EP1790819B1 - Turbine blade comprising a cooling circuit - Google Patents

Turbine blade comprising a cooling circuit Download PDF

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Publication number
EP1790819B1
EP1790819B1 EP06124041.2A EP06124041A EP1790819B1 EP 1790819 B1 EP1790819 B1 EP 1790819B1 EP 06124041 A EP06124041 A EP 06124041A EP 1790819 B1 EP1790819 B1 EP 1790819B1
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EP
European Patent Office
Prior art keywords
cavity
blade
suction
pressure
cooling circuit
Prior art date
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Active
Application number
EP06124041.2A
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German (de)
French (fr)
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EP1790819A1 (en
Inventor
Pascal Deschamps
Patrice Eneau
Thomas Potier
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 SAS
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Publication date
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Publication of EP1790819A1 publication Critical patent/EP1790819A1/en
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Classifications

    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/712—Shape curved concave
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film 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
    • F05D2260/2214—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 turbomachine moving blades, and in particular to the blades of the high-pressure turbine.
  • EP-A-1,584,790 discloses a blade according to the preamble of claim 1.
  • the main object of the present invention is thus to overcome such disadvantages by proposing a central cooling circuit of a mobile blade for efficient cooling of the blade at a low manufacturing cost.
  • a turbomachine moving blade is provided according to claim 1.
  • the intrados and extrados cooling circuits thus defined present an asymmetry of configuration between the intrados and the extrados and are specific to each wall (intrados, extrados) of the dawn.
  • the levels of heat exchange which are lower on the intrados than on the upper surface of the dawn.
  • the extrados cooling circuit may comprise a first cavity and a second cavity extending on the extrados side of the blade, a third cavity extending from the intrados to the extrados of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other radial end of the second cavity with a radial end adjacent to the third cavity, and outlet orifices opening in the third cavity and opening on the intrados face of the blade.
  • the third cavity of such an extrados cooling circuit can be arranged on the side of the leading edge or trailing edge of the blade.
  • the extrados cooling circuit may comprise a first cavity and a second cavity extending on the extrados side of the blade, a third cavity extending on the intrados side of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other end; radial of the second cavity with a radial end adjacent to the third cavity, and outlet orifices opening in the third cavity and opening on the intrados face of the blade.
  • the third cavity of such an extrados cooling circuit can be disposed on the leading edge side or the trailing edge of the blade.
  • the intrados cooling circuit may comprise a first, a second and a third cavity extending on the intrados side of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other radial end of the second cavity with a radial end adjacent to the third cavity; , and outlets opening in the third cavity and opening on the intrados face of the blade.
  • the blade may also comprise a cooling circuit of the leading edge of the blade and a cooling circuit of the trailing edge of the blade.
  • the invention also relates to a gas turbine comprising at least one moving blade as defined above.
  • the invention also relates to a turbomachine comprising at least one moving blade as defined above.
  • the figure 1 represents 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 also be applied to other blades of the turbomachine, for example to the blades of the low-pressure turbine thereof.
  • the blade 10 has an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14 ( figures 3 and 4 ).
  • This aerodynamic surface consists of a leading edge 16 disposed opposite the flow of hot gases from the combustion chamber of the turbomachine, a trailing edge 18 opposite to the leading edge 16, of 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 has a central portion C which occupies the geometric zone of the blade for which the distance between its intrados 20 and extrados faces 22 is the largest.
  • the central part C of the blade is divided geometrically into four adjacent intrados zones Z1 to Z4 disposed on the intrados side of the blade and in four adjacent extrados zones Z5 to Z8 disposed on the extrados side, the intrados and extrados zones being distributed from on both sides of the skeleton S of dawn.
  • Skeleton of the dawn means the geometric line S points equidistant from the side faces intrados 20 and extrados 22 of the blade.
  • the skeleton S of the blade defines two main areas of the central portion C of the blade which are each divided into four adjacent zones by three geometric lines L1 to L3 radially cutting the blade in the direction of its thickness.
  • the intrados geometrical zones Z1 to Z4 and extrados Z5 to Z8 thus defined constitute the smallest elements that can contain a cooling cavity.
  • these zones extend in cross-section on a surface typically comprised between 3 and 10 mm 2 approximately.
  • the central portion C of the blade is provided with a lower pressure cooling circuit and an extrados cooling circuit, the intrados cooling circuit comprising three radial cavities occupying three adjacent intrados zones, and the cooling circuit extrados cooling comprising three radial cavities occupying the four extrados areas and the remaining intrados area.
  • radial cavity is meant for the rest of the description, a cavity extending radially between the foot 12 and the top 14 of the blade.
  • the inner cooling circuit of the blade 10a comprises three radial cavities 24a, 26a and 28a respectively occupying the three adjacent intrados zones Z3, Z2 and Z1 of the figure 1 .
  • the extrados cooling circuit of the blade comprises three extrados radial cavities 30a, 32a and 34a occupying the four extrados zones Z5 to Z8 and the remaining intrados zone Z4.
  • the upper surface of the blade has a first cavity 30a extending on the upper surface of the blade and occupying the extrados zone Z5, a second cavity 32a extending on the upper surface of the blade and occupying the zones. extrados Z6 and Z7, and a third cavity 34a extending from the intrados face 20 to the extrados face 22 of the blade and occupying the extrados zone Z8 and the intrados zone Z4.
  • cavity extending on the upper surface of the blade is meant a cavity which extends in the direction of the thickness of the blade from the extrados face 22 of the blade to its skeleton S.
  • the cavities 30a to 34a of the extrados cooling circuit are cavities having cross sections greater than about 4 mm 2 .
  • the third cavity 34a of this extrados circuit which extends from the intrados face 20 to the extrados face 22 of the blade is disposed on the side of the trailing edge 18 of the blade.
  • the extrados cooling circuit also comprises an air inlet opening 36 at a radial end of the first cavity 30a (here at the foot 12 of the blade) to supply air to the extrados circuit.
  • a first passage 38 communicates the other radial end of the first cavity 30a (that is to say at the top 14 of the blade) with a radial end adjacent to the second cavity 32a.
  • a second passage 40 communicates the other radial end of the second cavity 32a with a radial end adjacent to the third cavity 34a.
  • outlet orifices 42a open into the third cavity 34a and open on the underside face 20 of the blade. These outlet orifices 42a are regularly distributed over the entire radial height of the blade.
