EP1333155A1 - Cooled trailing edge for a high pressure turbine rotor blade - Google Patents

Cooled trailing edge for a high pressure turbine rotor blade Download PDF

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Publication number
EP1333155A1
EP1333155A1 EP03290140A EP03290140A EP1333155A1 EP 1333155 A1 EP1333155 A1 EP 1333155A1 EP 03290140 A EP03290140 A EP 03290140A EP 03290140 A EP03290140 A EP 03290140A EP 1333155 A1 EP1333155 A1 EP 1333155A1
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EP
European Patent Office
Prior art keywords
blade
slot
pressure turbine
dawn
cavity
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP03290140A
Other languages
German (de)
French (fr)
Inventor
Jacques Boury
Maurice Judet
Jacky Tabardin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA Moteurs SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA Moteurs SA filed Critical SNECMA Moteurs SA
Publication of EP1333155A1 publication Critical patent/EP1333155A1/en
Withdrawn legal-status Critical Current

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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
    • 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
    • F01D5/186—Film cooling
    • 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
    • F05B2240/00—Components
    • F05B2240/80—Platforms for stationary or moving blades
    • F05B2240/801—Platforms for stationary or moving blades cooled platforms
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms

Definitions

  • the present invention relates to the general field of turbomachine high pressure turbine blades, and more particularly to the vents of the cooling air of the moving blades of a high pressure turbine.
  • a turbomachine comprises a combustion chamber in which air and fuel are mixed before burning.
  • the gases resulting from this combustion flow downstream into the combustion chamber and then feed a high pressure turbine.
  • the high pressure turbine has one or several rows of moving blades circumferentially spaced all around the rotor of the turbine. Mobile blades of the high turbine pressure are thus subjected to the very high temperatures of combustion. These temperatures reach values widely superior to those that can withstand without damage the blades that are in contact with these gases, which has the effect of limiting their lifetime.
  • cooling air which is generally introduced into the dawn by its foot, crosses it in following a path formed by cavities practiced in the dawn before being ejected by slits opening on the surface of dawn on its edge leakage, as in the patent application EP 0 945 594, or on its side intrados, as in US Pat. No. 4,601,638. More specifically, these cooling air vents are usually divided between the foot and the top of this dawn, substantially perpendicular to a longitudinal axis of the dawn.
  • connection zone situated between this slot and the platform supporting the dawn is very poorly cooled, all the more more than, because of the large dimensions of this slot and because the centrifugal force generated by the rotation of the blade, the air evacuated by the slot tends to be diverted to the top of dawn. It results significant thermal gradients in the vicinity of the trailing edge which generate by conduction, at the connection zone, a creek particularly detrimental to the life of dawn.
  • the present invention therefore aims to overcome such a disadvantage by proposing a high-pressure turbine turbine blade presenting a new geometry that does not create a crack.
  • the invention aims also not to degrade the general mechanical strength of the dawn, part subjected to very important mechanical constraints. She aims finally a turbomachine high pressure turbine equipped with such blades mobile with improved thermal behavior.
  • turbomachine pressure comprising at least one cooling consisting of at least one radially extending cavity between a summit and a foot of dawn, of at least one opening air intake at a radial end of the cavity or cavities for supplying the cooling air cooling circuit (s), and of a plurality of slots opening in the cavity or cavities and opening on a side intrados of the dawn between the foot and the top of the dawn, so substantially perpendicular to a longitudinal axis of the dawn, and a zone connection is provided between a slot closest to the foot of the dawn and an upper surface of a platform defining a wall internal flow for a flow of flue gas through the high pressure turbine, characterized in that it also comprises an extra slot for cooling air evacuation practiced in said connection zone in the extension of the edge leak.
  • this additional slot has a shape taken in the group of the following forms: oblong, rectangular, triangular or inverted T and it is obtained directly from foundry.
