EP1760261B1 - Air baffle for the cooling circuit of turbine blades - Google Patents

Air baffle for the cooling circuit of turbine blades Download PDF

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Publication number
EP1760261B1
EP1760261B1 EP06119232A EP06119232A EP1760261B1 EP 1760261 B1 EP1760261 B1 EP 1760261B1 EP 06119232 A EP06119232 A EP 06119232A EP 06119232 A EP06119232 A EP 06119232A EP 1760261 B1 EP1760261 B1 EP 1760261B1
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EP
European Patent Office
Prior art keywords
cavity
blade
cooling circuit
air
air deflector
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Active
Application number
EP06119232A
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German (de)
French (fr)
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EP1760261A1 (en
Inventor
Jacques Auguste Boury
Patrice Eneau
Guy Moreau
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Safran Aircraft Engines SAS
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SNECMA SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs

Definitions

  • the present invention relates to the general field of cooling gas turbine blades, in particular the blades of a turbomachine gas turbine.
  • the gas turbine blades of a turbomachine such as the blades of the high-pressure turbine for example, are subjected to the very high temperatures of the gases from the combustion chamber. These temperatures reach values much higher than those that can withstand without damage the vanes of the turbine, which has the effect of limiting their service life.
  • a gas turbine blade In terms of mechanical strength, a gas turbine blade has a good service life if its intrados and extrados faces have similar temperatures (that is to say if the thermal gradient between these faces is low). Moreover, whatever the embodiment of the cooling circuits, the internal cooling of a turbine blade is provided by internal convection of a fresh air flow on the walls of the cavities forming these circuits. This results in a different heat exchange on each wall of the cavity, regardless of whether it is smooth or disturbed or that the blade is fixed or movable.
  • the heat exchange with the hot gases flowing outside the blade is greater on the intrados side than on the extrados side of the blade. Also, to compensate for this phenomenon and thus obtain a low thermal gradient between the intrados and extrados surfaces of the blade, it is necessary to strongly cool the internal walls of the cooling system cavities which are arranged on the intrados side of the blade.
  • the main object of the present invention is thus to overcome such drawbacks by proposing a gas turbine blade for which the internal cooling circuit makes it possible to minimize the difference in temperature between the intrados and extrados faces thereof.
  • a gas turbine blade according to claim 1 is provided.
  • the air deflector has a slope inclined so as to project the air flowing along the wall of the cavity to the opposite wall.
  • a ramp has a length of between 2 and 4 times its height and may have a radius of curvature of between 20 and 30 mm.
  • the wall of the cavity of the cooling circuit comprising the air deflector can be arranged on the extrados side of the blade and the wall of the cavity on which the air is projected can be arranged on the intrados side of the dawn.
  • the air deflector is advantageously disposed on the wall of the cavity of the cooling circuit at a zone of attachment of the blade.
  • the air deflector is advantageously disposed on the wall of the cavity of the cooling circuit at the top of the blade.
  • the air deflector may be positioned at a passage communicating the radial end of one of the cavities with a radial end adjacent to the cavity. other cavity.
  • the invention also relates to a gas turbine and a turbomachine having a plurality of blades as defined above.
  • the Figures 1 to 4 represent a moving blade 10 of a turbomachine, such as a moving blade of a high-pressure turbine.
  • a turbomachine such as a moving blade of a high-pressure turbine.
  • the invention can be applied to other blades of a turbomachine gas turbine as well as to vanes of a turbomachine gas turbine.
  • the blade 10 comprises an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14.
  • This aerodynamic surface consists of a leading edge 16 disposed opposite the blade. flow of the hot gases from the combustion chamber of the turbomachine, a trailing edge 18 opposite the leading edge 16, a lateral face 20 and an extrados lateral face 22, these lateral faces 20 , 22 connecting the leading edge 16 to the trailing edge 18.
  • the blade 10 is provided with an internal cooling circuit of the type formed by at least one cavity extending radially between the root 12 and the top 14 of the blade, at least one air intake opening at a radial end of the cavity and at least one air outlet opening opening into the cavity and opening on one of the faces of the blade.
  • the internal cooling circuit of the blade consists of a leading edge cavity 24 disposed on the side of the leading edge 16 of the blade, three central cavities 26, 28 and 30 disposed in a central portion of the dawn and a trailing edge cavity 32 disposed on the side of the trailing edge 18 of the blade.
  • These different cavities 24, 26, 28, 30 and 32 extend from the intrados face 20 to the extrados face 22 of the blade.
  • An air inlet opening 34 is provided at a radial end of the leading edge cavity 24 (here at the foot 12 of the blade) to supply air to the cooling circuit.
  • a first passage 36 communicates the other radial end of the leading edge cavity 24 with a radial end adjacent to the central cavity 26 adjacent.
  • a second passage 38 and a third passage 40 communicate respectively the central cavity 26 with the central cavity 28 adjacent and the latter with the central cavity 30 remaining.
  • a fourth passage 42 communicates the central cavity 30 with the trailing edge cavity 32.
  • the intrados cooling circuit also has outlet orifices 44 opening in the trailing edge cavity 32 and opening on the intrados face 20 of the blade at the trailing edge 18 of the latter. These orifices 44 are regularly distributed over the entire radial height of the blade.
  • Airflow disturbers 46 for increasing heat transfer may be provided along the walls of the various cavities 24, 26, 28, 30 and 32 of the cooling circuit. These flow disturbers 46 may be in the form of ribs which are straight or inclined relative to the axis of rotation of the blade, in the form of pins or in any other equivalent form.