  • the circulation of the cooling air which runs through this extrados circuit derives evidently from the foregoing.
  • the circuit is supplied with cooling air through the inlet opening 36.
  • the air first passes through the first cavity 30a (according to a centrifugal flow) and then the second extrados cavity 32a (according to a centripetal flow) and finally the cavity central 34a (according to a centrifugal flow) before being emitted at the underside 20 of the blade through the outlet orifices 42a.
  • the cooling circuit intrados dawn comprises a first cavity 24a occupying the intrados zone Z3, a second cavity 26a occupying the intrados zone Z2 and a third cavity 28a occupying the intrados zone Z1.
  • cavities 24a to 28a extend on the intrados side of the blade, that is to say they extend in the direction of the thickness of the blade from the intrados face 20 of the blade until 'to his skeleton S.
  • cavities 24a to 28a are cavities having cross sections less than about 15 mm 2 .
  • the intrados cooling circuit also comprises an air inlet opening 44 at a radial end of the first cavity 24a (here at the foot 12 of the blade) for supplying air to the intrados circuit.
  • a first passage 46 communicates the other radial end (at the top 14 of the blade) of the first cavity 24a with a radial end adjacent to the second cavity 26a.
  • a second passage 48 communicates the other radial end of the second cavity 26a with a radial end adjacent to the third cavity 28a.
  • Outlets 50a open in the third cavity 28a and open on the underside face 20 of the blade.
  • the circulation of the cooling air which runs through this intrados circuit follows clearly from the foregoing.
  • the circuit is supplied with cooling air through the inlet opening 44.
  • the air then travels through the first 24a, second 26a and third cavities 28a before being emitted on the underside 20 of the blade by the orifices of exit 50a.
  • the inner walls of the cavities 24a, 26a, 28a, 30a, 32a and 34a of the lower and upper suction cooling circuits may advantageously be equipped with flow disruptors 52 intended to increase heat transfer along these walls. .
  • These flow disruptors may be in the form of ribs which are straight or inclined relative to the axis of rotation of the blade or in the form of pins (or any other equivalent forms).
  • the figure 5 represents an alternative embodiment of the cooling circuits intrados and extrados of the blade.
  • the extrados cooling circuit of the blade 10b comprises a first cavity 34b occupying the extrados zone Z8, a second cavity 36b occupying the extrados zones Z6 and Z7 and a third cavity 38b occupying the extrados zone Z5 and the intrados zone Z1.
  • the extrados circuit is distinguished in particular in that the third cavity 38b is disposed on the side of the leading edge 16 of the blade (and not the side of the trailing edge thereof).
  • An unrepresented air inlet opening is provided at a radial end (at the root of blade) of the first cavity 34b and passages (not shown) allow communication between the different cavities 34b, 36b and 38b according to a realization similar to that of the extrados circuit of Figures 2 to 4 .
  • Outlets 42b open in the third cavity 38b and open on the underside face 20 of the blade. The direction of air circulation in this extrados circuit is therefore reversed with respect to that of the embodiment of the Figures 2 to 4 .
  • the inner cooling circuit of the blade 10b comprises a first cavity 24b occupying the intrados zone Z2, a second cavity 26b occupying the intrados zone Z3 and a third cavity 28b occupying the intrados zone Z4.
  • an inlet opening (not shown) is provided at a radial end (at the root of blade) of the first cavity 24b and passages (not shown) allow communication between the different cavities 24b, 26b and 28b according to an embodiment similar to that of the intrados Figures 2 to 4 .
  • Outlets 50b open in the third cavity 28b and open on the underside face 20 of the blade. The direction of air circulation in this intrados circuit is therefore reversed with respect to that of the embodiment of the Figures 2 to 4 .
  • the figure 6 represents another alternative embodiment of the cooling circuits intrados and extrados of the blade.
  • the extrados cooling circuit of the blade 10c comprises a first cavity 34c occupying the extrados zones Z7 and Z8, a second cavity 36c occupying the extrados zones Z5 and Z6 and a third cavity 38c occupying the intrados zone Z1.
  • the third cavity 38c of the extrados cooling circuit is thus disposed on the side of the leading edge 16 of the blade.
  • cooling air is admitted into the first cavity 34c via an air inlet opening (not shown) and passages (not shown) allow communication between the different cavities 34c, 36c and 38c.
  • Outlets 42c open in the third cavity 38c and open on the underside face 20 of the blade.
  • the figure 7 represents yet another alternative embodiment of the cooling circuits intrados and extrados of the blade.
  • the extrados cooling circuit of the blade 10c comprises a first cavity 34d occupying the extrados zones Z5 and Z6, a second cavity 36d occupying the extrados zones Z7 and Z8 and a third cavity 38d occupying the intrados zone Z4.
  • the third cavity 38d of this extrados circuit is disposed on the trailing edge 18 side of the blade (rather than the leading edge side).
  • the cooling air is admitted into the first cavity 34d through an air inlet opening (not shown) and passages (not shown) allow communication between the various cavities 34d, 36d and 38d according to a realization similar to that of the extrados circuit of Figures 2 to 4 .
  • Outlets 42d open in the third cavity 38d and open on the underside face 20 of the blade. The direction of air flow in this extrados circuit is therefore reversed with respect to that of the embodiment of the figure 6 .
  • the intrados cooling circuit it is identical in its implementation to that described in connection with the Figures 2 to 4 .
  • the downward and upward cooling circuits each have their own air intake opening and that there is no air communication from one circuit to the other so that these circuits are completely independent of each other.
  • the leading edge cooling circuit of the blade comprises a first radial cavity 54 extending in the vicinity of the leading edge 16 of the blade and a second radial cavity 56 extending from the intrados face 20 to the extrados face 22 of the blade, this second cavity 56 being disposed between the first cavity 54 and the central portion C of the blade.
  • At least one air intake port 58 opens into the second cavity 56 to supply air to the leading edge circuit.
  • a plurality of communication holes 60 distributed over the entire radial height of the blade open into the second cavity 56 and open into the first cavity 54.
  • outlet orifices 62 opening into the first cavity 54 open onto the leading edge 16 and on the intrados 20 and extrados 22 faces of the blade.
  • the cooling circuit of the trailing edge of the blade comprises a first radial cavity 64 extending in the vicinity of the trailing edge 18 of the blade and a second radial cavity 66 extending from the underside face 20 to at the extrados face 22 of the blade, this second cavity 66 being disposed between the first cavity 64 and the central portion C of the blade.
  • At least one air intake port 68 opens into the second cavity 66 to supply air to the trailing edge circuit.
  • a plurality of communication holes 70 distributed over the entire radial height of the blade open into the second cavity 66 and open into the first cavity 64.
  • outlet orifices 72 open into the first cavity 64 and open on the underside 20 of the dawn, at the trailing edge 18.

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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 mobiles de turbomachine, et notamment aux aubes de la turbine haute-pression.The present invention relates to the general field of cooling turbomachine moving blades, and in particular to the blades of the high-pressure turbine.