  • this extra slot may have a section output different from that of its feed channel.
  • a longitudinal lower end of the additional slot is arranged just above said surface top of the platform.
  • FIG. 1 represents in perspective a moving blade 10, for example of a high pressure turbine of a turbomachine according to the present invention.
  • This blade of longitudinal axis X-X is fixed on a rotor disc (not shown) of the high pressure turbine by via a fitting 12 generally fir-shaped. It typically comprises a foot 14A, a vertex 14B, a wall 16A, an extrados wall 16B, leading edge 18 and an edge of 20.
  • the fitting 12 is connected to the foot 14A of the dawn level a platform 22 defining an internal wall for the vein flow of combustion gases through the high turbine pressure.
  • the blade 10 has at least one circuit of internal cooling composed for example of at least one cavity 24 extending radially between the foot 14A and the vertex 14B of the blade.
  • This cavity is supplied with cooling air to one of its radial ends through an air inlet opening (not shown).
  • This air intake opening is generally provided at the level of the fitting 12 of the dawn.
  • the slots 26 for exhausting the cooling air are typically distributed between the foot 14A and the summit 14B of the dawn, substantially perpendicular to the longitudinal axis X-X of the blade. More particularly, the slot 28 closest to the foot 14A of the dawn 10 is formed just above a connection zone 30 between the foot 14A of the dawn and an upper surface 22A of the platform 22 on the side of the flow of flue gas.
  • FIG. 2 and Figures 2A through 2C illustrate more precisely the geometry of the trailing edge 20 of the dawn at this level connection area with the slot 28 closest to the foot 14A of dawn 10.
  • a slot is provided additional opening in the cavity 24 and opening into said area connection in the extension of the trailing edge 20.
  • This slot additional 32 provides convective cooling of this part of the connection area and, by conduction, of the slot the closer to the foot of dawn and part of the platform located in the extension of the trailing edge.
  • Cooling air evacuated by this additional slot covers indeed the whole surface of the connection area at the trailing edge and lowers the local temperature of about 10%, without changing the aerodynamic performance provided by the vents of the side intrados.
  • the extra slot can have different shapes determined according to the criteria of thermal design and mechanics desired.
  • the feed channel and the orifice output can be of different sections.
  • Figure 2 illustrates a additional slot having a feed channel and an orifice elongate output, advantageously oblong (a section rectangular is also possible).
  • the output section is always oblong but the internal feed channel is substantially triangular, ie flared on both sides of this hole outlets, so as to ensure better cooling of the connection while having a perfectly calibrated output flow. according to the thermal stresses and the mechanical forces undergone by the dawn, this Variable angle flare can be asymmetrical and therefore point that to only one side, as shown in Figure 2B.
  • This slot is advantageously obtained directly from foundry at the same time as the dawn itself (and not machined next) and it crosses the dawn to the cavity 24 while remaining constantly just above the level of the upper surface of the platform (this is mean that its lower longitudinal end 32A or 34A is above of this upper surface 22A). So, it's this additional slot that suffers the effects of the metal casting pressure and not the most 28 slot close to the foot of the dawn, as in the prior art, and any risk of weakening of the blade due to machining is rejected.

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

Abstract

The blade (10) has at least one cavity (24) radially extending between its tip and its base to form at least one cooling circuit. Air is discharged from the cavity through exhaust slots (26) opened to the blade trailing edge (20). A connection zone (30) is formed between the blade base and the platform (22) top surface. An auxiliary exhaust slot leads air from the cavity to the discharge side of the zone. An Independent claim is also included for a high-pressure turbine.

Description

Arrière-plan de l'inventionBackground of the invention

La présente invention se rapporte au domaine général des aubes mobiles de turbine haute pression d'une turbomachine, et plus particulièrement aux fentes d'évacuation de l'air de refroidissement des aubes mobiles d'une turbine haute pression.The present invention relates to the general field of turbomachine high pressure turbine blades, and more particularly to the vents of the cooling air of the moving blades of a high pressure turbine.

