EP4004345A1 - Turbomachine moving blade with cooling circuit having a double row of discharge slots - Google Patents

Turbomachine moving blade with cooling circuit having a double row of discharge slots

Info

Publication number
EP4004345A1
EP4004345A1 EP20757636.4A EP20757636A EP4004345A1 EP 4004345 A1 EP4004345 A1 EP 4004345A1 EP 20757636 A EP20757636 A EP 20757636A EP 4004345 A1 EP4004345 A1 EP 4004345A1
Authority
EP
European Patent Office
Prior art keywords
blade
slots
discharge slots
discharge
open
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.)
Pending
Application number
EP20757636.4A
Other languages
German (de)
French (fr)
Inventor
Patrice Eneau
Michel SLUSARZ
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
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP4004345A1 publication Critical patent/EP4004345A1/en
Pending legal-status Critical Current

Links

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
    • F01D5/186—Film 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
    • F01D5/187—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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
    • 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

Definitions

  • the present invention relates to the general field of turbomachine blades, and more particularly to the evacuation at the trailing edge of cooling air from the blades of a high-pressure turbine of a turbomachine.
  • the blades of a turbomachine high-pressure turbine are subjected to the high temperatures of the gases from the combustion chamber which pass through the high-pressure turbine. These temperatures reach values much higher than those that the blades which are in contact with these gases can withstand, which has the consequence of limiting their service life.
  • cooling air which is generally introduced into the blade by its foot, passes through the latter by following a path formed by cavities made in the blade before being ejected through slots. opening to the surface of the blade, between the root and the top of the latter.
  • the trailing edge of the moving blade is a critical area from a point of view. thermal and mechanical due to the difficulty in cooling it effectively. This is mainly due to the lack of space, in particular because of the minimum thicknesses of material required for the manufacture of the blade, and in particular to the junction of the lower surface and upper surface at the trailing edge.
  • the vane area upstream of the exhaust slits is a difficult to cool area which regularly displays a high thermal level. This is mainly due to the lack of space to put turbulence promoters for cooling and to have two cooling cavities in the thickness of the blade.
  • the object of the present invention is therefore to provide a movable blade of
  • turbomachine which does not have the aforementioned drawbacks.
  • a mobile turbine engine blade comprising a blade extending radially between a blade root and a blade top and axially between a leading edge and a trailing edge.
  • at least one cooling circuit comprising at least one cavity extending radially between the foot and the top, at least one air intake opening at a radial end of the cavity, a plurality of first exhaust slots provided along the trailing edge between the foot and the crown, and a plurality of second exhaust slits distinct from the first slits and provided along the trailing edge between the foot and the crown, the second exhaust slits being offset axially upstream of the first discharge slots and each of the first discharge slots being radially offset from each of the second discharge slots, with no overlap between the first and second discharge slots cuation.
  • the invention is remarkable in that it provides an additional row of discharge slots upstream and radially offset without overlapping vis-à-vis. from the usual row of exhaust slots.
  • this additional row makes it possible to benefit from cooling upstream of the usual slots.
  • the intrados face of the blade is then cooled on a larger curvilinear abscissa at the level of the trailing edge of the blade.
  • upstream of this row
  • the first discharge slots and the second discharge slots may open into the same cavity of the cooling circuit.
  • evacuation can lead into two separate cavities of the cooling circuit.
  • the cavity into which the second discharge slots open is preferably offset axially upstream with respect to the cavity into which the first discharge slots open.
  • the first evacuation slits open at the level of the trailing edge and the second evacuation slits can open at the level of a lower surface of the blade.
  • drainage can open at a lower surface of the blade.
  • the first discharge slots and the second discharge slots can be arranged in columns. Likewise, the second exhaust slits can exactly occupy each of the radial spaces left between the first exhaust slits.