Il est connu de munir les aubes mobiles d'une turbine à gaz de turbomachine, telles que les turbines haute et basse pression, de circuits internes de refroidissement leur permettant de supporter sans dommages les températures très élevées auxquelles elles sont soumises pendant le fonctionnement de la turbomachine. Ainsi, dans le cas d'une turbine haute-pression, les températures des gaz issus de la chambre de combustion atteignent des valeurs largement supérieures à celles que peuvent supporter sans dommages les aubes mobiles de la turbine, ce qui a pour conséquence de limiter leur durée de vie.It is known to provide the blades of a turbomachine gas turbine, such as high and low pressure turbines, internal cooling circuits allowing them to withstand without damage the very high temperatures to which they are subjected during operation of the turbine engine. Thus, in the case of a high-pressure turbine, the temperatures of the gases from the combustion chamber reach values much higher than those which can withstand without damage the blades of the turbine, which has the consequence of limiting their lifetime.

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.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, ce qui présente l'inconvénient de limiter l'efficacité thermique du refroidissement. Dans le but de pallier ce défaut, d'autres circuits, tels que ceux décrits dans les documents EP 1 288 438 et EP 1 288 439 , 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. Bien que de tels circuits soient efficaces d'un point de vue thermique, ils restent difficiles et coûteux à réaliser par moulage et le poids de l'aube obtenue est important.There are many different achievements of these cooling circuits. Thus, some circuits use cooling cavities that occupy the entire width of the blade, which has the disadvantage of limiting the thermal efficiency of cooling. In order to overcome this defect, other circuits, such as those described in the documents EP 1 288 438 and EP 1 288 439 , 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. Although such circuits are thermally efficient, they are difficult and expensive to make by molding and the weight of the blade obtained is important.

EP-A-1 584 790 décrit une aube selon le préambule de la revendication 1. EP-A-1,584,790 discloses a blade according to the preamble of claim 1.

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 un circuit de refroidissement central d'une aube mobile permettant d'obtenir un refroidissement efficace de l'aube à un faible coût de fabrication.The main object of the present invention is thus to overcome such disadvantages by proposing a central cooling circuit of a mobile blade for efficient cooling of the blade at a low manufacturing cost.

A cet effet, il est prévu une aube mobile de turbomachine selon la revendication 1.For this purpose, a turbomachine moving blade is provided according to claim 1.

Les circuits de refroidissement intrados et extrados ainsi définis présentent une dissymétrie de configuration entre l'intrados et l'extrados et sont propres à chaque paroi (intrados, extrados) de l'aube. Ainsi, il est possible de prendre en compte les niveaux d'échange thermique qui sont plus faibles à l'intrados qu'à l'extrados de l'aube. Il est également possible de tenir compte de l'effet de la force de Coriolis qui a tendance à « plaquer » l'air vers l'une des parois de l'aube selon que l'écoulement soit centripète ou centrifuge. De la sorte, il est possible d'obtenir une aube dont la masse, la température moyenne et la durée de vie sont optimisées pour un faible coût de fabrication.The intrados and extrados cooling circuits thus defined present an asymmetry of configuration between the intrados and the extrados and are specific to each wall (intrados, extrados) of the dawn. Thus, it is possible to take into account the levels of heat exchange which are lower on the intrados than on the upper surface of the dawn. It is also possible to take into account the effect of the Coriolis force which tends to "press" the air towards one of the walls of the dawn according to whether the flow is centripetal or centrifugal. In this way, it is possible to obtain a blade whose mass, average temperature and service life are optimized for a low manufacturing cost.

Selon un mode de réalisation de l'invention, le circuit de refroidissement extrados peut comporter une première cavité et une deuxième cavité s'étendant du côté extrados de l'aube, une troisième cavité s'étendant depuis l'intrados jusqu'à l'extrados de l'aube, une ouverture d'admission d'air à une extrémité radiale de la première cavité, un premier passage faisant communiquer l'autre extrémité radiale de la première cavité avec une extrémité radiale voisine de la deuxième cavité, un second passage faisant communiquer l'autre extrémité radiale de la deuxième cavité avec une extrémité radiale voisine de la troisième cavité, et des orifices de sortie s'ouvrant dans la troisième cavité et débouchant sur la face intrados de l'aube.According to one embodiment of the invention, the extrados cooling circuit may comprise a first cavity and a second cavity extending on the extrados side of the blade, a third cavity extending from the intrados to the extrados of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other radial end of the second cavity with a radial end adjacent to the third cavity, and outlet orifices opening in the third cavity and opening on the intrados face of the blade.

La troisième cavité d'un tel circuit de refroidissement extrados peut être disposée du côté du bord d'attaque ou bord de fuite de l'aube.The third cavity of such an extrados cooling circuit can be arranged on the side of the leading edge or trailing edge of the blade.

Selon un autre mode de réalisation de l'invention, le circuit de refroidissement extrados peut comporter une première cavité et une deuxième cavité s'étendant du côté extrados de l'aube, une troisième cavité s'étendant du côté intrados de l'aube, une ouverture d'admission d'air à une extrémité radiale de la première cavité, un premier passage faisant communiquer l'autre extrémité radiale de la première cavité avec une extrémité radiale voisine de la deuxième cavité, un second passage faisant communiquer l'autre extrémité radiale de la deuxième cavité avec une extrémité radiale voisine de la troisième cavité, et des orifices de sortie s'ouvrant dans la troisième cavité et débouchant sur la face intrados de l'aube.According to another embodiment of the invention, the extrados cooling circuit may comprise a first cavity and a second cavity extending on the extrados side of the blade, a third cavity extending on the intrados side of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other end; radial of the second cavity with a radial end adjacent to the third cavity, and outlet orifices opening in the third cavity and opening on the intrados face of the blade.

La troisième cavité d'un tel circuit de refroidissement extrados peut être disposée du côté du bord d'attaque ou du bord de fuite de l'aube.The third cavity of such an extrados cooling circuit can be disposed on the leading edge side or the trailing edge of the blade.

Selon une disposition particulière de l'invention, le circuit de refroidissement intrados peut comporter une première, une deuxième et une troisième cavités s'étendant du côté intrados de l'aube, une ouverture d'admission d'air à une extrémité radiale de la première cavité, un premier passage faisant communiquer l'autre extrémité radiale de la première cavité avec une extrémité radiale voisine de la deuxième cavité, un second passage faisant communiquer l'autre extrémité radiale de la deuxième cavité avec une extrémité radiale voisine de la troisième cavité, et des orifices de sortie s'ouvrant dans la troisième cavité et débouchant sur la face intrados de l'aube.According to a particular embodiment of the invention, the intrados cooling circuit may comprise a first, a second and a third cavity extending on the intrados side of the blade, an air inlet opening at a radial end of the first cavity, a first passage communicating the other radial end of the first cavity with a radial end adjacent to the second cavity, a second passage communicating the other radial end of the second cavity with a radial end adjacent to the third cavity; , and outlets opening in the third cavity and opening on the intrados face of the blade.