  • any other embodiment of the internal cooling circuit of the blade of the type described above is applicable to the invention.
  • the number, shape and arrangement of the cavities, as well as the quantity and arrangement of the air intake orifices, the communication passages and the outlet orifices may vary according to the cooling circuit.
  • At least one of the walls of one (or more) of the cavities 24, 26, 28, 30 and 32 of the cooling circuit comprises at least one air deflector 48, 48 '.
  • an air deflector 48 is particularly visible on the figures 2 and 3 .
  • the air deflector 48 is positioned on the wall 24a of the leading edge cavity 24 which is disposed on the extrados side 22 of the blade.
  • FIG. 4 Another example of the location of such an air deflector 48 'is shown on the figure 4 .
  • the air deflector 48 ' is disposed on the wall 26a of the central cavity 26 adjacent to the leading edge cavity 24 which is disposed on the extrados side 22 of the blade.
  • the shape and the dimensions of the air deflector 48, 48 ' are adapted to project the air flowing along the wall 24a, 26a of the cavity 24, 26 to an opposite wall 24b, 26b of the cavity while avoiding a re-bonding of the boundary layer immediately downstream of the air deflector.
  • the air deflector according to the invention is distinguished in that it consists, on the one hand to project the air on the wall opposite to that of its implantation, and secondly to avoid an immediate gluing of the boundary layer.
  • an airflow disturbance has the essential function of increasing the turbulence of the flow of air in the immediate vicinity of the disturbance while seeking to re-glue the flow downstream thereof.
  • the presence of airflow disruptors 46 with the air deflector 48, 48 'according to the invention is also not incompatible.
  • the figure 3 shows more precisely one embodiment of an air deflector 48 according to the invention.
  • the air deflector 48 comprises a ramp 52 which is inclined with respect to the wall 24a of the cavity 24 on which the deflector is implanted so as to project the air flowing along this wall 24a towards the opposite wall 24b .
  • the inclined ramp 52 of the air deflector 48 has a length L which is between 2 and 4 times its height h .
  • the ramp 52 of the air deflector 48 has a height h of the order of 1.5 mm and a length L of between 3 and 5 mm.
  • an air-flow disruptor 46 as described above has a height of between 0.4 and 0.5 mm. .
  • the inclined ramp 52 of the air deflector 48 is rounded and has a radius of curvature R between 20 and 30 mm.
  • This value is given as an example for a cooling cavity 24 having a width d of the order of 4 mm.
  • a radius of curvature R as large relative to the width d of the cavity 24 makes it possible to move the air flowing along the wall 24a towards the opposite wall 24b without accelerating it suddenly.
  • the radius of curvature R of the ramp 52 of the deflector is preferably greater than the length L on which extends this ramp.
  • the air deflector 48 On the opposite side to the inclined ramp 52, the air deflector 48 has another rounded ramp 54 whose radius of curvature r and the length I on which it extends are calculated so as to avoid re-bonding of the boundary layer immediately. downstream of the air deflector.
  • the radius of curvature r of this other ramp 54 must be as small as possible to achieve this goal.
  • the flow of air in the leading edge cavity 24 is centrifugal, that is to say that the air flows from the foot 12 to the top 14 of the blade.
  • the air deflector 48 is advantageously disposed on the wall of the cavity 24 of the cooling circuit at a zone of attachment of the blade. This attachment zone extends from the radial end of the blade on the side of its foot 12 to a platform 56 defining the inner wall of the flow passage of the gas passing through the gas turbine.
  • a platform 56 defining the inner wall of the flow passage of the gas passing through the gas turbine.
  • the flow of air in the central cavity 26 is centripetal, that is to say that the air flows from the top 14 towards the foot 12 of dawn.
  • the air deflector 48 ' is advantageously disposed on the wall of the cavity 26 of the cooling circuit at the top 14 of the blade. Such a location makes it possible to obtain an optimum internal heat exchange on the underside of the dawn.
  • the air deflector 48 is positioned at a passage 100 communicating the radial end of a cavity 102 of an internal cooling circuit of a blade with a radial end adjacent to another cavity 104 adjacent thereto, such a communication passage 100 may for example be one of the passages 36 to 40 of the dawn of Figures 1 to 3 .
  • the air baffle 48 is disposed on one of the walls 104a of the cavity 104 and its shape and dimensions are adapted to project the air flowing along the wall 104a to the opposite wall 104b while avoiding a bonding of the boundary layer immediately downstream of the air deflector.
  • the air baffle 48 is positioned such that the air flowing in the cavity 102 is projected at its" turn-over "into the adjacent cavity 104 (i.e. from the communication passage 100) to an air circulation zone 106 which is located at the radial end of the opposite wall 104b of the adjacent cavity 104.
  • Such an area 106 is usually an area in which the Air circulation is low and undisturbed.
  • the air deflector 48 "thus makes it possible to avoid any risk of detachment of the boundary layer at the level of the" reversal "zone of the air between the two cavities 102, 104 of the cooling circuit .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général du refroidissement des aubes de turbine à gaz, notamment les aubes mobiles d'une turbine à gaz de turbomachine.The present invention relates to the general field of cooling gas turbine blades, in particular the blades of a turbomachine gas turbine.

Les aubes de turbine à gaz d'une turbomachine, telles que les aubes mobiles de la turbine haute-pression par exemple, sont soumises aux températures très élevées des gaz issus de la chambre de combustion. Ces températures atteignent des valeurs largement supérieures à celles que peuvent supporter sans dommages les aubes de la turbine, ce qui a pour conséquence de limiter leur durée de vie.The gas turbine blades of a turbomachine, such as the blades of the high-pressure turbine for example, are subjected to the very high temperatures of the gases from the combustion chamber. These temperatures reach values much higher than those that can withstand without damage the vanes of the turbine, which has the effect of limiting their service life.