  • the invention also relates to a process for manufacturing by foundry of a blade as defined above, comprising the production of a ceramic core by additive manufacturing, the core making it possible to produce the first slots
  • a further subject of the invention is a high-pressure turbine for a turbomachine, comprising a disc which has a plurality of cells which open out at the periphery of the disc and a plurality of blades as defined above.
  • Figure 1 is a perspective view of an exemplary dawn to which the invention applies.
  • Figure 2 is a cross-sectional view of a vane according to one embodiment of the invention showing the cooling circuit of the trailing edge of the vane.
  • FIG. 3 is a partial perspective view from the lower surface of a blade according to another embodiment of the invention showing the exhaust slots of the cooling circuit of the trailing edge of the blade.
  • FIG. 4 is a partial and perspective view from the lower surface of a blade according to yet another embodiment of the invention.
  • FIG. 1 shows in perspective a turbine blade 2, for example a moving blade of a high-pressure turbine of a turbomachine.
  • the blade 2 is attached to a turbine rotor (not shown) via a socket 4 generally in the shape of a fir tree.
  • the blade 2 comprises a blade 6 which extends radially between a blade root 8 and a blade top 10, and axially between a leading edge 12 and a trailing edge 14.
  • the blade 6 of the blade thus defines the lower surface 6a and the upper surface 6b of the blade.
  • the blade 2 which is subjected to the high temperatures of the combustion gases passing through the turbine, needs to be cooled.
  • the blade 2 comprises one or more internal cooling circuits, and in particular an internal cooling circuit for the trailing edge.
  • the internal circuit for cooling the trailing edge of the blade comprises at least one cavity 16 extending radially between the foot 8 and the top 10.
  • the cavity 16 is supplied with cooling air at one of its radial ends by an air intake opening (not shown) which is generally provided at the level of the root 4 of the blade. .
  • the internal cooling circuit of the trailing edge of the blade comprises two distinct cavities 16a, 16b which are axially offset from one another.
  • the cooling circuit of the trailing edge also comprises a plurality of first evacuation slots 18 which are arranged along the trailing edge 14 of the vane between the root 8 and the top 10, and a plurality 20 second evacuation slits which are distinct from the first slits
  • the first discharge slots 18 open into the cavity 16b of the cooling circuit and open onto the underside face 6a of the blade near its trailing edge 14.
  • the second evacuation slots 20 they open into the cavity 16a of the cooling circuit and also open onto the lower surface face 6a of the blade near its trailing edge 14.
  • the second discharge slots 20 are offset axially upstream with respect to the first discharge slots 18 and arranged to be radially offset with respect to the first discharge slots without overlap between them, that is, the bottom wall of a given slot does not overlap the top wall of the adjacent radially offset slot and vice versa.
  • first and second discharge slots 18, 20 are arranged to form two distinct rows of slots which are axially and radially offset from each other.
  • FIG. 3 represents a second embodiment of the invention in which the first discharge slits 18 and the second discharge slots 20 open into the same cavity 16 of the cooling circuit of the trailing edge of the blade. More precisely, in this example, which cannot be limited to this supply by a single cavity, the lower walls of the first slots 18 coincide with the upper walls of the adjacent second slits 20 and the upper walls of the first slits 18 coincide with the lower walls of the adjacent second slits 20, so that the second slits exactly occupy each of the radial spaces left between the first slits.
  • FIG. 4 shows a third embodiment of the invention in which the first evacuation slots 18 of the cooling circuit of the trailing edge open out at the level of the trailing edge 14 of the vane, while the second slots of evacuation 20 open at the level of the lower surface 6a of the blade 2.
  • the blade 2 according to the invention is obtained directly by molding.
  • the vane is made by pouring a metal into a mold containing a ceramic core which has the particular function of reserving a location for the circuit.
  • blade cooling and in particular for the cavity 16 and the first and second discharge slots 18, 20 of the cooling circuit of the trailing edge of the blade.
  • the ceramic core is advantageously produced by additive manufacturing.