L'aube peut également comporter un circuit de refroidissement du bord d'attaque de l'aube et un circuit de refroidissement du bord de fuite de l'aube.The blade may also comprise a cooling circuit of the leading edge of the blade and a cooling circuit of the trailing edge of the blade.

L'invention a aussi pour objet une turbine à gaz comportant au moins une aube mobile telle que définie précédemment.The invention also relates to a gas turbine comprising at least one moving blade as defined above.

L'invention a encore pour objet une turbomachine comportant au moins une aube mobile telle que définie précédemment.The invention also relates to a turbomachine comprising at least one moving blade 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 transversale d'une aube mobile de turbomachine montrant les différentes zones géométriques dans la partie centrale de celle-ci ;
  • la figure 2 est une vue en coupe transversale d'une aube mobile selon un mode de réalisation de l'invention ;
  • les figures 3 et 4 sont des vues en coupe de la figure 2 respectivement selon III-III et IV-IV ; et
  • les figures 5 à 7 sont des vues en coupe transversale d'aubes mobiles selon d'autres modes de réalisation de l'invention.
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:
  • the figure 1 is a cross-sectional view of a moving turbine engine blade showing the different geometrical zones in the central part thereof;
  • the figure 2 is a cross-sectional view of a blade according to one embodiment of the invention;
  • the figures 3 and 4 are sectional views of the figure 2 respectively according to III-III and IV-IV; and
  • the Figures 5 to 7 are cross-sectional views of blades according to other embodiments of the invention.

Description détaillée de modes de réalisationDetailed description of embodiments

La figure 1 représente une aube mobile 10 de turbomachine, telle qu'une aube mobile de turbine haute-pression. Bien entendu, l'invention peut également s'appliquer à d'autres aubes mobiles de la turbomachine, par exemple aux aubes de la turbine basse-pression de celle-ci.The figure 1 represents a moving blade 10 of a turbomachine, such as a moving blade of a high-pressure turbine. Of course, the invention can also be applied to other blades of the turbomachine, for example to the blades of the low-pressure turbine thereof.

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 (figures 3 et 4). 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 has an aerodynamic surface (or blade) which extends radially between a blade root 12 and a blade tip 14 ( figures 3 and 4 ). This aerodynamic surface consists of a leading edge 16 disposed opposite the flow of hot gases from the combustion chamber of the turbomachine, a trailing edge 18 opposite to the leading edge 16, of 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 comporte une partie centrale C qui occupe la zone géométrique de l'aube pour laquelle la distance entre ses faces intrados 20 et extrados 22 est la plus importante.The blade 10 has a central portion C which occupies the geometric zone of the blade for which the distance between its intrados 20 and extrados faces 22 is the largest.

Comme représenté sur la figure 1, la partie centrale C de l'aube est divisée géométriquement en quatre zones intrados adjacentes Z1 à Z4 disposées du côté intrados de l'aube et en quatre zones extrados adjacentes Z5 à Z8 disposées du côté extrados, les zones intrados et extrados étant réparties de part et d'autre du squelette S de l'aube.As shown on the figure 1 , the central part C of the blade is divided geometrically into four adjacent intrados zones Z1 to Z4 disposed on the intrados side of the blade and in four adjacent extrados zones Z5 to Z8 disposed on the extrados side, the intrados and extrados zones being distributed from on both sides of the skeleton S of dawn.

Par squelette de l'aube, on entend la ligne géométrique S des points situés à égale distance des faces latérales intrados 20 et extrados 22 de l'aube.Skeleton of the dawn means the geometric line S points equidistant from the side faces intrados 20 and extrados 22 of the blade.

Plus précisément, le squelette S de l'aube définit deux zones principales de la partie centrale C de l'aube qui sont chacune divisées en quatre zones adjacentes par trois lignes géométriques L1 à L3 découpant radialement l'aube dans le sens de son épaisseur.Specifically, the skeleton S of the blade defines two main areas of the central portion C of the blade which are each divided into four adjacent zones by three geometric lines L1 to L3 radially cutting the blade in the direction of its thickness.

Les zones géométriques intrados Z1 à Z4 et extrados Z5 à Z8 ainsi définies constituent les plus petits éléments pouvant contenir une cavité de refroidissement. Pour une aube classique de turbine haute-pression, ces zones s'étendent en coupe transversale sur une surface comprise typiquement entre 3 et 10 mm2 environ.The intrados geometrical zones Z1 to Z4 and extrados Z5 to Z8 thus defined constitute the smallest elements that can contain a cooling cavity. For a typical high-pressure turbine blade, these zones extend in cross-section on a surface typically comprised between 3 and 10 mm 2 approximately.

Selon l'invention, la partie centrale C de l'aube est munie d'un circuit de refroidissement intrados et d'un circuit de refroidissement extrados, le circuit de refroidissement intrados comprenant trois cavités radiales occupant trois zones intrados adjacentes, et le circuit de refroidissement extrados comprenant trois cavités radiales occupant les quatre zones extrados et la zone intrados restante.According to the invention, the central portion C of the blade is provided with a lower pressure cooling circuit and an extrados cooling circuit, the intrados cooling circuit comprising three radial cavities occupying three adjacent intrados zones, and the cooling circuit extrados cooling comprising three radial cavities occupying the four extrados areas and the remaining intrados area.

Par cavité radiale, on entend pour la suite de la description, une cavité s'étendant radialement entre le pied 12 et le sommet 14 de l'aube.By radial cavity is meant for the rest of the description, a cavity extending radially between the foot 12 and the top 14 of the blade.

Différents modes de réalisation des circuits de refroidissement intrados et extrados de l'aube sont envisageables.Different embodiments of the intrados and extrados cooling circuits of the blade are possible.

Dans le mode de réalisation de l'invention représenté par les figures 2 à 4, le circuit de refroidissement intrados de l'aube 10a comprend trois cavités radiales 24a, 26a et 28a occupant respectivement les trois zones intrados adjacentes Z3, Z2 et Z1 de la figure 1.In the embodiment of the invention represented by the Figures 2 to 4 , the inner cooling circuit of the blade 10a comprises three radial cavities 24a, 26a and 28a respectively occupying the three adjacent intrados zones Z3, Z2 and Z1 of the figure 1 .