Afin de remédier à ce problème, il est bien connu de munir ces aubes de circuits internes de refroidissement. Grâce à de tels circuits de refroidissement, de l'air, qui est généralement introduit dans l'aube par son pied, traverse celle-ci en suivant un trajet formé par des cavités pratiquées dans l'aube avant d'être éjecté par des orifices s'ouvrant à la surface de l'aube.In order to remedy this problem, it is well known to provide these vanes with internal cooling circuits. By means of such cooling circuits, air, which is generally introduced into the blade by its foot, traverses the latter along a path formed by cavities formed in the blade before being ejected by orifices. opening on the surface of dawn.

Il existe de nombreuses réalisations différentes de ces circuits de refroidissement. Ainsi, certains circuits utilisent des cavités de refroidissement qui occupent toute la largeur de l'aube (c'est-à-dire qui s'étendent depuis l'intrados jusqu'à l'extrados de l'aube). D'autres circuits proposent l'utilisation de cavités de refroidissement de bord n'occupant qu'un seul côté de l'aube (intrados ou extrados) ou les deux côtés avec l'adjonction d'une grande cavité centrale entre ces cavités de bord.There are many different achievements of these cooling circuits. Thus, some circuits use cooling cavities that occupy the entire width of the blade (that is to say that extend from the intrados to the upper surface of the blade). Other circuits propose the use of edge cooling cavities occupying only one side of the blade (intrados or extrados) or both sides with the addition of a large central cavity between these edge cavities. .

En terme de tenue mécanique, une aube de turbine à gaz affiche une bonne durée de vie si ses faces intrados et extrados présentent des températures voisines (c'est-à-dire si le gradient thermique entre ces faces est faible). Par ailleurs, quelque soit le mode de réalisation des circuits de refroidissement, le refroidissement interne d'une aube de turbine est assuré par convection interne d'un flux d'air frais sur les parois des cavités formant ces circuits. Il en résulte un échange thermique différent sur chaque paroi de la cavité, indépendamment du fait que celle-ci soit lisse ou perturbée ou que l'aube soit fixe ou mobile.In terms of mechanical strength, a gas turbine blade has a good service life if its intrados and extrados faces have similar temperatures (that is to say if the thermal gradient between these faces is low). Moreover, whatever the embodiment of the cooling circuits, the internal cooling of a turbine blade is provided by internal convection of a fresh air flow on the walls of the cavities forming these circuits. This results in a different heat exchange on each wall of the cavity, regardless of whether it is smooth or disturbed or that the blade is fixed or movable.

Or, l'échange thermique avec les gaz chauds circulant à l'extérieur de l'aube est plus important du côté intrados que du côté extrados de l'aube. Aussi, pour compenser ce phénomène et ainsi obtenir un faible gradient thermique entre les faces intrados et extrados de l'aube, il est nécessaire de refroidir fortement les parois internes des cavités du circuit de refroidissement qui sont disposées du côté intrados de l'aube.However, the heat exchange with the hot gases flowing outside the blade is greater on the intrados side than on the extrados side of the blade. Also, to compensate for this phenomenon and thus obtain a low thermal gradient between the intrados and extrados surfaces of the blade, it is necessary to strongly cool the internal walls of the cooling system cavities which are arranged on the intrados side of the blade.

Pour une aube mobile de turbine à gaz, lorsque l'écoulement de l'air dans les cavités du circuit de refroidissement est centrifuge, et malgré les effets de la force de Coriolis qui augmentent les échanges thermiques internes à l'intrados de l'aube, l'écart avec les échanges thermiques s'effectuant à l'extrados de l'aube reste trop important pour obtenir un faible gradient thermique. De même, lorsque l'écoulement de l'air dans les cavités du circuit de refroidissement de l'aube mobile est centripète, l'échange thermique est naturellement favorable à l'extrados de l'aube, ce qui accentue encore l'écart de température entre les faces intrados et extrados de l'aube.For a moving gas turbine blade, when the flow of air in the cavities of the cooling circuit is centrifugal, and despite the effects of the Coriolis force which increase the internal heat exchange on the underside of the dawn , the difference with the thermal exchanges taking place on the extrados of the dawn remains too important to obtain a low thermal gradient. Similarly, when the flow of air in the cavities of the cooling circuit of the moving blade is centripetal, the heat exchange is naturally favorable to the upper surface of the blade, which further accentuates the difference between temperature between the intrados and extrados faces of the dawn.

On connaît aussi de DE 195 26917 un circuit de refroidissement d'une aube dont les cavités sont munies de perturbateurs d'écoulement.We also know DE 195 26917 a cooling circuit of a blade whose cavities are provided with flow disruptors.

Objet et résumé de l'inventionObject and summary of the invention

La présente invention a donc pour but principal de pallier de tels inconvénients en proposant une aube de turbine à gaz pour laquelle le circuit interne de refroidissement permet de minimiser l'écart de température entre les faces intrados et extrados de celle-ci.The main object of the present invention is thus to overcome such drawbacks by proposing a gas turbine blade for which the internal cooling circuit makes it possible to minimize the difference in temperature between the intrados and extrados faces thereof.

A cet effet, il est prévu une aube de turbine à gaz selon la revendication 1.For this purpose, a gas turbine blade according to claim 1 is provided.