Landscapes

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

Abstract

The invention relates to a turbomachine moving blade (2) comprising at least one cooling circuit comprising at least one cavity (16; 16a, 16b) extending radially between the foot and the vertex, at least one air intake opening at a radial end of the cavity, a plurality of first discharge slots (18) arranged to open out along the trailing edge between the foot and the vertex, and a plurality of second discharge slots (20) which are separate from the first discharge slots and provided along the trailing edge (14) between the foot and the vertex, the second discharge slots (20) being axially offset upstream from the first discharge slots (18) and each of the first discharge slots being radially offset from each of the second discharge slots, without any overlap between the first and second discharge slots.

Description

Description Description
Titre de l'invention : Aube mobile de turbomachine à circuit de refroidissement ayant une double rangée de fentes d'évacuation Title of the invention: Mobile blade of a cooling circuit turbomachine having a double row of discharge slots
Domaine Technique Technical area
La présente invention se rapporte au domaine général des aubes de turbomachine, et plus particulièrement à l’évacuation en bord de fuite de l’air de refroidissement d’aubes d’une turbine haute-pression de turbomachine. The present invention relates to the general field of turbomachine blades, and more particularly to the evacuation at the trailing edge of cooling air from the blades of a high-pressure turbine of a turbomachine.
Technique antérieure Prior art
Les aubes d’une turbine haute-pression de turbomachine sont soumises aux températures élevées des gaz issus de la chambre de combustion et qui traversent la turbine haute-pression. Ces températures atteignent des valeurs largement supérieure à celles que peuvent supporter les aubes qui sont en contact avec ces gaz, ce qui a pour conséquence de limiter leur durée de vie. The blades of a turbomachine high-pressure turbine are subjected to the high temperatures of the gases from the combustion chamber which pass through the high-pressure turbine. These temperatures reach values much higher than those that the blades which are in contact with these gases can withstand, which has the consequence of limiting their service life.
Afin de limiter les dommages causés par ces gaz chauds sur les aubes, il est connu de les munir 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, entre le pied et le sommet de celle-ci. In order to limit the damage caused by these hot gases on the blades, it is known practice to provide them with internal cooling circuits aimed at reducing the temperature of the latter. Thanks to such circuits, the cooling air, which is generally introduced into the blade by its foot, passes through the latter by following a path formed by cavities made in the blade before being ejected through slots. opening to the surface of the blade, between the root and the top of the latter.
Les besoins grandissant en termes de performances, rendement, durée de vie et fiabilité poussent à concevoir des circuits de refroidissement de plus en plus efficaces. En effet, augmenter l’efficacité de ces circuits de refroidissement présente de nombreux avantages. En particulier, le niveau thermique admissible dans la veine sera plus élevé et le moteur plus performant à iso-débit de refroidissement. De plus, le débit de refroidissement nécessaire pour garantir l’intégrité des pièces refroidies par ces circuits de refroidissement sera moins important pour un point de The growing needs in terms of performance, efficiency, service life and reliability are pushing the design of increasingly efficient cooling circuits. Indeed, increasing the efficiency of these cooling circuits has many advantages. In particular, the permissible thermal level in the duct will be higher and the engine more efficient with iso-cooling flow. In addition, the cooling flow required to guarantee the integrity of the parts cooled by these cooling circuits will be less important for a
fonctionnement donné. Enfin, la durée de vie de ces pièces sera plus élevée pour un même débit de ventilation et pour les mêmes conditions thermodynamiques. given operation. Finally, the service life of these parts will be longer for the same ventilation flow rate and for the same thermodynamic conditions.
Dans cette optique d’augmenter l’efficacité des circuits de refroidissement, on constate que le bord de fuite de l’aube mobile est une zone critique d’un point de vue thermique et mécanique du fait de la difficulté à le refroidir efficacement. Ceci est principalement dû au manque d’espace, notamment à cause des épaisseurs minimales de matière requises pour la fabrication de l’aube, et en particulier à la jonction des parois intrados et extrados au bord de fuite. With this in mind to increase the efficiency of the cooling circuits, it can be seen that the trailing edge of the moving blade is a critical area from a point of view. thermal and mechanical due to the difficulty in cooling it effectively. This is mainly due to the lack of space, in particular because of the minimum thicknesses of material required for the manufacture of the blade, and in particular to the junction of the lower surface and upper surface at the trailing edge.
Pour refroidir efficacement le bord de fuite, il est connu de réaliser par fonderie des fentes d’évacuation des circuits de refroidissement du côté intrados de l’aube. Ces fentes permettent un refroidissement de la matière au bord de fuite par pompage, et par film (« film cooling » en anglais) avec une éjection quasi-tangente au profil de l’aube, ce qui augmente fortement son efficacité. In order to effectively cool the trailing edge, it is known practice to produce drainage slots for the cooling circuits by casting on the lower surface of the blade. These slots allow cooling of the material at the trailing edge by pumping, and by film ("film cooling" in English) with an ejection almost tangent to the profile of the blade, which greatly increases its efficiency.
