement dans ces zones.Now, 3D calculations show that the flow of gases in the combustion chamber is not always longitudinal, but only in some areas it is slightly tilted or even opposed to flow, especially downstream of the dilution holes. It can be produce detachments of cooling air in these areas.

Le but de la présente invention est d'éviter que l'air issu de la multiperforation ne décolle de la paroi.The purpose of the present invention is to prevent the air from the multiperforation does not take off from the wall.

La présente invention propose donc d'orienter localement les orifices en fonction de l'écoulement local des gaz brûlés.The present invention therefore proposes to locally orient the orifices according to the local flow of the burnt gases.

Dans, la chambre de combustion connue par EP-A-0 492 864 cité ci-dessus la paroi est subdivisée en plusieurs zones, dans chacune desquelles les orifices sont définis par des inclinaisons A et des angles B ayant respectivement des valeurs identiques et calculées en fonction des caractéristiques de l'écoulement des gaz brûlés dans chacune desdites zones.In, the combustion chamber known from EP-A-0 492 864 cited above the wall is subdivided into several zones, in each of which the orifices are defined by inclinations A and angles B respectively having identical values and calculated as a function characteristics of the flue gas flow in each of said zones.

Selon l'invention, ladite paroi est subdivisée notamment en des premières zones situées respectivement en aval des trous de dilution, et dans lesquelles les orifices sont dirigés à contre courant de la direction générale de l'écoulement des gaz brûlés, des deuxièmes et troisièmes zones disposées de part et d'autre desdites premières zones par rapport aux plans axiaux passant par les trous de dilution correspondants, et une quatrième zone recouvrant le reste de ladite paroi.According to the invention, said wall is subdivided in particular into first zones located respectively downstream of the dilution holes, and in which the orifices are directed against the current of the general direction of the flue gas flow, second and third zones arranged on either side of said first zones with respect to axial planes passing through the corresponding dilution holes, and a fourth zone covering the rest of said wall.

Les orifices ménagés dans la quatrième zone ont une inclinaison axiale supérieure à 30. Leur angle B est sensiblement égal à 0°. L'écoulement d'air frais issu de ces orifices vient lécher la surface interne de la paroi dans le sens de l'écoulement axial des gaz brûlés.The holes in the fourth zone have an inclination axial greater than 30. Their angle B is substantially equal to 0 °. The flow of fresh air from these holes licks the surface internal wall in the direction of the axial flow of the burnt gases.

Les orifices ménagés dans les premières zones, c'est-à-dire en aval des trous de dilution, diffusent un air de refroidissement à contre-courant de la direction générale d'écoulement des gaz brûlés. Leur inclinaison A est comprise entre 0° et -60°, et leur angle B est sensiblement égal à 0°.The orifices made in the first zones, that is to say in downstream of the dilution holes, diffuse a cooling air against the current of the general direction of flue gas flow. Their tilt A is between 0 ° and -60 °, and their angle B is substantially equal to 0 °.

De part et d'autre de chacune des premières zones, dans le sens circonférentiel, il est prévu une deuxième et une troisième zones, dont les orifices diffusent un air de refroidissement vers le plan axial passant par le trou de dilution correspondant et dans la direction de l'écoulement général des gaz brûlés.On either side of each of the first zones, in the direction circumferential, a second and a third zone are provided, of which the orifices diffuse cooling air towards the passing axial plane through the corresponding dilution hole and in the direction of the general flow of burnt gases.

D'autres avantages et caractéristiques de l'invention ressortiront à la lecture de la description suivante faite à titre d'exemple et en référence aux dessins annexés dans lesquels :

  • La figure 1 montre en coupe une chambre de combustion annulaire d'une turbomachine ;
  • la figure 2 est une représentation 3D de l'écoulement des gaz brûlés au voisinage de deux trous de dilution ;
  • la figure 3 montre la subdivision de la paroi multiperforée en plusieurs zones homogènes ;
  • la figure 4 est une coupe axiale à grande échelle de la paroi multiperforée selon un plan axial passant par l'axe d'un trou de dilution ;
  • la figure 5 est une représentation en perspective d'une portion de paroi dans laquelle les orifices de la multiperforation ont une inclinaison axiale et tangentielle.
    • Other advantages and characteristics of the invention will emerge on reading the following description given by way of example and with reference to the appended drawings in which:
  • Figure 1 shows in section an annular combustion chamber of a turbomachine;
  • Figure 2 is a 3D representation of the flue gas flow in the vicinity of two dilution holes;
  • FIG. 3 shows the subdivision of the multi-perforated wall into several homogeneous zones;
  • Figure 4 is a large-scale axial section of the multi-perforated wall along an axial plane passing through the axis of a dilution hole;
  • Figure 5 is a perspective representation of a wall portion in which the orifices of the multi-perforation have an axial and tangential inclination.