Quant au circuit de refroidissement extrados de l'aube, il comprend trois cavités radiales extrados 30a, 32a et 34a occupant les quatre zones extrados Z5 à Z8 et la zone intrados restante Z4.As for the extrados cooling circuit of the blade, it comprises three extrados radial cavities 30a, 32a and 34a occupying the four extrados zones Z5 to Z8 and the remaining intrados zone Z4.

Plus précisément, le circuit extrados de l'aube comporte une première cavité 30a s'étendant du côté extrados de l'aube et occupant la zone extrados Z5, une deuxième cavité 32a s'étendant du côté extrados de l'aube et occupant les zones extrados Z6 et Z7, et une troisième cavité 34a s'étendant depuis la face intrados 20 jusqu'à la face extrados 22 de l'aube et occupant la zone extrados Z8 et la zone intrados Z4.More specifically, the upper surface of the blade has a first cavity 30a extending on the upper surface of the blade and occupying the extrados zone Z5, a second cavity 32a extending on the upper surface of the blade and occupying the zones. extrados Z6 and Z7, and a third cavity 34a extending from the intrados face 20 to the extrados face 22 of the blade and occupying the extrados zone Z8 and the intrados zone Z4.

Par cavité s'étendant du côté extrados de l'aube, on entend une cavité qui s'étend dans le sens de l'épaisseur de l'aube depuis la face extrados 22 de l'aube jusqu'à son squelette S.By cavity extending on the upper surface of the blade is meant a cavity which extends in the direction of the thickness of the blade from the extrados face 22 of the blade to its skeleton S.

Les cavités 30a à 34a du circuit de refroidissement extrados sont des cavités ayant des sections transversales supérieures à 4 mm2 environ.The cavities 30a to 34a of the extrados cooling circuit are cavities having cross sections greater than about 4 mm 2 .

Par ailleurs, la troisième cavité 34a de ce circuit extrados qui s'étend depuis la face intrados 20 jusqu'à la face extrados 22 de l'aube est disposée du côté du bord de fuite 18 de l'aube.Furthermore, the third cavity 34a of this extrados circuit which extends from the intrados face 20 to the extrados face 22 of the blade is disposed on the side of the trailing edge 18 of the blade.

En liaison avec la figure 3, le circuit de refroidissement extrados comporte également une ouverture d'admission d'air 36 à une extrémité radiale de la première cavité 30a (ici au niveau du pied 12 de l'aube) afin d'alimenter en air le circuit extrados.In connection with the figure 3 , the extrados cooling circuit also comprises an air inlet opening 36 at a radial end of the first cavity 30a (here at the foot 12 of the blade) to supply air to the extrados circuit.

Un premier passage 38 fait communiquer l'autre extrémité radiale de la première cavité 30a (c'est-à-dire au niveau du sommet 14 de l'aube) avec une extrémité radiale voisine de la deuxième cavité 32a. De même, un second passage 40 fait communiquer l'autre extrémité radiale de la deuxième cavité 32a avec une extrémité radiale voisine de la troisième cavité 34a.A first passage 38 communicates the other radial end of the first cavity 30a (that is to say at the top 14 of the blade) with a radial end adjacent to the second cavity 32a. Similarly, a second passage 40 communicates the other radial end of the second cavity 32a with a radial end adjacent to the third cavity 34a.

En outre, des orifices de sortie 42a s'ouvrent dans la troisième cavité 34a et débouchent sur la face intrados 20 de l'aube. Ces orifices de sortie 42a sont régulièrement répartis sur toute la hauteur radiale de l'aube.In addition, outlet orifices 42a open into the third cavity 34a and open on the underside face 20 of the blade. These outlet orifices 42a are regularly distributed over the entire radial height of the blade.

La circulation de l'air de refroidissement qui parcourt ce circuit extrados découle de manière évidente de ce qui précède. Le circuit est alimenté en air de refroidissement par l'ouverture d'admission 36. L'air parcourt d'abord la première cavité 30a (selon un écoulement centrifuge) puis la seconde cavité extrados 32a (selon un écoulement centripète) et enfin la cavité centrale 34a (selon un écoulement centrifuge) avant d'être émis à l'intrados 20 de l'aube par les orifices de sortie 42a.The circulation of the cooling air which runs through this extrados circuit derives evidently from the foregoing. The circuit is supplied with cooling air through the inlet opening 36. The air first passes through the first cavity 30a (according to a centrifugal flow) and then the second extrados cavity 32a (according to a centripetal flow) and finally the cavity central 34a (according to a centrifugal flow) before being emitted at the underside 20 of the blade through the outlet orifices 42a.

Le circuit de refroidissement intrados de l'aube comporte une première cavité 24a occupant la zone intrados Z3, une deuxième cavité 26a occupant la zone intrados Z2 et une troisième cavité 28a occupant la zone intrados Z1.The cooling circuit intrados dawn comprises a first cavity 24a occupying the intrados zone Z3, a second cavity 26a occupying the intrados zone Z2 and a third cavity 28a occupying the intrados zone Z1.

Ces cavités 24a à 28a s'étendent du côté intrados de l'aube, c'est-à-dire qu'elles s'étendent dans le sens de l'épaisseur de l'aube depuis la face intrados 20 de l'aube jusqu'à son squelette S.These cavities 24a to 28a extend on the intrados side of the blade, that is to say they extend in the direction of the thickness of the blade from the intrados face 20 of the blade until 'to his skeleton S.

Par ailleurs, ces cavités 24a à 28a sont des cavités ayant des sections transversales inférieures à 15 mm2 environ.Moreover, these cavities 24a to 28a are cavities having cross sections less than about 15 mm 2 .

Comme représenté sur la figure 4, le circuit de refroidissement intrados comporte également une ouverture d'admission d'air 44 à une extrémité radiale de la première cavité 24a (ici au niveau du pied 12 de l'aube) pour alimenter en air le circuit intrados.As shown on the figure 4 , the intrados cooling circuit also comprises an air inlet opening 44 at a radial end of the first cavity 24a (here at the foot 12 of the blade) for supplying air to the intrados circuit.

Un premier passage 46 fait communiquer l'autre extrémité radiale (au niveau du sommet 14 de l'aube) de la première cavité 24a avec une extrémité radiale voisine de la deuxième cavité 26a. De même, un second passage 48 fait communiquer l'autre extrémité radiale de la deuxième cavité 26a avec une extrémité radiale voisine de la troisième cavité 28a. Des orifices de sortie 50a s'ouvrent dans la troisième cavité 28a et débouchent sur la face intrados 20 de l'aube.A first passage 46 communicates the other radial end (at the top 14 of the blade) of the first cavity 24a with a radial end adjacent to the second cavity 26a. Similarly, a second passage 48 communicates the other radial end of the second cavity 26a with a radial end adjacent to the third cavity 28a. Outlets 50a open in the third cavity 28a and open on the underside face 20 of the blade.