En revanche, la zone de l’aube en amont des fentes d’évacuation est une zone difficile à refroidir qui affiche régulièrement un niveau thermique important. Ceci est dû notamment au manque d’espace pour mettre des promoteurs de turbulences pour le refroidissement et pour avoir deux cavités de refroidissement dans l’épaisseur de l’aube. In contrast, the vane area upstream of the exhaust slits is a difficult to cool area which regularly displays a high thermal level. This is mainly due to the lack of space to put turbulence promoters for cooling and to have two cooling cavities in the thickness of the blade.
Exposé de l’invention Disclosure of the invention
La présente invention a donc pour but de proposer une aube mobile de The object of the present invention is therefore to provide a movable blade of
turbomachine qui ne présente pas les inconvénients précités. turbomachine which does not have the aforementioned drawbacks.
Conformément à l’invention, ce but est atteint grâce à une aube mobile de turbomachine, comprenant une pale s’étendant radialement entre un pied d’aube et un sommet d’aube et axialement entre un bord d’attaque et un bord de fuite, et au moins un circuit de refroidissement comprenant au moins une cavité s’étendant radialement entre le pied et le sommet, au moins une ouverture d’admission d’air à une extrémité radiale de la cavité, une pluralité de premières fentes d’évacuation aménagées le long du bord de fuite entre le pied et le sommet, et une pluralité de secondes fentes d’évacuation distinctes des premières fentes et aménagées le long du bord de fuite entre le pied et le sommet, les secondes fentes d’évacuation étant décalées axialement vers l’amont par rapport aux premières fentes d’évacuation et chacune des premières fentes d’évacuation étant radialement décalée par rapport à chacune des deuxièmes fentes d’évacuation, sans chevauchement entre les premières et secondes fentes d’évacuation. According to the invention, this object is achieved by virtue of a mobile turbine engine blade, comprising a blade extending radially between a blade root and a blade top and axially between a leading edge and a trailing edge. , and at least one cooling circuit comprising at least one cavity extending radially between the foot and the top, at least one air intake opening at a radial end of the cavity, a plurality of first exhaust slots provided along the trailing edge between the foot and the crown, and a plurality of second exhaust slits distinct from the first slits and provided along the trailing edge between the foot and the crown, the second exhaust slits being offset axially upstream of the first discharge slots and each of the first discharge slots being radially offset from each of the second discharge slots, with no overlap between the first and second discharge slots cuation.
L’invention est remarquable en ce qu’elle prévoit une rangée supplémentaire de fentes d’évacuation en amont et radialement décalée sans chevauchement vis-à-vis de la rangée de fentes d’évacuation habituelle. Ainsi, cette rangée supplémentaire permet de bénéficier d’un refroidissement en amont des fentes habituelles. La face intrados de l’aube est alors refroidie sur une abscisse curviligne plus importante au niveau du bord de fuite de l’aube. Par ailleurs, en amont de cette rangée The invention is remarkable in that it provides an additional row of discharge slots upstream and radially offset without overlapping vis-à-vis. from the usual row of exhaust slots. Thus, this additional row makes it possible to benefit from cooling upstream of the usual slots. The intrados face of the blade is then cooled on a larger curvilinear abscissa at the level of the trailing edge of the blade. Moreover, upstream of this row
supplémentaire de fentes d’évacuation, l’épaisseur du profil de l’aube est plus importante, ce qui permet de disposer d’une cavité munie de promoteurs de refroidissement ou de disposer de deux cavités distinctes. Enfin, cette disposition radialement décalée des fentes des deux rangées sans chevauchement entre elles permet d’augmenter l’efficacité du refroidissement, notamment pour le Additional discharge slots, the thickness of the blade profile is greater, which allows to have a cavity provided with cooling promoters or to have two separate cavities. Finally, this radially offset arrangement of the slots of the two rows without overlapping between them makes it possible to increase the efficiency of the cooling, in particular for the
refroidissement des nervures de fentes situées en aval. cooling downstream slot ribs.
Les premières fentes d’évacuation et les secondes fentes d’évacuation peuvent déboucher dans la même cavité du circuit de refroidissement. The first discharge slots and the second discharge slots may open into the same cavity of the cooling circuit.
Alternativement, les premières fentes d’évacuation et les secondes fentes Alternatively, the first escape slits and the second slits
d’évacuation peuvent déboucher dans deux cavités distinctes du circuit de refroidissement. evacuation can lead into two separate cavities of the cooling circuit.
Dans ce cas, la cavité dans laquelle débouchent les secondes fentes d’évacuation est de préférence décalée axialement vers l’amont par rapport à la cavité dans laquelle débouchent les premières fentes d’évacuation. In this case, the cavity into which the second discharge slots open is preferably offset axially upstream with respect to the cavity into which the first discharge slots open.
Les premières fentes d’évacuation débouchent au niveau du bord de fuite et les secondes fentes d’évacuation peuvent déboucher au niveau d’une face intrados de l’aube. The first evacuation slits open at the level of the trailing edge and the second evacuation slits can open at the level of a lower surface of the blade.