    • La chambre de combustion 1, de type annulaire, comporte une paroi axiale annulaire extérieure 2 et une paroi axiale annulaire intérieure 3, réunies à leurs extrémités amont par un fond de chambre 4 équipé de systèmes d'injection 5, et présentant entre leurs extrémités aval une ouverture annulaire 6 pour l'échappement des gaz brûlés G vers une turbine non représentée sur les dessins. Les gaz brûlés G circulent dans la cavité interne 7 de la chambre de combustion 1 selon une direction générale axiale représentée par la flèche D.The combustion chamber 1, of annular type, has a outer annular axial wall 2 and an annular axial wall interior 3, joined at their upstream ends by a chamber bottom 4 equipped with injection systems 5, and having between their ends downstream an annular opening 6 for the exhaust of the burnt gases G towards a turbine not shown in the drawings. The burnt gases G circulate in the internal cavity 7 of the combustion chamber 1 according to an axial general direction represented by the arrow D.

    Les parois axiales extérieure 2 et intérieure 3 délimitent avec les carters extérieur 8 et intérieur 9 des passages annulaires 10 et 11 dans lesquels circule un air de refroidissement A issu d'un compresseur non représenté sur les dessins et situé en amont de la chambre de combustion 1. The outer 2 and inner 3 axial walls define with the outer casings 8 and inner 9 of the annular passages 10 and 11 in which circulates cooling air A coming from a compressor not shown in the drawings and located upstream of the combustion 1.

    Les deux parois 2 et 3 sont munis d'une pluralité- de trous de dilution 12 régulièrement répartis dans un plan axial 13 perpendiculaire à l'axe de la turbomachine, et d'une pluralité d'orifices traversants 14 constituant une multiperforation.The two walls 2 and 3 are provided with a plurality of holes for dilution 12 regularly distributed in an axial plane 13 perpendicular to the axis of the turbomachine, and a plurality of through holes 14 constituting a multi-perforation.

    Une partie de l'air de refroidissement A pénètre axialement dans la cavité interne 7 par les trous de dilution 12 et participe à l'appauvrissement et au refroidissement des gaz de combustion dans la zone de dilution de la chambre de combustion 1, tandis que le reste de l'air A pénètre dans la cavité interne 7 par les orifices 14 afin de former un film de refroidissement sur des faces internes 2a et 3a des parois axiales 2 et 3.Part of the cooling air A enters axially into the internal cavity 7 through the dilution holes 12 and participates in depletion and cooling of the combustion gases in the dilution zone of combustion chamber 1, while the rest of air A enters the internal cavity 7 through the orifices 14 in order to form a cooling film on internal faces 2a and 3a of the walls axial 2 and 3.

    La figure 2 montre le diagramme des vitesses des gaz au voisinage de la face interne 2a de la paroi extérieure 2, dans la région de deux trous de dilution 12a et 12b, ce diagramme ayant été obtenu par des calculs 3D.Figure 2 shows the gas velocity diagram at vicinity of the internal face 2a of the external wall 2, in the region of two dilution holes 12a and 12b, this diagram having been obtained by 3D calculations.

    Ce diagramme montre que, dans la zone 15 qui sépare les deux trous de dilution 12a et 12b, les gaz s'écoulent dans la direction D.This diagram shows that in zone 15 which separates the two dilution holes 12a and 12b, the gases flow in the direction D.

    Dans les zones 16 situées immédiatement en aval des trous de dilution 12a et 12b, les gaz circulent au contraire vers les trous de dilution 12a et 12b, c'est-à-dire dans une direction globalement opposée à la direction D.In zones 16 located immediately downstream of the dilution 12a and 12b, the gases flow on the contrary towards the holes of dilution 12a and 12b, i.e. in a direction globally opposite to direction D.