De façon connue en soi, une turbomachine comporte une chambre de combustion dans laquelle de l'air et du carburant sont mélangés avant d'y être brûlés. Les gaz issus de cette combustion s'écoulent vers l'aval dans la chambre de combustion et alimentent ensuite une turbine haute pression. La turbine haute pression comporte une ou plusieurs rangées d'aubes mobiles espacées de façon circonférentielle tout autour du rotor de la turbine. Les aubes mobiles de la turbine haute pression sont ainsi soumises aux températures très élevées des gaz de combustion. Ces températures atteignent des valeurs largement supérieures à celles que peuvent supporter sans dommages les aubes qui sont en contact avec ces gaz, ce qui a pour conséquence de limiter leur durée de vie.In a manner known per se, a turbomachine comprises a combustion chamber in which air and fuel are mixed before burning. The gases resulting from this combustion flow downstream into the combustion chamber and then feed a high pressure turbine. The high pressure turbine has one or several rows of moving blades circumferentially spaced all around the rotor of the turbine. Mobile blades of the high turbine pressure are thus subjected to the very high temperatures of combustion. These temperatures reach values widely superior to those that can withstand without damage the blades that are in contact with these gases, which has the effect of limiting their lifetime.

Afin de résoudre ce problème, il est connu de munir ces aubes de circuits de refroidissement internes visant à réduire la température de ces dernières. Grâce à de tels circuits, de l'air de refroidissement, 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 fentes s'ouvrant à la surface de l'aube sur son bord de fuite, comme dans la demande de brevet EP 0 945 594, ou sur son coté intrados, comme dans le brevet US 4 601 638. Plus précisément, ces fentes d'évacuation de l'air de refroidissement sont généralement réparties entre le pied et le sommet de cette aube, de façon sensiblement perpendiculaire à un axe longitudinal de l'aube.In order to solve this problem, it is known to provide these vanes internal cooling circuits to reduce the temperature of these last. Through such circuits, cooling air, which is generally introduced into the dawn by its foot, crosses it in following a path formed by cavities practiced in the dawn before being ejected by slits opening on the surface of dawn on its edge leakage, as in the patent application EP 0 945 594, or on its side intrados, as in US Pat. No. 4,601,638. More specifically, these cooling air vents are usually divided between the foot and the top of this dawn, substantially perpendicular to a longitudinal axis of the dawn.

Il est également connu que les aubes de turbine haute pression équipées de circuits de refroidissement sont réalisées par moulage. Les emplacements des fentes des circuits de refroidissement sont classiquement réservés par des noyaux disposés parallèlement entre eux dans le moule avant la coulée du métal. Pour éviter une fragilisation du noyau lors de la coulée, la fente d'évacuation de l'air de refroidissement la plus proche du pied de l'aube est généralement réalisée dans des dimensions plus importantes que celles des autres fentes comme l'illustre la figure 3 et le brevet américain précité.It is also known that high pressure turbine blades equipped with cooling circuits are made by molding. The Slots locations of the cooling circuits are classically reserved by nuclei arranged parallel to each other in the mold before casting the metal. To avoid embrittlement core during casting, the cooling air vent slot the closer to the foot of dawn is usually carried out in dimensions larger than those of other slots as illustrated Figure 3 and the aforementioned US patent.

Or, dans la pratique, la zone de raccordement située entre cette fente et la plate-forme supportant l'aube est très mal refroidie, d'autant plus que, à cause des dimensions importantes de cette fente et en raison de la force centrifuge engendrée par la rotation de l'aube, l'air évacué par la fente a tendance à être dévié vers le sommet de l'aube. Il en résulte des gradients thermiques importants au voisinage du bord de fuite qui génèrent par conduction, au niveau de la zone de raccordement, une crique particulièrement préjudiciable à la durée de vie de l'aube.In practice, however, the connection zone situated between this slot and the platform supporting the dawn is very poorly cooled, all the more more than, because of the large dimensions of this slot and because the centrifugal force generated by the rotation of the blade, the air evacuated by the slot tends to be diverted to the top of dawn. It results significant thermal gradients in the vicinity of the trailing edge which generate by conduction, at the connection zone, a creek particularly detrimental to the life of dawn.