Alternativement, les premières fentes d’évacuation et les secondes fentes Alternatively, the first escape slits and the second slits
d’évacuation peuvent s’ouvrir au niveau d’une face intrados de l’aube. drainage can open at a lower surface of the blade.
Les premières fentes d’évacuation et les secondes fentes d’évacuation peuvent être agencées en colonnes. De même, les secondes fentes d’évacuation peuvent occuper exactement chacun des espaces radiaux laissés entre les premières fentes d’évacuation The first discharge slots and the second discharge slots can be arranged in columns. Likewise, the second exhaust slits can exactly occupy each of the radial spaces left between the first exhaust slits.
L’invention a également objet un procédé de fabrication par fonderie d’une aube telle que définie précédemment, comprenant la réalisation d’un noyau en céramique par fabrication additive, le noyau permettant de réaliser les premières fentes The invention also relates to a process for manufacturing by foundry of a blade as defined above, comprising the production of a ceramic core by additive manufacturing, the core making it possible to produce the first slots
d’évacuation et les secondes fentes d’évacuation. Cette solution de fabrication permet de réaliser les noyaux de fonderie nécessaires pour réserver les emplacements pour les cavités du circuit de refroidissement. L’invention a encore pour objet une turbine haute-pression de turbomachine, comprenant un disque qui présente une pluralité d’alvéoles qui débouchent à la périphérie du disque et une pluralité d’aubes telles que définies précédemment. evacuation and the second evacuation slots. This manufacturing solution makes it possible to produce the foundry cores necessary to reserve the locations for the cavities of the cooling circuit. A further subject of the invention is a high-pressure turbine for a turbomachine, comprising a disc which has a plurality of cells which open out at the periphery of the disc and a plurality of blades as defined above.
Brève description des dessins Brief description of the drawings
[Fig. 1 ] La figure 1 est une vue en perspective d’un exemple d’aube à laquelle s’applique l’invention. [Fig. 1] Figure 1 is a perspective view of an exemplary dawn to which the invention applies.
[Fig. 2] La figure 2 est une vue en coupe transversale d’une aube selon un mode de réalisation de l’invention montrant le circuit de refroidissement du bord de fuite de l’aube. [Fig. 2] Figure 2 is a cross-sectional view of a vane according to one embodiment of the invention showing the cooling circuit of the trailing edge of the vane.
[Fig. 3] La figure 3 est une vue partielle et en perspective côté intrados d’une aube selon un autre mode de réalisation de l’invention montrant les fentes d’évacuation du circuit de refroidissement du bord de fuite de l’aube. [Fig. 3] FIG. 3 is a partial perspective view from the lower surface of a blade according to another embodiment of the invention showing the exhaust slots of the cooling circuit of the trailing edge of the blade.
[Fig. 4] La figure 4 est une vue partielle et en perspective côté intrados d’une aube selon encore un autre mode de réalisation de l’invention. [Fig. 4] FIG. 4 is a partial and perspective view from the lower surface of a blade according to yet another embodiment of the invention.
Description des modes de réalisation Description of embodiments
La figure 1 représente en perspective une aube 2 de turbine, par exemple une aube mobile de turbine haute-pression d’une turbomachine. L’aube 2 est fixée sur un rotor de turbine (non représenté) par l’intermédiaire d’un emmanchement 4 généralement en forme de sapin. FIG. 1 shows in perspective a turbine blade 2, for example a moving blade of a high-pressure turbine of a turbomachine. The blade 2 is attached to a turbine rotor (not shown) via a socket 4 generally in the shape of a fir tree.
De façon connue, l’aube 2 comprend une pale 6 qui s’étend radialement entre un pied 8 d’aube et un sommet 10 d’aube, et axialement entre un bord d’attaque 12 et un bord de fuite 14. La pale 6 de l’aube définit ainsi l’intrados 6a et l’extrados 6b de l’aube. In known manner, the blade 2 comprises a blade 6 which extends radially between a blade root 8 and a blade top 10, and axially between a leading edge 12 and a trailing edge 14. The blade 6 of the blade thus defines the lower surface 6a and the upper surface 6b of the blade.
L’aube 2, qui est soumise aux températures élevées des gaz de combustion traversant la turbine nécessite d’être refroidie. A cet effet, et toujours de façon connue, l’aube 2 comporte un ou plusieurs circuits internes de refroidissement, et notamment un circuit interne de refroidissement du bord de fuite. The blade 2, which is subjected to the high temperatures of the combustion gases passing through the turbine, needs to be cooled. To this end, and still in a known manner, the blade 2 comprises one or more internal cooling circuits, and in particular an internal cooling circuit for the trailing edge.
Comme représenté sur la figure 2, le circuit interne de refroidissement du bord de fuite de l’aube comprend au moins une cavité 16 s’étendant radialement entre le pied 8 et le sommet 10. La cavité 16 est alimentée en air de refroidissement à l’une de ses extrémités radiales par une ouverture d’admission d’air (non représentée) qui est généralement prévue au niveau du pied 4 de l’aube. As shown in FIG. 2, the internal circuit for cooling the trailing edge of the blade comprises at least one cavity 16 extending radially between the foot 8 and the top 10. The cavity 16 is supplied with cooling air at one of its radial ends by an air intake opening (not shown) which is generally provided at the level of the root 4 of the blade. .
Dans l’exemple de réalisation représenté sur la figure 2, le circuit interne de refroidissement du bord de fuite de l’aube comprend deux cavités distinctes 16a, 16b qui sont décalées axialement l’une par rapport à l’autre. In the exemplary embodiment shown in Figure 2, the internal cooling circuit of the trailing edge of the blade comprises two distinct cavities 16a, 16b which are axially offset from one another.