    De part et d'autre de chaque zone 16, les gaz s'écoulent selon une direction inclinée vers le plan axial 18 passant par le trou de dilution correspondant, et globalement dirigée dans le sens de l'écoulement général des gaz brûlés D.On either side of each zone 16, the gases flow in a direction inclined towards the axial plane 18 passing through the dilution hole corresponding, and generally directed in the direction of flow general of burnt gases D.

    En amont des trous de dilution 12a et 12b et dans la région éloignée des trous de dilution 12a et 12b, les gaz brûlés circulent selon la direction D.Upstream of the dilution holes 12a and 12b and in the region away from the dilution holes 12a and 12b, the burnt gases circulate according to direction D.

    Le diagramme 3D des températures au voisinage des trous de dilution montre également des écarts notables en fonction des zones.The 3D temperature diagram in the vicinity of the dilution also shows significant differences depending on the area.

    Selon la présente invention, on subdivise la région de la paroi 2 et 3 qui comporte les orifices 14 en plusieurs zones, dans chacune desquelles, les angles d'inclinaison A des axes 30 des orifices 14 par rapport aux normales 31 à la paroi sont identiques, ainsi que les angles B des plans 32 contenant lesdits axes 30 et les normales 31 par rapport aux plans axiaux 33 contenant lesdites normales. According to the present invention, the region of the wall 2 is subdivided and 3 which comprises the orifices 14 in several zones, in each of which, the angles of inclination A of the axes 30 of the orifices 14 by compared to the normal 31 to the wall are identical as well as the angles B planes 32 containing said axes 30 and the normals 31 relative to to the axial planes 33 containing said normal.

    Sur la figure 3, on a représenté une portion de paroi axiale 34 comportant deux trous de dilution 12a et 12b. La flèche D représente la direction générale de l'écoulement des gaz brûlés dans la chambre de combustion 1.In Figure 3, there is shown an axial wall portion 34 comprising two dilution holes 12a and 12b. The arrow D represents the general direction of the flue gas flow in the combustion 1.

    Les références 16a et 16b représentent des premières zones dans lesquelles les gaz brûlés s'écoulent à contre-courant. Dans les deuxièmes zones 17a et 17b situées à gauche des plans axiaux 18a et 18b, les gaz brûlés s'écoulent dans l'ensemble selon la direction des flèches 19. Dans les troisièmes zones 19a et 19b situées à droite des plan axiaux 18a et 18b, les gaz s'écoulent dans le sens des flèches 20.References 16a and 16b represent first zones in which the burnt gases flow against the current. In the second zones 17a and 17b situated to the left of the axial planes 18a and 18b, the burnt gases generally flow in the direction of the arrows 19. In the third zones 19a and 19b located to the right of axial plane 18a and 18b, the gases flow in the direction of the arrows 20.

    Dans la quatrième zone 21 située en dehors des zones 16a, 16b, 17a, 17b, 19a et 19b, les gaz s'écoulent globalement dans le sens de la flèche D.In the fourth zone 21 located outside zones 16a, 16b, 17a, 17b, 19a and 19b, the gases flow generally in the direction of the arrow D.

    Comme on le voit sur la figure 4, les orifices 14 ménagés dans la quatrième zone 21 sont définis par une inclinaison A4 supérieure à 30° et un angle B sensiblement égal à 0°. L'air de refroidissement diffusé par ces orifices 14 pénètre dans la chambre de combustion 1, dans le sens de l'écoulement général D des gaz, mais avec une inclinaison A4.As can be seen in FIG. 4, the orifices 14 formed in the fourth zone 21 are defined by an inclination A 4 greater than 30 ° and an angle B substantially equal to 0 °. The cooling air diffused by these orifices 14 enters the combustion chamber 1, in the general flow direction D of the gases, but with an inclination A 4 .

    Les orifices 14 ménagés dans la première zone 16a sont inclinés de manière à permettre une diffusion d'un air de refroidissement à contre-courant de la direction générale D. Les axes 30 de ces orifices 14 font un angle A1 avec les normales 31 qui est compris entre -60° et 0°. Les axes 30 de ces orifices 14 sont également parallèles au plan axial 18a passant par l'axe 35 du trou de dilution 12a.The orifices 14 formed in the first zone 16a are inclined so as to allow a diffusion of cooling air against the current of the general direction D. The axes 30 of these orifices 14 form an angle A 1 with the normals 31 which is between -60 ° and 0 °. The axes 30 of these orifices 14 are also parallel to the axial plane 18a passing through the axis 35 of the dilution hole 12a.