En positionnant judicieusement le déflecteur d'air dans la cavité du circuit de refroidissement selon que l'écoulement dans celle-ci soit centrifuge ou centripète, il est possible de projeter l'air circulant dans la cavité vers la paroi de la cavité qui est disposée du côté intrados de l'aube. Ainsi, un tel déflecteur d'air permet d'augmenter l'échange thermique interne à l'intrados de l'aube et donc de réduire le gradient thermique entre les parois extrados et intrados de la cavité du circuit de refroidissement. De la sorte, tout écart de température entre les faces intrados et extrados de l'aube peut être évité.By judiciously positioning the air deflector in the cavity of the cooling circuit according to whether the flow therein is centrifugal or centripetal, it is possible to project the air circulating in the cavity towards the wall of the cavity which is disposed on the intrados side of the blade. Thus, such an air deflector makes it possible to increase the internal heat exchange at the intrados of the blade and thus to reduce the thermal gradient between the extrados and intrados walls of the cavity of the cooling circuit. In this way, any difference in temperature between the intrados and extrados faces of the blade can be avoided.

Selon l'invention, le déflecteur d'air présente une rampe inclinée de façon à projeter l'air s'écoulant le long de la paroi de la cavité vers la paroi opposée. Une telle rampe possède une longueur comprise entre 2 et 4 fois sa hauteur et peut présenter un rayon de courbure compris entre 20 et 30 mm.According to the invention, the air deflector has a slope inclined so as to project the air flowing along the wall of the cavity to the opposite wall. Such a ramp has a length of between 2 and 4 times its height and may have a radius of curvature of between 20 and 30 mm.

Selon une application particulière de l'invention, la paroi de la cavité du circuit de refroidissement comportant le déflecteur d'air peut être disposée du côté extrados de l'aube et la paroi de la cavité sur laquelle est projetée l'air peut être disposée du côté intrados de l'aube.According to a particular application of the invention, the wall of the cavity of the cooling circuit comprising the air deflector can be arranged on the extrados side of the blade and the wall of the cavity on which the air is projected can be arranged on the intrados side of the dawn.

Lorsque l'écoulement de l'air dans la cavité du circuit de refroidissement est centrifuge, le déflecteur d'air est avantageusement disposé sur la paroi de la cavité du circuit de refroidissement au niveau d'une zone d'attache de l'aube.When the flow of air in the cavity of the cooling circuit is centrifugal, the air deflector is advantageously disposed on the wall of the cavity of the cooling circuit at a zone of attachment of the blade.

Alternativement, lorsque l'écoulement de l'air dans la cavité du circuit de refroidissement est centripète, le déflecteur d'air est avantageusement disposé sur la paroi de la cavité du circuit de refroidissement au niveau du sommet de l'aube.Alternatively, when the flow of air in the cavity of the cooling circuit is centripetal, the air deflector is advantageously disposed on the wall of the cavity of the cooling circuit at the top of the blade.

Selon encore une autre alternative pour laquelle le circuit de refroidissement comporte au moins deux cavités, le déflecteur d'air peut être positionné au niveau d'un passage faisant communiquer l'extrémité radiale de l'une des cavités avec une extrémité radiale voisine de l'autre cavité.According to yet another alternative for which the cooling circuit comprises at least two cavities, the air deflector may be positioned at a passage communicating the radial end of one of the cavities with a radial end adjacent to the cavity. other cavity.

L'invention a également pour objet une turbine à gaz et une turbomachine ayant une pluralité d'aubes telles que définies précédemment.The invention also relates to a gas turbine and a turbomachine having a plurality of blades as defined above.

Brève description des dessinsBrief description of the drawings

D'autres caractéristiques et avantages de la présente invention ressortiront de la description faite ci-dessous, en référence aux dessins annexés qui en illustrent un exemple de réalisation dépourvu de tout caractère limitatif. Sur les figures :

  • la figure 1 est une vue en coupe longitudinale d'une aube mobile de turbine à gaz selon un mode de réalisation de l'invention ;
  • la figure 2 est une vue en coupe selon II-II de la figure 1 ;
  • la figure 3 est une loupe d'un détail de la figure 2 ;
  • la figure 4 est une vue en coupe selon IV-IV de la figure 1 ; et
  • la figure 5 est une vue partielle et en coupe longitudinale d'une aube mobile de turbine à gaz selon un autre mode de réalisation de l'invention.
Other features and advantages of the present invention will become apparent from the description given below, with reference to the drawings annexed which illustrate an embodiment without any limiting character. In the figures:
  • the figure 1 is a longitudinal sectional view of a gas turbine moving blade according to one embodiment of the invention;
  • the figure 2 is a sectional view along II-II of the figure 1 ;
  • the figure 3 is a magnifying glass of a detail of the figure 2 ;
  • the figure 4 is a sectional view along IV-IV of the figure 1 ; and
  • the figure 5 is a partial view in longitudinal section of a gas turbine moving blade according to another embodiment of the invention.

Description détaillée d'un mode de réalisationDetailed description of an embodiment

Les figures 1 à 4 représentent une aube mobile 10 de turbomachine, telle qu'une aube mobile de turbine haute-pression. Bien entendu, l'invention peut aussi bien s'appliquer à d'autres aubes mobiles d'une turbine à gaz de turbomachine, ainsi qu'à des aubes fixes d'une turbine à gaz de turbomachine.The Figures 1 to 4 represent a moving blade 10 of a turbomachine, such as a moving blade of a high-pressure turbine. Of course, the invention can be applied to other blades of a turbomachine gas turbine as well as to vanes of a turbomachine gas turbine.

L'aube 10 comporte une surface aérodynamique (ou pale) qui s'étend radialement entre un pied d'aube 12 et un sommet d'aube 14. Cette surface aérodynamique se compose d'un bord d'attaque 16 disposé en regard de l'écoulement des gaz chauds issus de la chambre de combustion de la turbomachine, d'un bord de fuite 18 opposé au bord d'attaque 16, d'une face latérale intrados 20 et d'une face latérale extrados 22, ces faces latérales 20, 22 reliant le bord d'attaque 16 au bord de fuite 18.The blade 10 comprises an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14. This aerodynamic surface consists of a leading edge 16 disposed opposite the blade. flow of the hot gases from the combustion chamber of the turbomachine, a trailing edge 18 opposite the leading edge 16, a lateral face 20 and an extrados lateral face 22, these lateral faces 20 , 22 connecting the leading edge 16 to the trailing edge 18.