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

La présente invention vise donc à pallier un tel inconvénient en proposant une aube mobile de turbine haute pression présentant une nouvelle géométrie qui n'engendre pas de crique. L'invention vise également à ne pas dégrader la tenue mécanique générale de l'aube, pièce soumise à des contraintes mécaniques très importantes. Elle vise enfin une turbiné haute pression de turbomachine équipée de telles aubes mobiles au comportement thermique amélioré.The present invention therefore aims to overcome such a disadvantage by proposing a high-pressure turbine turbine blade presenting a new geometry that does not create a crack. The invention aims also not to degrade the general mechanical strength of the dawn, part subjected to very important mechanical constraints. She aims finally a turbomachine high pressure turbine equipped with such blades mobile with improved thermal behavior.

A cet effet, il est prévu une aube mobile de turbine haute pression de turbomachine, comprenant au moins un circuit de refroidissement composé d'au moins une cavité s'étendant radialement entre un sommet et un pied de l'aube, d'au moins une ouverture d'admission d'air à une extrémité radiale de la ou des cavités pour alimenter le ou les circuits de refroidissement en air de refroidissement, et d'une pluralité de fentes s'ouvrant dans la ou les cavités et débouchant sur un coté intrados de l'aube entre le pied et le sommet de l'aube, de façon sensiblement perpendiculaire à un axe longitudinal de l'aube, et une zone de raccordement est prévue entre une fente la plus proche du pied de l'aube et une surface supérieure d'une plate-forme définissant une paroi interne pour une veine d'écoulement de gaz de combustion au travers de la turbine haute pression, caractérisée en ce qu'elle comporte en outre une fente supplémentaire d'évacuation de l'air de refroidissement pratiquée dans ladite zone de raccordement dans le prolongement du bord de fuite.For this purpose, a high turbine rotor blade is provided. turbomachine pressure, comprising at least one cooling consisting of at least one radially extending cavity between a summit and a foot of dawn, of at least one opening air intake at a radial end of the cavity or cavities for supplying the cooling air cooling circuit (s), and of a plurality of slots opening in the cavity or cavities and opening on a side intrados of the dawn between the foot and the top of the dawn, so substantially perpendicular to a longitudinal axis of the dawn, and a zone connection is provided between a slot closest to the foot of the dawn and an upper surface of a platform defining a wall internal flow for a flow of flue gas through the high pressure turbine, characterized in that it also comprises an extra slot for cooling air evacuation practiced in said connection zone in the extension of the edge leak.

De la sorte, l'air de refroidissement évacué par cette fente additionnelle est guidé au niveau du bord de fuite sur toute la surface de la zone de raccordement de façon à éviter que des criques n'apparaissent au niveau de celle-ci. Cette géométrie particulière du pied d'aube permet d'abaisser de 10% environ la température locale au niveau de cette zone tout en conservant les performances aérodynamiques procurées par les fentes d'évacuation de coté intrados. Dès lors, il n'est plus nécessaire que la fente la plus proche de l'aube présente des dimensions supérieures aux autres fentes car c'est maintenant la fente additionnelle qui subit les effets de pression dus à la coulée du métal. En outre, la fente la plus proche de l'aube reprenant des dimensions normales, le problème posé par la déviation de l'air de refroidissement due à la force centrifuge est éliminé et les pertes en termes de débit en résultant sont donc réduites. Enfin, la tenue de l'aube aux différentes contraintes mécaniques auxquelles elle est soumise n'est pas détériorée par cette géométrie particulière.In this way, the cooling air evacuated by this slot additional is guided at the trailing edge over the entire surface of the connection area to prevent cracks from appearing at this level. This particular geometry of the blade root allows to reduce by 10% the local temperature in this area while maintaining the aerodynamic performance provided by evacuation slots on the intrados side. Therefore, it is no longer necessary the slot closest to dawn has larger dimensions than other slots because it is now the additional slot that suffers the effects pressure due to the casting of the metal. In addition, the slot closest to the dawn resumed normal dimensions, the problem posed by the deflection of cooling air due to centrifugal force is eliminated and the resulting losses in terms of throughput are therefore reduced. Finally, holding the dawn to the different mechanical stresses to which it is subject is not deteriorated by this particular geometry.