La circulation de l'air de refroidissement qui parcourt ce circuit intrados découle de manière évidente de ce qui précède. Le circuit est alimenté en air de refroidissement par l'ouverture d'admission 44. L'air parcourt ensuite les première 24a, deuxième 26a et troisième cavités 28a avant d'être émis à l'intrados 20 de l'aube par les orifices de sortie 50a.The circulation of the cooling air which runs through this intrados circuit follows clearly from the foregoing. The circuit is supplied with cooling air through the inlet opening 44. The air then travels through the first 24a, second 26a and third cavities 28a before being emitted on the underside 20 of the blade by the orifices of exit 50a.

De façon connue en soi, les parois internes des cavités 24a, 26a, 28a, 30a, 32a et 34a des circuits de refroidissement intrados et extrados peuvent être avantageusement munies de perturbateurs d'écoulement 52 destinés à accroître les transferts thermiques le long de ces parois.In a manner known per se, the inner walls of the cavities 24a, 26a, 28a, 30a, 32a and 34a of the lower and upper suction cooling circuits may advantageously be equipped with flow disruptors 52 intended to increase heat transfer along these walls. .

Ces perturbateurs d'écoulement peuvent se présenter sous la forme de nervures qui sont droites ou inclinées par rapport à l'axe de rotation de l'aube ou sous la forme de picots (ou toutes autres formes équivalentes).These flow disruptors may be in the form of ribs which are straight or inclined relative to the axis of rotation of the blade or in the form of pins (or any other equivalent forms).

La figure 5 représente une variante de réalisation de réalisation des circuits de refroidissement intrados et extrados de l'aube.The figure 5 represents an alternative embodiment of the cooling circuits intrados and extrados of the blade.

Le circuit de refroidissement extrados de l'aube 10b selon ce mode de réalisation comporte une première cavité 34b occupant la zone extrados Z8, une deuxième cavité 36b occupant les zones extrados Z6 et Z7 et une troisième cavité 38b occupant la zone extrados Z5 et la zone intrados Z1.The extrados cooling circuit of the blade 10b according to this embodiment comprises a first cavity 34b occupying the extrados zone Z8, a second cavity 36b occupying the extrados zones Z6 and Z7 and a third cavity 38b occupying the extrados zone Z5 and the intrados zone Z1.

En d'autres termes, par rapport au mode de réalisation des figures 2 à 4, le circuit extrados se distingue notamment en ce que la troisième cavité 38b est disposée du côté du bord d'attaque 16 de l'aube (et non du côté du bord de fuite de celle-ci).In other words, compared to the embodiment of the Figures 2 to 4 , the extrados circuit is distinguished in particular in that the third cavity 38b is disposed on the side of the leading edge 16 of the blade (and not the side of the trailing edge thereof).

Une ouverture d'admission d'air non représentée est prévue à une extrémité radiale (au niveau du pied d'aube) de la première cavité 34b et des passages (non représentés) permettent une communication entre les différentes cavités 34b, 36b et 38b selon une réalisation similaire à celle du circuit extrados des figures 2 à 4. Des orifices de sortie 42b s'ouvrent dans la troisième cavité 38b et débouchent sur la face intrados 20 de l'aube. Le sens de circulation de l'air dans ce circuit extrados est donc inversé par rapport à celui du mode de réalisation des figures 2 à 4.An unrepresented air inlet opening is provided at a radial end (at the root of blade) of the first cavity 34b and passages (not shown) allow communication between the different cavities 34b, 36b and 38b according to a realization similar to that of the extrados circuit of Figures 2 to 4 . Outlets 42b open in the third cavity 38b and open on the underside face 20 of the blade. The direction of air circulation in this extrados circuit is therefore reversed with respect to that of the embodiment of the Figures 2 to 4 .

Le circuit de refroidissement intrados de l'aube 10b selon ce mode de réalisation comporte une première cavité 24b occupant la zone intrados Z2, une deuxième cavité 26b occupant la zone intrados Z3 et une troisième cavité 28b occupant la zone intrados Z4.The inner cooling circuit of the blade 10b according to this embodiment comprises a first cavity 24b occupying the intrados zone Z2, a second cavity 26b occupying the intrados zone Z3 and a third cavity 28b occupying the intrados zone Z4.

De même que pour le mode de réalisation précédent, une ouverture d'admission (non représentée) est prévue à une extrémité radiale (au niveau du pied d'aube) de la première cavité 24b et des passages (non représentés) permettent une communication entre les différentes cavités 24b, 26b et 28b selon une réalisation similaire à celle du circuit intrados des figures 2 à 4. Des orifices de sortie 50b s'ouvrent dans la troisième cavité 28b et débouchent sur la face intrados 20 de l'aube. Le sens de circulation de l'air dans ce circuit intrados est donc inversé par rapport à celui du mode de réalisation des figures 2 à 4.As for the previous embodiment, an inlet opening (not shown) is provided at a radial end (at the root of blade) of the first cavity 24b and passages (not shown) allow communication between the different cavities 24b, 26b and 28b according to an embodiment similar to that of the intrados Figures 2 to 4 . Outlets 50b open in the third cavity 28b and open on the underside face 20 of the blade. The direction of air circulation in this intrados circuit is therefore reversed with respect to that of the embodiment of the Figures 2 to 4 .

La figure 6 représente une autre variante de réalisation de réalisation des circuits de refroidissement intrados et extrados de l'aube.The figure 6 represents another alternative embodiment of the cooling circuits intrados and extrados of the blade.

Le circuit de refroidissement extrados de l'aube 10c selon ce mode de réalisation comporte une première cavité 34c occupant les zones extrados Z7 et Z8, une deuxième cavité 36c occupant les zones extrados Z5 et Z6 et une troisième cavité 38c occupant la zone intrados Z1. La troisième cavité 38c du circuit de refroidissement extrados est donc disposée du côté du bord d'attaque 16 de l'aube.The extrados cooling circuit of the blade 10c according to this embodiment comprises a first cavity 34c occupying the extrados zones Z7 and Z8, a second cavity 36c occupying the extrados zones Z5 and Z6 and a third cavity 38c occupying the intrados zone Z1. The third cavity 38c of the extrados cooling circuit is thus disposed on the side of the leading edge 16 of the blade.

Selon une réalisation similaire à celle du circuit extrados des figures 2 à 4, de l'air de refroidissement est admis dans la première cavité 34c par l'intermédiaire d'une ouverture d'admission d'air (non représentée) et des passages (non représentés) permettent une communication entre les différentes cavités 34c, 36c et 38c. Des orifices de sortie 42c s'ouvrent dans la troisième cavité 38c et débouchent sur la face intrados 20 de l'aube.According to an embodiment similar to that of the extrados Figures 2 to 4 , cooling air is admitted into the first cavity 34c via an air inlet opening (not shown) and passages (not shown) allow communication between the different cavities 34c, 36c and 38c. Outlets 42c open in the third cavity 38c and open on the underside face 20 of the blade.