L'aube 10 est munie d'un circuit interne de refroidissement du type formé par au moins une cavité s'étendant radialement entre le pied 12 et le sommet 14 de l'aube, au moins une ouverture d'admission d'air à une extrémité radiale de la cavité et au moins un orifice de sortie d'air s'ouvrant dans la cavité et débouchant sur l'une des faces de l'aube.The blade 10 is provided with an internal cooling circuit of the type formed by at least one cavity extending radially between the root 12 and the top 14 of the blade, at least one air intake opening at a radial end of the cavity and at least one air outlet opening opening into the cavity and opening on one of the faces of the blade.

Sur l'exemple de réalisation des figures 1 à 4, le circuit interne de refroidissement de l'aube se compose d'une cavité bord d'attaque 24 disposée du côté du bord d'attaque 16 de l'aube, de trois cavités centrales 26, 28 et 30 disposées dans une partie centrale de l'aube et d'une cavité bord de fuite 32 disposée du côté du bord de fuite 18 de l'aube. Ces différentes cavités 24, 26, 28, 30 et 32 s'étendent depuis la face intrados 20 jusqu'à la face extrados 22 de l'aube.On the example of realization of the Figures 1 to 4 , the internal cooling circuit of the blade consists of a leading edge cavity 24 disposed on the side of the leading edge 16 of the blade, three central cavities 26, 28 and 30 disposed in a central portion of the dawn and a trailing edge cavity 32 disposed on the side of the trailing edge 18 of the blade. These different cavities 24, 26, 28, 30 and 32 extend from the intrados face 20 to the extrados face 22 of the blade.

Une ouverture d'admission d'air 34 est prévue à une extrémité radiale de la cavité bord d'attaque 24 (ici au niveau du pied 12 de l'aube) afin d'alimenter en air le circuit de refroidissement.An air inlet opening 34 is provided at a radial end of the leading edge cavity 24 (here at the foot 12 of the blade) to supply air to the cooling circuit.

Un premier passage 36 fait communiquer l'autre extrémité radiale de la cavité bord d'attaque 24 avec une extrémité radiale voisine de la cavité centrale 26 adjacente. Un deuxième passage 38 et un troisième passage 40 font communiquer respectivement la cavité centrale 26 avec la cavité centrale 28 adjacente et cette dernière avec la cavité centrale 30 restante. Enfin, un quatrième passage 42 fait communiquer la cavité centrale 30 avec la cavité bord de fuite 32.A first passage 36 communicates the other radial end of the leading edge cavity 24 with a radial end adjacent to the central cavity 26 adjacent. A second passage 38 and a third passage 40 communicate respectively the central cavity 26 with the central cavity 28 adjacent and the latter with the central cavity 30 remaining. Finally, a fourth passage 42 communicates the central cavity 30 with the trailing edge cavity 32.

Le circuit de refroidissement intrados comporte aussi des orifices de sortie 44 s'ouvrant dans la cavité bord de fuite 32 et débouchant sur la face intrados 20 de l'aube au niveau du bord de fuite 18 de cette dernière. Ces orifices 44 sont régulièrement répartis sur toute la hauteur radiale de l'aube.The intrados cooling circuit also has outlet orifices 44 opening in the trailing edge cavity 32 and opening on the intrados face 20 of the blade at the trailing edge 18 of the latter. These orifices 44 are regularly distributed over the entire radial height of the blade.

Des perturbateurs d'écoulement de l'air 46 destinés à accroître les transferts thermiques peuvent être prévus le long des parois des différents cavités 24, 26, 28, 30 et 32 du circuit de refroidissement. Ces perturbateurs d'écoulement 46 peuvent se présenter sous la forme de nervures qui sont droites ou inclinées par rapport à l'axe de rotation de l'aube, sous la forme de picots ou encore sous toutes autres formes équivalentes.Airflow disturbers 46 for increasing heat transfer may be provided along the walls of the various cavities 24, 26, 28, 30 and 32 of the cooling circuit. These flow disturbers 46 may be in the form of ribs which are straight or inclined relative to the axis of rotation of the blade, in the form of pins or in any other equivalent form.

Bien entendu, tout autre mode de réalisation du circuit interne de refroidissement de l'aube du type décrit précédemment est applicable à l'invention. Notamment, le nombre, la forme et la disposition des cavités, ainsi que la quantité et la disposition des orifices d'admission d'air, des passages de communication et des orifices de sortie peuvent varier selon le circuit de refroidissement.Of course, any other embodiment of the internal cooling circuit of the blade of the type described above is applicable to the invention. In particular, the number, shape and arrangement of the cavities, as well as the quantity and arrangement of the air intake orifices, the communication passages and the outlet orifices may vary according to the cooling circuit.

Selon l'invention, au moins l'une des parois de l'une (ou de plusieurs) des cavités 24, 26, 28, 30 et 32 du circuit de refroidissement comporte au moins un déflecteur d'air 48, 48'.According to the invention, at least one of the walls of one (or more) of the cavities 24, 26, 28, 30 and 32 of the cooling circuit comprises at least one air deflector 48, 48 '.