De préférence, cette fente supplémentaire présente une forme prise dans le groupe des formes suivantes : oblongue, rectangulaire, triangulaire ou en T inversé et elle est obtenue directement de fonderie.Preferably, this additional slot has a shape taken in the group of the following forms: oblong, rectangular, triangular or inverted T and it is obtained directly from foundry.

En outre, cette fente supplémentaire peut présenter une section de sortie différente de celle de son canal d'alimentation.In addition, this extra slot may have a section output different from that of its feed channel.

Avantageusement, une extrémité inférieure longitudinale de la fente supplémentaire est disposée juste au-dessus de ladite surface supérieure de la plate-forme.Advantageously, a longitudinal lower end of the additional slot is arranged just above said surface top of the platform.

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 perspective d'une aube mobile de turbine haute pression selon l'invention ;
  • la figure 2 est une vue partielle agrandie de la figure 1 montrant un premier exemple de réalisation de la fente supplémentaire d'évacuation de l'air de refroidissement pratiquée dans la zone de raccordement entre le pied de l'aube et la plate-forme,
  • les figures 2A et 2B sont des vues en bout du bord de fuite au niveau de la zone de raccordement avec la plate-forme de deux variantes de réalisation de la fente supplémentaire d'évacuation de l'air de refroidissement,
  • la figure 2C est une vue en coupe selon le plan AA de la figure 2A,
  • la figure 3 est une vue partielle agrandie de la figure 1 illustrant un second exemple de réalisation de la fente supplémentaire d'évacuation de l'air de refroidissement,
  • la figure 4 est une vue d'un pied d'aube et de la zone de raccordement entre ce pied et la plate-forme dans une aube de l'art antérieur.
Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate an embodiment having no limiting character. In the figures:
  • Figure 1 is a perspective view of a moving blade of high pressure turbine according to the invention;
  • FIG. 2 is an enlarged partial view of FIG. 1 showing a first embodiment of the additional cooling air discharge slot made in the connection zone between the blade root and the platform,
  • FIGS. 2A and 2B are end views of the trailing edge at the connection zone with the platform of two alternative embodiments of the additional cooling air discharge slot,
  • FIG. 2C is a sectional view along the plane AA of FIG. 2A,
  • FIG. 3 is an enlarged partial view of FIG. 1 illustrating a second exemplary embodiment of the additional slot for evacuating the cooling air,
  • Figure 4 is a view of a blade root and the connection area between the foot and the platform in a dawn of the prior art.

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

La figure 1 représente en perspective une aube mobile 10, par exemple d'une turbine haute pression d'une turbomachine conforme à la présente invention. Cette aube d'axe longitudinal X-X est fixée sur un disque rotor (non représenté) de la turbine haute pression par l'intermédiaire d'un emmanchement 12 généralement en forme de sapin. Elle comporte typiquement un pied 14A, un sommet 14B, une paroi intrados 16A, une paroi extrados 16B, bord d'attaque 18 et un bord de fuite 20. L'emmanchement 12 se raccorde au pied 14A de l'aube au niveau d'une plate-forme 22 définissant une paroi interne pour la veine d'écoulement des gaz de combustion au travers de la turbine haute pression.FIG. 1 represents in perspective a moving blade 10, for example of a high pressure turbine of a turbomachine according to the present invention. This blade of longitudinal axis X-X is fixed on a rotor disc (not shown) of the high pressure turbine by via a fitting 12 generally fir-shaped. It typically comprises a foot 14A, a vertex 14B, a wall 16A, an extrados wall 16B, leading edge 18 and an edge of 20. The fitting 12 is connected to the foot 14A of the dawn level a platform 22 defining an internal wall for the vein flow of combustion gases through the high turbine pressure.