Selon l’invention, le circuit de refroidissement du bord de fuite comprend également une pluralité de premières fentes d’évacuation 18 qui sont aménagées le long du bord de fuite 14 de l’aube entre le pied 8 et le sommet 10, et une pluralité de secondes fentes d’évacuation 20 qui sont distinctes des premières fentes According to the invention, the cooling circuit of the trailing edge also comprises a plurality of first evacuation slots 18 which are arranged along the trailing edge 14 of the vane between the root 8 and the top 10, and a plurality 20 second evacuation slits which are distinct from the first slits
d’évacuation 18 et qui sont également aménagées le long du bord de fuite entre le pied et le sommet d’aube. 18 and which are also arranged along the trailing edge between the foot and the top of the dawn.
Dans l’exemple de réalisation représenté sur la figure 2, les premières fentes d’évacuation 18 débouchent dans la cavité 16b du circuit de refroidissement et s’ouvrent sur la face intrados 6a de l’aube à proximité de son bord de fuite 14. Quant aux secondes fentes d’évacuation 20, elles débouchent dans la cavité 16a du circuit de refroidissement et s’ouvrent également sur la face intrados 6a de l’aube à proximité de son bord de fuite 14. In the exemplary embodiment shown in FIG. 2, the first discharge slots 18 open into the cavity 16b of the cooling circuit and open onto the underside face 6a of the blade near its trailing edge 14. As for the second evacuation slots 20, they open into the cavity 16a of the cooling circuit and also open onto the lower surface face 6a of the blade near its trailing edge 14.
Par ailleurs, comme représenté plus précisément sur la figure 3, les secondes fentes d’évacuation 20 sont décalées axialement vers l’amont par rapport aux premières fentes d’évacuation 18 et disposées pour être radialement décalées par rapport aux premières fentes d’évacuation sans chevauchement entre elles, c’est-à-dire que la paroi inférieure d’une fente donnée ne chevauche pas la paroi supérieure de la fente adjacente radialement décalé et inversement. Furthermore, as shown more precisely in Figure 3, the second discharge slots 20 are offset axially upstream with respect to the first discharge slots 18 and arranged to be radially offset with respect to the first discharge slots without overlap between them, that is, the bottom wall of a given slot does not overlap the top wall of the adjacent radially offset slot and vice versa.
Ainsi, les premières et secondes fentes d’évacuation 18, 20 sont agencées de sorte à former deux rangées distinctes de fentes qui sont décalées axialement et radialement l’une par rapport à l’autre. Thus, the first and second discharge slots 18, 20 are arranged to form two distinct rows of slots which are axially and radially offset from each other.
La figure 3 représente un deuxième mode de réalisation de l’invention dans laquelle les premières fentes d’évacuation 18 et les secondes fentes d’évacuation 20 débouchent dans la même cavité 16 du circuit de refroidissement du bord de fuite de l’aube. Plus précisément, dans cet exemple qui ne saurait être limité à cette alimentation par une unique cavité, les parois inférieures des premières fentes 18 coïncident avec les parois supérieures des secondes fentes adjacentes 20 et les parois supérieures des premières fentes 18 coïncident avec les parois inférieures des secondes fentes adjacentes 20, de sorte que les secondes fentes occupent exactement chacun des espaces radiaux laissés entre les premières fentes. FIG. 3 represents a second embodiment of the invention in which the first discharge slits 18 and the second discharge slots 20 open into the same cavity 16 of the cooling circuit of the trailing edge of the blade. More precisely, in this example, which cannot be limited to this supply by a single cavity, the lower walls of the first slots 18 coincide with the upper walls of the adjacent second slits 20 and the upper walls of the first slits 18 coincide with the lower walls of the adjacent second slits 20, so that the second slits exactly occupy each of the radial spaces left between the first slits.
La figure 4 représente un troisième mode de réalisation de l’invention dans laquelle les premières fentes d’évacuation 18 du circuit de refroidissement du bord de fuite débouchent au niveau du bord de fuite 14 de l’aube, tandis que les secondes fentes d’évacuation 20 débouchent au niveau de la face intrados 6a de l’aube 2. FIG. 4 shows a third embodiment of the invention in which the first evacuation slots 18 of the cooling circuit of the trailing edge open out at the level of the trailing edge 14 of the vane, while the second slots of evacuation 20 open at the level of the lower surface 6a of the blade 2.
L’aube 2 selon l’invention est obtenue directement par moulage. A cet effet, l’aube est réalisée en coulant un métal dans un moule contenant un noyau céramique qui a notamment pour fonction de réserver un emplacement pour le circuit de The blade 2 according to the invention is obtained directly by molding. For this purpose, the vane is made by pouring a metal into a mold containing a ceramic core which has the particular function of reserving a location for the circuit.
refroidissement de l’aube, et notamment pour la cavité 16 et les premières et secondes fentes d’évacuation 18, 20 du circuit de refroidissement du bord de fuite de l’aube. blade cooling, and in particular for the cavity 16 and the first and second discharge slots 18, 20 of the cooling circuit of the trailing edge of the blade.
Afin d’obtenir directement en sortie de fonderie la double rangée de fentes d’évacuation, le noyau en céramique est avantageusement réalisée par fabrication additive. In order to obtain the double row of discharge slots directly at the foundry outlet, the ceramic core is advantageously produced by additive manufacturing.