Un exemple d'emplacement d'un tel déflecteur d'air 48 est notamment visible sur les figures 2 et 3. Sur ces figures, le déflecteur d'air 48 est positionné sur la paroi 24a de la cavité bord d'attaque 24 qui est disposée du côté extrados 22 de l'aube.An example of the location of such an air deflector 48 is particularly visible on the figures 2 and 3 . In these figures, the air deflector 48 is positioned on the wall 24a of the leading edge cavity 24 which is disposed on the extrados side 22 of the blade.

Un autre exemple d'emplacement d'un tel déflecteur d'air 48' est représenté sur la figure 4. Sur cette figure, le déflecteur d'air 48' est disposé sur la paroi 26a de la cavité centrale 26 adjacente à la cavité bord d'attaque 24 qui est disposée du côté extrados 22 de l'aube.Another example of the location of such an air deflector 48 'is shown on the figure 4 . In this figure, the air deflector 48 'is disposed on the wall 26a of the central cavity 26 adjacent to the leading edge cavity 24 which is disposed on the extrados side 22 of the blade.

Toujours selon l'invention, la forme et les dimensions du déflecteur d'air 48, 48' sont adaptées pour projeter l'air s'écoulant le long de la paroi 24a, 26a de la cavité 24, 26 vers une paroi opposée 24b, 26b de la cavité tout en évitant un recollement de la couche limite immédiatement en aval du déflecteur d'air.Still according to the invention, the shape and the dimensions of the air deflector 48, 48 'are adapted to project the air flowing along the wall 24a, 26a of the cavity 24, 26 to an opposite wall 24b, 26b of the cavity while avoiding a re-bonding of the boundary layer immediately downstream of the air deflector.

Par recollement de la couche limite immédiatement en aval du déflecteur d'air 48, 48', il faut comprendre que l'écoulement de l'air en aval du déflecteur s'effectue principalement le long de la paroi 24b, 26b opposée à la paroi 24a, 26a sur laquelle est implanté le déflecteur d'air. Aussi, dans la zone 50, 50' immédiatement en aval du déflecteur d'air 48, 48', l'écoulement de l'air le long de la paroi 24a, 26a d'emplacement du déflecteur est faible. A titre d'exemple, cette zone 50, 50' de faible écoulement de l'air s'étend sur une hauteur radiale de l'aube de l'ordre de 20% environ de la hauteur radiale totale de l'aube.By bonding of the boundary layer immediately downstream of the air deflector 48, 48 ', it is to be understood that the flow of air downstream of the deflector takes place mainly along the wall 24b, 26b opposite to the wall 24a, 26a on which is implanted the air deflector. Also, in the zone 50, 50 'immediately downstream of the air deflector 48, 48', the flow of air along the deflector location wall 24a, 26a is small. For example, this zone 50, 50 'of low airflow extends over a radial height of the blade of about 20% of the total radial height of the blade.

Par rapport aux perturbateurs d'écoulement de l'air qui sont utilisés pour accroître les transferts thermiques, le déflecteur d'air selon l'invention se distingue en ce qu'il consiste, d'une part à projeter l'air sur la paroi opposée à celle de son implantation, et d'autre part à éviter un recollement immédiat de la couche limite. En revanche, un perturbateur d'écoulement de l'air a pour fonction essentielle d'augmenter la turbulence de l'écoulement de l'air au voisinage immédiat du perturbateur tout en cherchant à recoller le flux en aval de celui-ci. Comme représenté sur les figures 1 à 4, la présence de perturbateurs d'écoulement d'air 46 avec le déflecteur d'air 48, 48' selon l'invention n'est d'ailleurs pas incompatible.Compared to airflow disruptors which are used to increase the heat transfer, the air deflector according to the invention is distinguished in that it consists, on the one hand to project the air on the wall opposite to that of its implantation, and secondly to avoid an immediate gluing of the boundary layer. In contrast, an airflow disturbance has the essential function of increasing the turbulence of the flow of air in the immediate vicinity of the disturbance while seeking to re-glue the flow downstream thereof. As shown on Figures 1 to 4 , the presence of airflow disruptors 46 with the air deflector 48, 48 'according to the invention is also not incompatible.

La figure 3 représente de façon plus précise un mode de réalisation d'un déflecteur d'air 48 selon l'invention.The figure 3 shows more precisely one embodiment of an air deflector 48 according to the invention.

Le déflecteur d'air 48 comporte une rampe 52 qui est inclinée par rapport à la paroi 24a de la cavité 24 sur laquelle le déflecteur est implanté de façon à projeter l'air s'écoulant le long de cette paroi 24a vers la paroi opposée 24b.The air deflector 48 comprises a ramp 52 which is inclined with respect to the wall 24a of the cavity 24 on which the deflector is implanted so as to project the air flowing along this wall 24a towards the opposite wall 24b .

De façon avantageuse, la rampe inclinée 52 du déflecteur d'air 48 possède une longueur L qui est comprise entre 2 et 4 fois sa hauteur h. Par exemple, pour une cavité de refroidissement 24 ayant une largeur d (c'est-à-dire la distance séparant ses parois 24a, 24b) de l'ordre de 4 mm, la rampe 52 du déflecteur d'air 48 possède une hauteur h de l'ordre de 1,5 mm et une longueur L comprise entre 3 et 5 mm. A titre de comparaison, pour une cavité de refroidissement 24 ayant une largeur d de l'ordre de 3 mm, un perturbateur d'écoulement de l'air 46 tel que décrit précédemment possède une hauteur comprise entre 0,4 et 0,5 mm.Advantageously, the inclined ramp 52 of the air deflector 48 has a length L which is between 2 and 4 times its height h . For example, for a cooling cavity 24 having a width d (that is to say the distance separating its walls 24a, 24b) of the order of 4 mm, the ramp 52 of the air deflector 48 has a height h of the order of 1.5 mm and a length L of between 3 and 5 mm. By way of comparison, for a cooling cavity 24 having a width d of the order of 3 mm, an air-flow disruptor 46 as described above has a height of between 0.4 and 0.5 mm. .