Une telle aube est soumise aux températures très élevées des gaz de combustion et nécessite donc d'être refroidie. A cet effet, et de façon connue en soi, l'aube mobile 10 comporte au moins un circuit de refroidissement interne composé par exemple d'au moins une cavité 24 s'étendant radialement entre le pied 14A et le sommet 14B de l'aube. Cette cavité est alimentée en air de refroidissement à l'une de ses extrémités radiales par une ouverture d'admission d'air (non représentée). Cette ouverture d'admission d'air est généralement prévue au niveau de l'emmanchement 12 de l'aube. Il est également prévu une pluralité de fentes 26 s'ouvrant dans la cavité 24 et débouchant, dans l'exemple illustré, sur le coté intrados 16A de l'aube afin d'évacuer l'air de refroidissement s'écoulant dans la cavité. Cette disposition des fentes d'évacuation directement au travers de la paroi intrados 16A de l'aube est préférable à celle sur le bord de fuite (qui nécessite une épaisseur d'aube plus importante), du fait des performances aérodynamiques meilleures qu'elle autorise. Les fentes 26 d'évacuation de l'air de refroidissement sont typiquement réparties entre le pied 14A et le sommet 14B de l'aube, de façon sensiblement perpendiculaire à l'axe longitudinal X-X de l'aube. Plus particulièrement, la fente 28 la plus proche du pied 14A de l'aube 10 est formée juste au-dessus d'une zone de raccordement 30 entre le pied 14A de l'aube et une surface supérieure 22A de la plate-forme 22 du côté de la veine d'écoulement des gaz de combustion.Such a dawn is subject to the very high temperatures of combustion gas and therefore needs to be cooled. For this purpose, and known manner, the blade 10 has at least one circuit of internal cooling composed for example of at least one cavity 24 extending radially between the foot 14A and the vertex 14B of the blade. This cavity is supplied with cooling air to one of its radial ends through an air inlet opening (not shown). This air intake opening is generally provided at the level of the fitting 12 of the dawn. It is also planned a plurality of slots 26 opening in the cavity 24 and opening, in the example illustrated, on the intrados side 16A of the dawn to evacuate the air of cooling flowing in the cavity. This disposition of the slots evacuation directly through the intrados wall 16A of the dawn is preferable to that on the trailing edge (which requires a dawn thickness more important), because of the better aerodynamic performance that she authorizes. The slots 26 for exhausting the cooling air are typically distributed between the foot 14A and the summit 14B of the dawn, substantially perpendicular to the longitudinal axis X-X of the blade. More particularly, the slot 28 closest to the foot 14A of the dawn 10 is formed just above a connection zone 30 between the foot 14A of the dawn and an upper surface 22A of the platform 22 on the side of the flow of flue gas.

La perspective de la figure 2 et les figures 2A à 2C illustrent plus précisément la géométrie du bord de fuite 20 de l'aube au niveau de cette zone de raccordement avec la fente 28 la plus proche du pied 14A de l'aube 10.The perspective of Figure 2 and Figures 2A through 2C illustrate more precisely the geometry of the trailing edge 20 of the dawn at this level connection area with the slot 28 closest to the foot 14A of dawn 10.

Conformément à l'invention, il est prévu une fente supplémentaire s'ouvrant dans la cavité 24 et débouchant dans ladite zone de raccordement dans le prolongement du bord de fuite 20. Cette fente supplémentaire 32 permet d'assurer un refroidissement par convection de cette partie de la zone de raccordement et, par conduction, de la fente la plus proche du pied de l'aube et d'une partie de la plate-forme située dans le prolongement du bord de fuite. Ainsi, en homogénéisant la température au niveau de celle-ci, il est possible de supprimer tout point chaud et ainsi d'améliorer le comportement thermique de l'aube. L'air de refroidissement évacué par cette fente additionnelle recouvre en effet toute la surface de la zone de raccordement au niveau du bord de fuite et en abaisse la température locale de 10% environ, et cela sans modifier les performances aérodynamiques que procurent les fentes d'évacuation du coté intrados. Ainsi, tout risque de crique au niveau de cette zone de raccordement entre le pied de l'aube et la plate-forme disparaít et la durée de vie de l'aube s'en trouve rallongée. Dès lors, il n'est plus nécessaire que la fente 28 la plus proche du pied de l'aube présente des dimensions supérieures aux autres fentes 26, comme l'illustre l'art antérieur de la figure 4 et, en reprenant des dimensions normales, le problème posé par la déviation de l'air de refroidissement au niveau de cette fente, due à la force centrifuge, est éliminé ainsi que les pertes en termes de débit en résultant.According to the invention, a slot is provided additional opening in the cavity 24 and opening into said area connection in the extension of the trailing edge 20. This slot additional 32 provides convective cooling of this part of the connection area and, by conduction, of the slot the closer to the foot of dawn and part of the platform located in the extension of the trailing edge. Thus, by homogenizing the temperature at the level of this one, it is possible to remove any hot spot and so to improve the thermal behavior of the dawn. Cooling air evacuated by this additional slot covers indeed the whole surface of the connection area at the trailing edge and lowers the local temperature of about 10%, without changing the aerodynamic performance provided by the vents of the side intrados. Thus, any risk of crack in this area of connection between the foot of the dawn and the platform vanishes and the duration life of dawn is lengthened. Therefore, it is no longer necessary that the slot 28 closest to the foot of the dawn has dimensions higher than the other slots 26, as illustrated by the prior art of the Figure 4 and, taking again normal dimensions, the problem posed by the deviation of the cooling air at this slot, due to the centrifugal force, is eliminated as well as the losses in terms of flow in resulting.