Quant au circuit de refroidissement intrados, il est identique dans sa réalisation à celui décrit en liaison avec la figure 5.As for the intrados cooling circuit, it is identical in its realization to that described in connection with the figure 5 .

La figure 7 représente encore une autre variante de réalisation de réalisation des circuits de refroidissement intrados et extrados de l'aube.The figure 7 represents yet another alternative embodiment of the cooling circuits intrados and extrados of the blade.

Le circuit de refroidissement extrados de l'aube 10c selon ce mode de réalisation comporte une première cavité 34d occupant les zones extrados Z5 et Z6, une deuxième cavité 36d occupant les zones extrados Z7 et Z8 et une troisième cavité 38d occupant la zone intrados Z4.The extrados cooling circuit of the blade 10c according to this embodiment comprises a first cavity 34d occupying the extrados zones Z5 and Z6, a second cavity 36d occupying the extrados zones Z7 and Z8 and a third cavity 38d occupying the intrados zone Z4.

Par rapport au mode de réalisation du circuit de refroidissement extrados de la figure 6, la troisième cavité 38d de ce circuit extrados est disposée du côté du bord de fuite 18 de l'aube (plutôt que du côté du bord d'attaque).Compared to the embodiment of the extrados cooling circuit of the figure 6 , the third cavity 38d of this extrados circuit is disposed on the trailing edge 18 side of the blade (rather than the leading edge side).

L'air de refroidissement est admis dans la première cavité 34d par l'intermédiaire d'une ouverture d'admission d'air (non représentée) et des passages (non représentés) permettent une communication entre les différentes cavités 34d, 36d et 38d selon une réalisation similaire à celle du circuit extrados des figures 2 à 4. Des orifices de sortie 42d s'ouvrent dans la troisième cavité 38d et débouchent sur la face intrados 20 de l'aube. Le sens de circulation de l'air dans ce circuit extrados est donc inversé par rapport à celui du mode de réalisation de la figure 6.The cooling air is admitted into the first cavity 34d through an air inlet opening (not shown) and passages (not shown) allow communication between the various cavities 34d, 36d and 38d according to a realization similar to that of the extrados circuit of Figures 2 to 4 . Outlets 42d open in the third cavity 38d and open on the underside face 20 of the blade. The direction of air flow in this extrados circuit is therefore reversed with respect to that of the embodiment of the figure 6 .

Quant au circuit de refroidissement intrados, il est identique dans sa réalisation à celui décrit en liaison avec les figures 2 à 4.As for the intrados cooling circuit, it is identical in its implementation to that described in connection with the Figures 2 to 4 .

Quelque soit le mode de réalisation, on notera que les circuits de refroidissement intrados et extrados présentent chacun leur propre ouverture d'admission d'air et qu'il n'existe aucune communication d'air d'un circuit vers l'autre de sorte que ces circuits sont complètement indépendants l'un de l'autre.Whatever the embodiment, it will be noted that the downward and upward cooling circuits each have their own air intake opening and that there is no air communication from one circuit to the other so that these circuits are completely independent of each other.

En liaison avec les figures 2 à 4, on décrira maintenant brièvement un mode de réalisation de circuits de refroidissement supplémentaires destinés à refroidir le bord d'attaque 16 et le bord de fuite 18 de l'aube.In liaison with Figures 2 to 4 Briefly, an embodiment of additional cooling circuits for cooling the leading edge 16 and the trailing edge 18 of the blade will now be briefly described.

Le circuit de refroidissement bord d'attaque de l'aube comprend une première cavité radiale 54 s'étendant au voisinage du bord d'attaque 16 de l'aube et une deuxième cavité radiale 56 s'étendant depuis la face intrados 20 jusqu'à la face extrados 22 de l'aube, cette deuxième cavité 56 étant disposée entre la première cavité 54 et la partie centrale C de l'aube.The leading edge cooling circuit of the blade comprises a first radial cavity 54 extending in the vicinity of the leading edge 16 of the blade and a second radial cavity 56 extending from the intrados face 20 to the extrados face 22 of the blade, this second cavity 56 being disposed between the first cavity 54 and the central portion C of the blade.

Au moins un orifice d'admission d'air 58 débouche dans la deuxième cavité 56 afin d'alimenter en air le circuit bord d'attaque. Une pluralité de trous de communication 60 répartis sur toute la hauteur radiale de l'aube s'ouvrent dans la deuxième cavité 56 et débouchent dans la première cavité 54. Enfin, des orifices de sortie 62 s'ouvrant dans la première cavité 54 débouchent sur le bord d'attaque 16 et sur les faces intrados 20 et extrados 22 de l'aube.At least one air intake port 58 opens into the second cavity 56 to supply air to the leading edge circuit. A plurality of communication holes 60 distributed over the entire radial height of the blade open into the second cavity 56 and open into the first cavity 54. Finally, outlet orifices 62 opening into the first cavity 54 open onto the leading edge 16 and on the intrados 20 and extrados 22 faces of the blade.

Quant au circuit de refroidissement bord de fuite de l'aube, il comprend une première cavité radiale 64 s'étendant au voisinage du bord de fuite 18 de l'aube et une deuxième cavité radiale 66 s'étendant depuis la face intrados 20 jusqu'à la face extrados 22 de l'aube, cette deuxième cavité 66 étant disposée entre la première cavité 64 et la partie centrale C de l'aube.As for the cooling circuit of the trailing edge of the blade, it comprises a first radial cavity 64 extending in the vicinity of the trailing edge 18 of the blade and a second radial cavity 66 extending from the underside face 20 to at the extrados face 22 of the blade, this second cavity 66 being disposed between the first cavity 64 and the central portion C of the blade.

Au moins un orifice d'admission d'air 68 débouche dans la deuxième cavité 66 pour alimenter en air le circuit bord de fuite. Une pluralité de trous de communication 70 répartis sur toute la hauteur radiale de l'aube s'ouvrent dans la deuxième cavité 66 et débouchent dans la première cavité 64. En outre, des orifices de sortie 72 s'ouvrent dans la première cavité 64 et débouchent sur la face intrados 20 de l'aube, au niveau du bord de fuite 18.At least one air intake port 68 opens into the second cavity 66 to supply air to the trailing edge circuit. A plurality of communication holes 70 distributed over the entire radial height of the blade open into the second cavity 66 and open into the first cavity 64. In addition, outlet orifices 72 open into the first cavity 64 and open on the underside 20 of the dawn, at the trailing edge 18.