Claims

Revendications Claims
[Revendication 1] Aube mobile (2) de turbomachine, comprenant : [Claim 1] movable blade (2) of a turbomachine, comprising:
une pale (6) s'étendant radialement entre un pied (8) d'aube et un sommet (10) d'aube et axialement entre un bord d'attaque (12) et un bord de fuite (14) ; et a blade (6) extending radially between a blade root (8) and a blade top (10) and axially between a leading edge (12) and a trailing edge (14); and
au moins un circuit de refroidissement comprenant au moins une cavité (16 ; 16a, 16b) s'étendant radialement entre le pied (8) et le sommet (10), au moins une ouverture d'admission d'air à une extrémité radiale de la cavité (16 ; 16a, 16b), une pluralité de premières fentes d'évacuation (18) aménagées pour déboucher le long du bord de fuite entre le pied (8) et le sommet (10), et une pluralité de secondes fentes d'évacuation (20) distinctes des premières fentes d'évacuation et aménagées le long du bord de fuite (14) entre le pied (8) et le sommet (10), les secondes fentes d'évacuation (20) étant décalées axialement vers l'amont par rapport aux premières fentes d'évacuation (18) et chacune des premières fentes d'évacuation (18) étant radialement décalée par rapport à chacune des deuxièmes fentes at least one cooling circuit comprising at least one cavity (16; 16a, 16b) extending radially between the foot (8) and the top (10), at least one air intake opening at a radial end of the cavity (16; 16a, 16b), a plurality of first discharge slits (18) arranged to open along the trailing edge between the foot (8) and the top (10), and a plurality of second slits d 'discharge (20) distinct from the first discharge slots and arranged along the trailing edge (14) between the foot (8) and the top (10), the second discharge slots (20) being offset axially towards the 'upstream with respect to the first discharge slots (18) and each of the first discharge slots (18) being radially offset from each of the second slots
d'évacuation (20), sans chevauchement entre les premières et secondes fentes d'évacuation. outlet (20), without overlap between the first and second outlet slots.
[Revendication 2] Aube (2) selon la revendication 1, dans laquelle les [Claim 2] A blade (2) according to claim 1, wherein the
premières fentes d'évacuation (18) et les secondes fentes d'évacuation (20) débouchent dans la même cavité (16) du circuit de refroidissement. first discharge slots (18) and the second discharge slots (20) open into the same cavity (16) of the cooling circuit.
[Revendication 3] Aube (2) selon la revendication 1, dans laquelle les [Claim 3] A blade (2) according to claim 1, wherein the
premières fentes d'évacuation (18) et les secondes fentes d'évacuation (20) débouchent dans deux cavités (16a, 16b) distinctes du circuit de first evacuation slots (18) and the second evacuation slots (20) open into two cavities (16a, 16b) separate from the circuit of
refroidissement. cooling.
[Revendication 4] Aube (2) selon la revendication 3, dans laquelle la cavité (16a) dans laquelle débouchent les secondes fentes d'évacuation (20) est décalée axialement vers l'amont par rapport à la cavité (16b) dans laquelle débouchent les premières fentes d'évacuation (18). [Claim 4] blade (2) according to claim 3, wherein the cavity (16a) into which the second discharge slots (20) open is axially offset upstream with respect to the cavity (16b) into which open the first evacuation slots (18).
[Revendication 5] Aube (2) selon l'une quelconque des revendications 1 à 4, dans laquelle les premières fentes d'évacuation (18) débouchent au niveau du bord de fuite (14) et les secondes fentes d'évacuation (20) débouchent au niveau d'une face intrados (6a) de l'aube. [Claim 5] blade (2) according to any one of claims 1 to 4, wherein the first discharge slots (18) open at the trailing edge (14) and the second discharge slots (20) emerge at the level of an intrados face (6a) of the blade.
[Revendication 6] Aube (2) selon l'une quelconque des revendications 1 à 4, dans laquelle les premières fentes d'évacuation (18) et les secondes fentes d'évacuation (20) débouchent au niveau d'une face intrados (6a) de l'aube.[Claim 6] blade (2) according to any one of claims 1 to 4, in which the first discharge slots (18) and the second discharge slots (20) open out at a lower surface face (6a ) of dawn.
[Revendication 7] Aube (2) selon l'une quelconque des revendications 1 à 6, dans laquelle les premières fentes d'évacuation (18) et les secondes fentes d'évacuation (20) sont agencées en colonnes. [Claim 7] A blade (2) according to any one of claims 1 to 6, wherein the first discharge slots (18) and the second discharge slots (20) are arranged in columns.
[Revendication 8] Aube (2) selon l'une quelconque des revendications 1 à 6, dans laquelle les secondes fentes d'évacuation (20) occupent exactement chacun des espaces radiaux laissés entre les premières fentes d'évacuation (18). [Claim 8] A blade (2) according to any one of claims 1 to 6, wherein the second discharge slots (20) exactly occupy each of the radial spaces left between the first discharge slots (18).
[Revendication 9] Procédé de fabrication par fonderie d'une aube selon [Claim 9] A method of manufacturing by foundry of a blade according to
l'une quelconque des revendications 1 à 6, comprenant la réalisation d'un noyau en céramique par fabrication additive, le noyau permettant de réaliser les premières fentes d'évacuation (18) et les secondes fentes d'évacuation (20). any one of claims 1 to 6, comprising the production of a ceramic core by additive manufacturing, the core making it possible to produce the first discharge slots (18) and the second discharge slots (20).
[Revendication 10] Turbine haute-pression de turbomachine, comprenant un disque qui présente une pluralité d'alvéoles qui débouchent à la périphérie du disque et une pluralité d'aubes (2) selon l'une quelconque des revendications 1 à 7, le pied de chaque aube (2) étant monté dans une alvéole respective du disque. [Claim 10] A high-pressure turbine for a turbomachine, comprising a disc which has a plurality of cells which open out at the periphery of the disc and a plurality of vanes (2) according to any one of claims 1 to 7, the root of each blade (2) being mounted in a respective cell of the disc.
EP20757636.4A 2019-07-30 2020-07-22 Turbomachine moving blade with cooling circuit having a double row of discharge slots Pending EP4004345A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1908655A FR3099522B1 (en) 2019-07-30 2019-07-30 Cooling circuit turbomachine moving blade having a double row of discharge slots
PCT/FR2020/051338 WO2021019156A1 (en) 2019-07-30 2020-07-22 Turbomachine moving blade with cooling circuit having a double row of discharge slots