La fente supplémentaire peut présenter différentes formes déterminées en fonction des critères de dimensionnement thermique et mécanique souhaités. De même, le canal d'alimentation et l'orifice de sortie peuvent être de sections différentes. Ainsi, la figure 2 illustre une fente supplémentaire présentant un canal d'alimentation et un orifice de sortie de forme allongée, avantageusement oblongue (une section rectangulaire est aussi envisageable). Sur la figure 2A, la section en sortie est toujours oblongue mais le canal interne d'alimentation est sensiblement triangulaire, c'est à dire évasé de part et d'autre de ce trou de sortie, de sorte à assurer un meilleur refroidissement de la zone de raccordement tout en ayant un débit de sortie parfaitement calibré. Selon les contraintes thermiques et les efforts mécaniques subis par l'aube, cet évasement d'angle variable peut être dissymétrique et donc se diriger que vers un seul coté, comme l'illustre la figure 2B.The extra slot can have different shapes determined according to the criteria of thermal design and mechanics desired. Similarly, the feed channel and the orifice output can be of different sections. Thus, Figure 2 illustrates a additional slot having a feed channel and an orifice elongate output, advantageously oblong (a section rectangular is also possible). In Figure 2A, the output section is always oblong but the internal feed channel is substantially triangular, ie flared on both sides of this hole outlets, so as to ensure better cooling of the connection while having a perfectly calibrated output flow. according to the thermal stresses and the mechanical forces undergone by the dawn, this Variable angle flare can be asymmetrical and therefore point that to only one side, as shown in Figure 2B.

Une variante de réalisation de la fente additionnelle dont le canal d'alimentation présente une forme en T inversé confondue avec celle de l'orifice de sortie 34 est également illustré à la figure 3.An alternative embodiment of the additional slot whose feed channel has an inverted T shape merged with that of the outlet orifice 34 is also illustrated in FIG.

Cette fente est avantageusement obtenue directement de fonderie en même temps que l'aube elle-même (et non usinée ensuite) et elle traverse l'aube jusqu'à la cavité 24 tout en restant constamment juste au-dessus du niveau de la surface supérieure de la plate-forme (c'est à dire que son extrémité inférieure longitudinale 32A ou 34A est au-dessus de cette surface supérieure 22A). Ainsi, c'est cette fente additionnelle qui subit les effets de la pression de coulée de métal et non la fente 28 la plus proche du pied de l'aube, comme dans l'art antérieur, et tout risque de fragilisation de l'aube lié à un usinage est écarté.This slot is advantageously obtained directly from foundry at the same time as the dawn itself (and not machined next) and it crosses the dawn to the cavity 24 while remaining constantly just above the level of the upper surface of the platform (this is mean that its lower longitudinal end 32A or 34A is above of this upper surface 22A). So, it's this additional slot that suffers the effects of the metal casting pressure and not the most 28 slot close to the foot of the dawn, as in the prior art, and any risk of weakening of the blade due to machining is rejected.