    Sur la figure 5, on a représenté une petite partie 36 de la paroi extérieure 2 au niveau d'une troisième zone 19b. Dans cette troisième zone 19b, les orifices sont percés selon une inclinaison A3 par rapport à la normale 31 et dans un plan faisant un angle B3 par rapport à la direction de l'écoulement principal D. L'angle B3 est calculé en fonction de la direction moyenne de l'écoulement local des gaz dans la troisième zone 19b.In Figure 5, there is shown a small part 36 of the outer wall 2 at a third area 19b. In this third zone 19b, the orifices are drilled at an inclination A 3 relative to the normal 31 and in a plane making an angle B 3 with respect to the direction of the main flow D. The angle B 3 is calculated in function of the average direction of local gas flow in the third zone 19b.

    Claims (6)

    1. A combustor, particularly for a turbomachine, which is defined by at least one axial wall (2,3) formed with a number of through orifices (14) constituting a "multiperforation" serving in particular for the passage of a fluid A for cooling the axial wall (2.3), the same also being formed with a number of dilution apertures (12) evenly distributed in a plane (13) transverse to the general direction (D) of the flow of burnt gases (G) from combustion, each orifice (14) having a geometric axis (30) inclined at an angle A to the perpendicular (31) to the wall (2, 3), the geometric axis (30) being disposed in a plane (32) containing the said perpendicular (31) and making an angle (B) with the plane (33) defined by the said perpendicular and the general burnt gas flow direction (D), wherein the wall (2, 3) is subdivided into a number of zones (16a, 16b, 17a, 17b, 19a, 19b, 21) in each of which the orifices (14) are defined by inclinations A and angles B having respective identical values calculated in dependence upon the local flow (6) of the burnt gases in each of the said zones, characterised in that the wall (2, 3) is subdivided into first zones (16a, 16b) which are disposed downstream of the respective dilution apertures and in which the orifices (14) extend in countercurrent to the general direction (D) of the burnt gas flow (G), into second zones (17a, 17b) and third zones disposed on either side of the first zones (16a, 16b) relative to the axial planes (18a, 18b) extending through the corresponding dilution apertures (12a, 12b), and into a fourth zone (21) covering the remainder of the wall (2, 3).
    2. a combustor according to claim 1, characterised in that the orifices (14) in the fourth zone (21) are defined by an inclination A greater than 30°.
    3. A combustor according to claim 2, characterised in that the orifices (14) in the fourth zone (21) are defined by an angle B of substantially 0°.
    4. A combustor according to claim 1, characterised in that the orifices (14) in the first zones (16a, 16b) are defined by an inclination A between 0° and -60°.
    5. A combustor according to claim 4, characterised in that the orifices (14) in the first zones (16a, 16b) are defined by an angle (B) of substantially 0°.
    6. A combustor according to claim 2, characterised in that the orifices (14) in the second zones (17a, 17b) are defined by angles B of opposite values to the angles B defining the orifices (14) in the third zones (19a, 19b).
    EP96400863A 1995-04-26 1996-04-24 Combustion chamber having a multitude of cooling holes which are inclined in varying axial and tangential directions Expired - Lifetime EP0743490B1 (en)

    Applications Claiming Priority (2)

    Application Number Priority Date Filing Date Title
    FR9504968 1995-04-26
    FR9504968A FR2733582B1 (en) 1995-04-26 1995-04-26 COMBUSTION CHAMBER COMPRISING VARIABLE AXIAL AND TANGENTIAL TILT MULTIPERFORATION

    Publications (2)

    Publication Number Publication Date
    EP0743490A1 EP0743490A1 (en) 1996-11-20
    EP0743490B1 true EP0743490B1 (en) 1999-06-09

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    US (1) US5775108A (en)
    EP (1) EP0743490B1 (en)
    JP (1) JP3302559B2 (en)
    DE (1) DE69602804T2 (en)
    FR (1) FR2733582B1 (en)

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    Also Published As

    Publication number Publication date
    JPH08312960A (en) 1996-11-26
    DE69602804T2 (en) 2000-01-27
    US5775108A (en) 1998-07-07
    FR2733582B1 (en) 1997-06-06
    EP0743490A1 (en) 1996-11-20
    DE69602804D1 (en) 1999-07-15
    FR2733582A1 (en) 1996-10-31
    JP3302559B2 (en) 2002-07-15

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