Publications (1)

Publication Number Publication Date
EP4004345A1 true EP4004345A1 (en) 2022-06-01

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US (1) US11913354B2 (en)
EP (1) EP4004345A1 (en)
CN (1) CN114207249B (en)
CA (1) CA3146412A1 (en)
FR (1) FR3099522B1 (en)
WO (1) WO2021019156A1 (en)

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2678318B1 (en) * 1991-06-25 1993-09-10 Snecma COOLED VANE OF TURBINE DISTRIBUTOR.
FR2689176B1 (en) * 1992-03-25 1995-07-13 Snecma DAWN REFRIGERATED FROM TURBO-MACHINE.
FR2782118B1 (en) * 1998-08-05 2000-09-15 Snecma COOLED TURBINE BLADE WITH LEADING EDGE
JP4798416B2 (en) * 2001-08-09 2011-10-19 株式会社Ｉｈｉ Turbine blade parts
FR2858352B1 (en) * 2003-08-01 2006-01-20 Snecma Moteurs COOLING CIRCUIT FOR TURBINE BLADE
US6981840B2 (en) * 2003-10-24 2006-01-03 General Electric Company Converging pin cooled airfoil
EP1847684A1 (en) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Turbine blade
US8721285B2 (en) * 2009-03-04 2014-05-13 Siemens Energy, Inc. Turbine blade with incremental serpentine cooling channels beneath a thermal skin
JP2012189026A (en) * 2011-03-11 2012-10-04 Ihi Corp Turbine blade
US20130084191A1 (en) * 2011-10-04 2013-04-04 Nan Jiang Turbine blade with impingement cavity cooling including pin fins
JP6038620B2 (en) 2012-12-05 2016-12-07 三菱日立パワーシステムズ株式会社 Gas turbine cooling blade and method of repairing gas turbine cooling blade
US10683762B2 (en) * 2016-07-12 2020-06-16 Rolls-Royce North American Technologies Inc. Gas engine component with cooling passages in wall
US10370300B2 (en) * 2017-10-31 2019-08-06 General Electric Company Additively manufactured turbine shroud segment

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CA3146412A1 (en) 2021-02-04
CN114207249A (en) 2022-03-18
US11913354B2 (en) 2024-02-27
FR3099522B1 (en) 2021-08-20
US20220316344A1 (en) 2022-10-06
WO2021019156A1 (en) 2021-02-04
CN114207249B (en) 2024-03-29
FR3099522A1 (en) 2021-02-05

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