Claims (6)

Aube mobile de turbine haute pression de turbomachine, comprenant au moins un circuit de refroidissement composé d'au moins une cavité (24) s'étendant radialement entre un sommet (16) et un pied (14) de l'aube (10), d'au moins une ouverture d'admission d'air à une extrémité radiale de la ou les cavités pour alimenter le ou les circuits de refroidissement en air de refroidissement, et d'une pluralité de fentes (26) s'ouvrant dans la ou des cavités et débouchant sur un coté intrados de l'aube (16A) entre le pied et le sommet de l'aube, de façon sensiblement perpendiculaire à un axe longitudinal (X-X) de l'aube, et une zone de raccordement (30) est prévue entre une fente (28) la plus proche du pied de l'aube et une surface supérieure (22A) d'une plate-forme (22) définissant une paroi interne pour une veine d'écoulement de gaz de combustion au travers de la turbine haute pression, caractérisée en ce qu'elle comporte en outre une fente supplémentaire (32, 34) d'évacuation de l'air de refroidissement s'ouvrant dans ladite cavité et débouchant dans ladite zone de raccordement dans le prolongement du bord de fuite (20).A turbomachine turbine high pressure turbine blade, comprising at least one cooling circuit composed of at least one cavity (24) extending radially between a top (16) and a root (14) of the blade (10), at least one air inlet opening at a radial end of the at least one cavity for supplying the at least one cooling air cooling circuit, and at a plurality of slots (26) opening at or cavities and opening on an intrados side of the blade (16A) between the foot and the apex of the blade, substantially perpendicular to a longitudinal axis (XX) of the blade, and a connecting zone (30) is provided between a slot (28) closest to the root of the blade and an upper surface (22A) of a platform (22) defining an inner wall for a stream of flue gas flow through the high pressure turbine, characterized in that it further comprises an additional slot (32, 34) for evacuating there is cooling air opening in said cavity and opening into said connection zone in the extension of the trailing edge (20). Aube selon la revendication 1, caractérisée en ce que ladite fente supplémentaire présente une forme prise dans le groupe des formes suivantes : oblongue, rectangulaire, triangulaire ou en T inversé.A blade according to claim 1, characterized in that said additional slot has a shape taken from the group of the following forms: oblong, rectangular, triangular or inverted T. Aube selon la revendication 2, caractérisée en ce que ladite fente supplémentaire présente une section de sortie différente de celle de son canal d'alimentation.A blade according to claim 2, characterized in that said additional slot has an exit section different from that of its supply channel. Aube selon la revendication 1, caractérisée en ce que ladite fente supplémentaire est obtenue directement de fonderie.Blade according to Claim 1, characterized in that the said additional slot is obtained directly from a foundry. Aube selon l'une quelconque des revendications 1 à 4, caractérisée en ce qu'une extrémité inférieure longitudinale (32A, 34A) de la fente supplémentaire est disposée juste au-dessus de ladite surface supérieure de la plate-forme. A blade according to any one of claims 1 to 4, characterized in that a lower longitudinal end (32A, 34A) of the additional slot is disposed just above said upper surface of the platform. Turbine haute-pression de turbomachine, caractérisée en ce qu'elle comporte une pluralité d'aubes mobiles (10) selon l'une quelconque des revendications précédentes.A turbomachine high-pressure turbine, characterized in that it comprises a plurality of moving blades (10) according to any one of the preceding claims.
EP03290140A 2002-01-23 2003-01-21 Cooled trailing edge for a high pressure turbine rotor blade Withdrawn EP1333155A1 (en)

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FR0200802A FR2835015B1 (en) 2002-01-23 2002-01-23 HIGH-PRESSURE TURBINE MOBILE TURBINE WITH IMPROVED THERMAL BEHAVIOR LEAKAGE EDGE
FR0200802 2002-01-23

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CA2418241A1 (en) 2003-07-23
CN1436919A (en) 2003-08-20
FR2835015B1 (en) 2005-02-18
FR2835015A1 (en) 2003-07-25
US20030138322A1 (en) 2003-07-24
JP2003214108A (en) 2003-07-30

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