Toujours de façon avantageuse, la rampe inclinée 52 du déflecteur d'air 48 est arrondie et présente un rayon de courbure R compris entre 20 et 30 mm. Cette valeur est donnée à titre d'exemple pour une cavité de refroidissement 24 ayant une largeur d de l'ordre de 4 mm. Un rayon de courbure R aussi important par rapport à la largeur d de la cavité 24 permet de déplacer l'air s'écoulant le long de la paroi 24a vers la paroi opposée 24b sans pour autant l'accélérer brutalement. On notera également que le rayon de courbure R de la rampe 52 du déflecteur est de préférence supérieur à la longueur L sur laquelle s'étend cette rampe.Still advantageously, the inclined ramp 52 of the air deflector 48 is rounded and has a radius of curvature R between 20 and 30 mm. This value is given as an example for a cooling cavity 24 having a width d of the order of 4 mm. A radius of curvature R as large relative to the width d of the cavity 24 makes it possible to move the air flowing along the wall 24a towards the opposite wall 24b without accelerating it suddenly. Note also that the radius of curvature R of the ramp 52 of the deflector is preferably greater than the length L on which extends this ramp.

Du côté opposé à la rampe inclinée 52, le déflecteur d'air 48 présente une autre rampe arrondie 54 dont le rayon de courbure r et la longueur I sur laquelle elle s'étend sont calculés de façon à éviter un recollement de la couche limite immédiatement en aval du déflecteur d'air. Notamment, le rayon de courbure r de cette autre rampe 54 doit être le plus faible possible pour atteindre ce but.On the opposite side to the inclined ramp 52, the air deflector 48 has another rounded ramp 54 whose radius of curvature r and the length I on which it extends are calculated so as to avoid re-bonding of the boundary layer immediately. downstream of the air deflector. In particular, the radius of curvature r of this other ramp 54 must be as small as possible to achieve this goal.

Sur l'exemple de réalisation des figures 1 à 3, l'écoulement de l'air dans la cavité bord d'attaque 24 est centrifuge, c'est-à-dire que l'air s'écoule du pied 12 vers le sommet 14 de l'aube. Dans ce type d'écoulement, le déflecteur d'air 48 est avantageusement disposé sur la paroi de la cavité 24 du circuit de refroidissement au niveau d'une zone d'attache de l'aube. Cette zone d'attache s'étend depuis l'extrémité radiale de l'aube située du côté de son pied 12 jusqu'à une plate-forme 56 délimitant la paroi interne de la veine d'écoulement des gaz traversant la turbine à gaz. Un tel emplacement du déflecteur d'air permet d'obtenir un échange thermique interne optimum à l'intrados de l'aube.On the example of realization of the Figures 1 to 3 , the flow of air in the leading edge cavity 24 is centrifugal, that is to say that the air flows from the foot 12 to the top 14 of the blade. In this type of flow, the air deflector 48 is advantageously disposed on the wall of the cavity 24 of the cooling circuit at a zone of attachment of the blade. This attachment zone extends from the radial end of the blade on the side of its foot 12 to a platform 56 defining the inner wall of the flow passage of the gas passing through the gas turbine. Such a location of the air deflector makes it possible to obtain an optimum internal heat exchange on the underside of the blade.

Sur l'exemple de réalisation de la figure 4, l'écoulement de l'air dans la cavité centrale 26 est centripète, c'est-à-dire que l'air s'écoule du sommet 14 vers le pied 12 de l'aube. Dans ce type d'écoulement, le déflecteur d'air 48' est avantageusement disposé sur la paroi de la cavité 26 du circuit de refroidissement au niveau du sommet 14 de l'aube. Un tel emplacement permet d'obtenir un échange thermique interne optimum à l'intrados de l'aube.On the example of realization of the figure 4 , the flow of air in the central cavity 26 is centripetal, that is to say that the air flows from the top 14 towards the foot 12 of dawn. In this type of flow, the air deflector 48 'is advantageously disposed on the wall of the cavity 26 of the cooling circuit at the top 14 of the blade. Such a location makes it possible to obtain an optimum internal heat exchange on the underside of the dawn.

On notera par ailleurs que la forme et les dimensions du déflecteur d'air 48' de ce mode de réalisation représenté par la figure 4 sont identiques à celles décrites en liaison avec les figures 1 à 3.Note also that the shape and dimensions of the air deflector 48 'of this embodiment represented by the figure 4 are identical to those described in connection with the Figures 1 to 3 .

En liaison avec la figure 5, on décrira maintenant un autre exemple d'emplacement d'un déflecteur d'air 48" selon l'invention.In connection with the figure 5 Another example of the location of an air deflector 48 "according to the invention will now be described.

Dans ce mode de réalisation, le déflecteur d'air 48" est positionné au niveau d'un passage 100 faisant communiquer l'extrémité radiale d'une cavité 102 d'un circuit interne de refroidissement d'une aube avec une extrémité radiale voisine d'une autre cavité 104 qui lui est adjacente. Un tel passage de communication 100 peut par exemple être l'un des passages 36 à 40 de l'aube des figures 1 à 3.In this embodiment, the air deflector 48 "is positioned at a passage 100 communicating the radial end of a cavity 102 of an internal cooling circuit of a blade with a radial end adjacent to another cavity 104 adjacent thereto, such a communication passage 100 may for example be one of the passages 36 to 40 of the dawn of Figures 1 to 3 .