Claims (12)

  1. A moving blade (10a, 10b, 10c, 10d) for a turbomachine, the central portion (C) of the blade being geometrically subdivided into four adjacent pressure-side zones (Z1 to Z4) disposed on the pressure side of the blade, and into four adjacent suction-side zones (Z5 to Z8) disposed on the suction side, the pressure-side and suction-side zones being distributed on opposite sides of the skeleton (S) of the blade, each pressure-side zone having a common side with a suction-side zone and each suction-side zone having a common side with a pressure-side zone, the pressure-side zones (Z1 to Z4) and suction-side zones (Z5 to Z8) forming the smallest elements that can contain a cooling cavity, the blade including in its central portion (C) both a pressure-side cooling circuit and a suction-side cooling circuit that are independent from each other, characterized in that the pressure-side cooling circuit comprises three radial cavities (24a to 28a ; 24b to 26b) occupying three adjacent pressure-side zones, and in that the suction-side cooling circuit consists in three radial cavities (30a to 34a ; 34b to 38b ; 34c to 38c ; 34d to 38d) occupying the four suction-side zones and the remaining pressure-side zone.
  2. A blade according to claim 1, in which the suction- side cooling circuit comprises:
    • a first cavity (30a ; 34b) and a second cavity (32a ; 36b) extending on the suction side of the blade;
    • a third cavity (34a ; 38b) extending from the pressure side to the suction side of the blade;
    • an air admission opening (36) at one radial end of the first cavity (30a ; 34b);
    • a first passage (38)causing the other radial end of the first cavity (30a ; 34b) to communicate with an adjacent radial end of the second cavity (32a ; 36b);
    • a second passage (40) causing the other radial end of the second cavity (32a ; 36b) to communicate with an adjacent radial end of the third cavity (34a ; 38b); and
    • outlet orifices (42a ; 42b) opening from the third cavity (34a ; 38b) out into the pressure-side face (20) of the blade.
  3. A blade according to claim 2, in which the third cavity (34a) of the suction-side cooling circuit is disposed beside the trailing edge (18) of the blade.
  4. A blade according to claim 2, in which the third cavity (38b) of the suction-side cooling circuit is disposed beside the leading edge (16) of the blade.
  5. A blade according to claim 1, in which the suction-side cooling circuit comprises:
    • a first cavity (34c ; 34d) and a second cavity (36c ; 36d) extending on the suction side of the blade;
    • a third cavity (38c ; 38d) extending on the pressure side of the blade;
    • an air admission opening at one radial end of the first cavity;
    • a first passage causing the other radial end of the first cavity (34c ; 34d) to communicate with an adjacent radial end of the second cavity (36c ;36d);
    • a second passage causing the other radial end of the second cavity (36c ;36d) to communicate with an adjacent radial end of the third cavity (38c ; 38d); and
    • outlet orifices (42c ; 42d) opening from the third cavity (38c ; 38d) out into the pressure-side face (20) of the blade.
  6. A blade according to claim 5, in which the third cavity (38c) of the suction-side cooling circuit is disposed beside the leading edge (16) of the blade.
  7. A blade according to claim 5, in which the third cavity (38d) of the suction-side cooling circuit is disposed beside the trailing edge (18) of the blade.
  8. A blade according to any one of claims 1 to 7, in which the pressure- side cooling circuit comprises:
    • First (24a ; 24b), second (26a ; 26b), and third (28a ; 28b) cavities extending on the pressure side of the blade;
    • an air admission opening (44) at a radial end of the first cavity (24a ; 24b);
    • a first passage (46) causing the other radial end of the first cavity (24a ; 24b) to communicate with an adjacent radial end of the second cavity (26a ; 26b);
    • a second passage (48)causing the other radial end of the second cavity (26a ; 26b) to communicate with an adjacent radial end of the third cavity (28a ; 28b); and
    • outlet orifices (50a ; 50b) opening from the third cavity (28a ; 28b) out into the pressure-side face (20) of the blade.
  9. A blade according to any one of claims 1 to 8, further including a leading edge cooling circuit comprising:
    • a first radial cavity (54) extending in the vicinity of the leading edge (16) of the blade;
    • a second radial cavity (56) extending from the pressure side to the suction side of the blade, said second cavity (56) being disposed between the first cavity (54) and the central portion (C) of the blade;
    • at least one air admission orifice (58) opening into the second cavity (56);
    • a plurality of communication holes (60) distributed over the entire radial height of the blade, opening from the second cavity (56) out into the first cavity (64); and
    • outlet orifices (62) opening from said first cavity (54) out into the leading edge (16) and into the pressure-side (20) and suction-side (22) faces of the blade.
  10. A blade according to any one of claims 1 to 9, further including a trailing edge cooling circuit, comprising:
    • a first radial cavity (64) extending in the vicinity of the trailing edge (18) of the blade;
    • a second radial cavity (66) extending from the pressure side to the suction side of the blade, said second cavity (66) being disposed between the first cavity (64) and the central portion (C) of the blade;
    • at least one air admission orifice (68) opening into the second cavity (66);
    • a plurality of communication holes (70) distributed over the radial height of the blade opening from the second cavity (66) out into the first cavity (64); and
    • outlet orifices (72) opening from said first cavity (64) out into the trailing edge (18) of the blade.
  11. A gas turbine, including at least one moving blade (10a, 10b, 10c, 10d) according to any one of claims 1 to 10.
  12. A turbomachine, including at least one moving blade (10a, 10b, 10c, 10d) according to any one of claims 1 to 10.
EP06124041.2A 2005-11-28 2006-11-14 Turbine blade comprising a cooling circuit Active EP1790819B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0512003A FR2893974B1 (en) 2005-11-28 2005-11-28 CENTRAL COOLING CIRCUIT FOR MOBILE TURBINE DRIVE

Publications (2)

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EP1790819A1 EP1790819A1 (en) 2007-05-30
EP1790819B1 true EP1790819B1 (en) 2017-06-21

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EP (1) EP1790819B1 (en)
JP (1) JP4823872B2 (en)
CA (1) CA2569566C (en)
FR (1) FR2893974B1 (en)
RU (1) RU2421623C2 (en)

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US7661930B2 (en) 2010-02-16
RU2006141862A (en) 2008-06-10
FR2893974A1 (en) 2007-06-01
CA2569566C (en) 2013-12-24
JP4823872B2 (en) 2011-11-24
CA2569566A1 (en) 2007-05-28
RU2421623C2 (en) 2011-06-20
US20070122282A1 (en) 2007-05-31
EP1790819A1 (en) 2007-05-30
FR2893974B1 (en) 2011-03-18
JP2007146842A (en) 2007-06-14

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