Le déflecteur d'air 48" est disposé sur l'une des parois 104a de la cavité 104 et sa forme et ses dimensions sont adaptées pour projeter l'air s'écoulant le long de cette paroi 104a vers la paroi opposée 104b tout en évitant un recollement de la couche limite immédiatement en aval du déflecteur d'air.The air baffle 48 "is disposed on one of the walls 104a of the cavity 104 and its shape and dimensions are adapted to project the air flowing along the wall 104a to the opposite wall 104b while avoiding a bonding of the boundary layer immediately downstream of the air deflector.

De façon plus précise, le déflecteur d'air 48" est positionné de telle sorte que l'air circulant dans la cavité 102 est projeté au niveau de son « retournement » dans la cavité adjacente 104 (c'est-à-dire au niveau du passage de communication 100) vers une zone 106 de circulation de l'air qui est située au niveau de l'extrémité radiale de la paroi opposée 104b de la cavité adjacente 104. Une telle zone 106 est d'ordinaire une zone dans laquelle la circulation de l'air est faible et non perturbée.More specifically, the air baffle 48 "is positioned such that the air flowing in the cavity 102 is projected at its" turn-over "into the adjacent cavity 104 (i.e. from the communication passage 100) to an air circulation zone 106 which is located at the radial end of the opposite wall 104b of the adjacent cavity 104. Such an area 106 is usually an area in which the Air circulation is low and undisturbed.

Dans cet exemple de réalisation, le déflecteur d'air 48" permet donc d'éviter tout risque de décollement de la couche limite au niveau de la zone de « retournement » de l'air entre les deux cavités 102, 104 du circuit de refroidissement.In this exemplary embodiment, the air deflector 48 "thus makes it possible to avoid any risk of detachment of the boundary layer at the level of the" reversal "zone of the air between the two cavities 102, 104 of the cooling circuit .

Claims (9)

  1. A gas turbine blade (10) comprising an internal cooling circuit consisting of at least one cavity (24, 26, 102, 104) extending radially between the base (12) and tip (14) of the blade, at least one air inlet aperture (34) at one radial end of the cavity (24, 26, 102, 104) and at least one air outlet orifice (44) opening into the cavity and emerging onto one of the faces (20, 22) of the blade, at least one of the walls (24a, 26a, 104a) of said cavity of the cooling circuit comprising at least one air deflector (48, 48', 48") whereof the shape and dimensions are adapted to project the air flowing along said wall (24a, 26a, 104a) of the cavity towards an opposite wall (24b, 26b, 104b) of said cavity whilst avoiding re-attachment of the boundary layer immediately downstream of said air deflector (48, 48', 48"), the blade being characterised in that the air deflector (48, 48', 48") has an inclined ramp (52) that is rounded and that has a length (L) of between 2 and 4 times its height (h) so as to project the air flowing along the wall (24a, 26a, 104a) of the cavity towards the opposite wall (24b, 26b, 104b), the inclined ramp (52) of the air deflector having a height (h) corresponding to approximately 37.5% of the distance separating the two opposite walls of the cavity of the cooling circuit.
  2. The blade according to claim 1, in which the inclined ramp (52) of the air deflector (48, 48', 48") has a radius of curvature (R) of between 20 and 30 mm.
  3. The blade according to claim 1 or claim 2, in which the wall (24a, 26a) of the cavity (24, 26) of the cooling circuit comprising the air deflector (48, 48') is disposed on the convex side (22) of the blade and the wall (24b, 26b) of said cavity onto which the air is projected is disposed on the concave side (20) of the blade.
  4. The blade according to any one of claims 1 to 3, in which the air deflector (48) is disposed on the wall (24a) of the cavity (24) of the cooling circuit in the region of an attachment zone of the blade.
  5. The blade according to any one of claims 1 to 4, in which the air deflector (48') is disposed on the wall (26a) of the cavity (26) of the cooling circuit in the region of the tip (14) of the blade.
  6. The blade according to any one of claims 1 to 3, in which the internal cooling circuit comprises at least two cavities (102, 104), the air deflector (48") being positioned in the region of a passage (100) connecting the radial end of one cavity (102) with a neighboring radial end of the other cavity (104).
  7. The blade according to any one of claims 1 to 6, in which the walls of the cavity (24, 26) of the cooling circuit are provided with a plurality of flow disrupters (46) intended to increase the heat transfers along these walls.
  8. A gas turbine comprising a plurality of blades according to any one of claims 1 to 7.
  9. A turbine engine comprising a gas turbine having a plurality of blades according to any one of claims 1 to 7.
EP06119232A 2005-08-25 2006-08-21 Air baffle for the cooling circuit of turbine blades Active EP1760261B1 (en)

Applications Claiming Priority (1)

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FR0508740A FR2890103A1 (en) 2005-08-25 2005-08-25 Movable gas turbine engine blade e.g. movable high-pressure turbine blade, has air deflector positioned based on air flow that is centrifugal or centripetal, to project air circulating in cavity towards wall of cavity

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EP1760261A1 EP1760261A1 (en) 2007-03-07
EP1760261B1 true EP1760261B1 (en) 2008-03-05

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KR101797370B1 (en) * 2016-07-04 2017-12-12 두산중공업 주식회사 Gas Turbine Blade
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KR102161765B1 (en) * 2019-02-22 2020-10-05 두산중공업 주식회사 Airfoil for turbine, turbine including the same
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DE602006000641T2 (en) 2009-03-26
FR2890103A1 (en) 2007-03-02
EP1760261A1 (en) 2007-03-07
US20070048136A1 (en) 2007-03-01
DE602006000641D1 (en) 2008-04-17
ES2303312T3 (en) 2008-08-01
CA2557112C (en) 2013-12-10
CA2557112A1 (en) 2007-02-25
US7192251B1 (en) 2007-03-20

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