EP3697552A1 - Hollow turbine blade with reduced intake of cooling air - Google Patents

Hollow turbine blade with reduced intake of cooling air

Info

Publication number
EP3697552A1
EP3697552A1 EP18799584.0A EP18799584A EP3697552A1 EP 3697552 A1 EP3697552 A1 EP 3697552A1 EP 18799584 A EP18799584 A EP 18799584A EP 3697552 A1 EP3697552 A1 EP 3697552A1
Authority
EP
European Patent Office
Prior art keywords
blade
cooling
core
diameter
rising
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.)
Granted
Application number
EP18799584.0A
Other languages
German (de)
French (fr)
Other versions
EP3697552B1 (en
Inventor
Léandre OSTINO
Matthieu Simon
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 EP3697552A1 publication Critical patent/EP3697552A1/en
Application granted granted Critical
Publication of EP3697552B1 publication Critical patent/EP3697552B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2240/307—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 tip 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
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the present invention relates to the general field of turbomachine blades, and more particularly to hollow turbine blades provided with integrated cooling circuits produced by the lost wax casting technique.
  • a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burned.
  • the gases from this combustion flow downstream of the combustion chamber and then feed a high pressure turbine and a low pressure turbine.
  • Each turbine has one or more rows of stationary blades (called distributors) alternating with one or more rows of moving blades (called wheels), circumferentially spaced around the rotor of the turbine.
  • These turbine blades are subjected to the very high temperatures of the combustion gases, which reach values which are much higher than those which can be withstood without damage from the blades in direct contact with these gases.
  • FIG. 4 schematically illustrates a core portion 10 of a gas turbine engine high-pressure turbine blade having an aerodynamic surface or blade 12 (in phantom tracing) which extends in a radial direction between a blade root (not shown) and a blade tip having a shaped part called tub 18 consisting of a bottom 18A transverse to the blade and a wall (or wall 18B ) forming its edge in the extension of the wall of the blade.
  • the blade comprises a plurality of cavities, however, for the purposes of the description, only four lateral cavities along the intrados face of the blade and a so-called "sub-bath" cavity disposed largely under the bottom of the bathtub 18A are illustrated by their respective core portions 22, 24, 26, 28, 30.
  • the core also includes first ceramic rods 32 - 40 extending from the sidewalls (e.g., the sidewall 24A of the core portion 24 ) core portions and intended to form inclined holes for cooling the bath wall 18B on the intrados face of the dawn
  • the present invention therefore aims to overcome the aforementioned drawbacks by proposing a hollow turbine blade whose cooling air intake is reduced to improve the specific consumption of the engine.
  • a turbomachine hollow turbine blade having a plurality of rising cavities communicating on the one hand with a bath of the blade by a plurality of dusting holes of a standard diameter for the evacuation of dust and secondly by a plurality of inclined cooling holes for cooling a wall of said tub by opening on an underside face of the blade, at least one rising cavity whose apex is devoid of a dedusting hole comprises an inclined cooling bore formed in its side wall and intended to cool said bath wall and whose diameter is enlarged to have a diameter at least equal to said standard diameter of a dedusting hole and thus also act as a dedusting hole, so that the flow of air taken for the cooling of the blade is reduced, dawn characterized in that at least one cavities of the blade disposed opposite said top of said at least one rising cavity has an increased volume corresponding at least to a volume subtracted from said top of said at least one rising cavity.
  • the inclined cooling bore thus enlarged also acting as a hole for Dusting has a slope oriented towards the bath between 45 and 75 °.
  • said apex of said at least one rising cavity has a concave shape, typically an inclined plane with an angle substantially equal to that of said inclined cooling bore or a step of stepping to direct the flow in the same direction as said inclined cooling bore.
  • said inclined cooling bore thus enlarged is disposed closer to said apex of said at least one rising cavity until it comes tangent to said vertex.
  • the invention also relates to a ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost-wax foundry technique, the blade comprising a plurality of rising cavities communicating on the one hand with a bath of the dawn by a plurality of dust extraction holes for the evacuation of dust and secondly by a plurality of inclined cooling holes for cooling a wall of said bathtub opening on an intrados face of the blade, the core comprising:
  • a core portion for forming a rising cavity of the blade is devoid at its top of a second ceramic rod for forming a dedusting hole and a first ceramic rod for forming in its side wall a inclined cooling bore also serving as a dusting hole for cooling said bath wall, has a first diameter at least equal to said second predetermined diameter, and in that said core portion has a subtracted volume at its apex and at least one of the other core portions of said plurality of core portions disposed opposite said apex of said core portion has an increased volume corresponding at least to said volume subtracted from said top of said at least one rising cavity.
  • said subtracted volume at the top of said at least one rising cavity has a concave shape, typically an inclined plane or a stair step whose inclination corresponds to that of said first ceramic rod.
  • said volume increase is a projecting portion centered on said core portion with a width and height substantially equal to that of said inclined plane without exceeding the top of said core portion.
  • the invention also relates to the use of such a ceramic core for the manufacture of a turbomachine hollow turbine blade according to the lost wax foundry technique and any turbomachine turbine provided with a plurality of hollow turbine blades.
  • FIG. 1 is an external perspective view of a moving blade of a high pressure turbine according to the invention
  • FIG. 2 is a schematic view of a first exemplary embodiment of a core portion of the turbine blade of FIG. 1,
  • FIG. 2A is a sectional view at an inclined cooling and dusting hole
  • FIG. 3 is a schematic view of a second exemplary embodiment of a core portion of the turbine blade of FIG. 1, and
  • FIG. 4 is a schematic view of a core portion of a turbine blade of the prior art. Detailed description of an embodiment
  • FIG. 1 illustrates a turbine engine high pressure turbine hollow blade conventionally extending radially with respect to an axis of rotation of a mobile wheel on which this hollow turbine blade is intended to be encased with a plurality of others.
  • the blade comprises a blade 12 forming the aerodynamic surface of the blade, a platform 14 supporting the blade and a blade root 16 carrying the assembly and ensuring its entrenchment to the rotor of the turbine wheel (not shown).
  • the blade 12 comprises, as is known, a leading edge 12A, a trailing edge 12B, an intrados face 12C and an extrados face (face hidden in the figure).
  • the bath 18 consisting of the bottom 18A transverse to the blade and the wall 18B forming its edge in the extension of the wall of the blade .
  • the blade also has perforations (holes on both sides or slots on the trailing edge) for generating a protective cooling air film for this blade. The number and the position of the perforations are optimized to maximize the cooling in the most heat-sensitive areas of the combustion gases in which these vanes are immersed and in particular for its intrados face 12C which undergoes the highest thermal stresses.
  • FIG. 2 shows a portion of a ceramic core 10 intended for producing the moving blade of FIG. 1.
  • This core does indeed show, in the illustrated example, only five core portions or columns that can be rising or down.
  • the first riser 22 is for example intended to form, once the blade has been completed, a lateral cavity of the blade (referenced 23 in FIG. 1) receiving a first flow of cooling air brought by a first pipe while the other three adjacent columns going back and forth on the intrados face (with two risers 24, 28 and one, in the center, 26) are intended to form lateral cavities of the blade (referenced respectively 25, 29 and 27 in Figure 1) which can receive a second flow of cooling air supplied by another pipe for example.
  • the last core portion 30 is intended to form a cavity called "sub-bath" (referenced 31 in Figure 1) disposed largely under the bath floor 18A.
  • the core also comprises the first ceramic rods 32, 36, 38, 40 extending from a side wall (for example 24A) of the risers and intended to form the inclined bores for cooling the bath wall 18B on the lower face of the bath.
  • the dawn and the second ceramic rods 42, 46, 48 extending vertically from the top (for example 24B) of these risers and intended to form the dedusting holes for the evacuation into the bath of the dust passing through with the cooling air the rising cavities 23, 29, 31 formed from these columns.
  • Such a multi-cavity ceramic core naturally includes other core portions intended to form other cavities, not shown, such as a cavity situated in the part of the blade near the leading edge 12A and one or more successive cavities. in line in the portion of the blade near the trailing edge 12B, all allowing the routing of the cooling air from the blade root 16 to parts of the blade associated with cooling.
  • the ceramic rods make it possible to create the inclined holes through which this air passes to reach the wall of the blade or to remove dust for those intended to form the dusting holes.
  • the columns are separated from each other by determined spacings thus leaving room for the creation of a full inter-cavity wall during the casting of the molten metal.
  • At least one of the rising cavities is devoid of a dedusting hole at its top and the inclined cooling bore (with an inclination oriented towards the bath of the order of 45 to 75 °), made in its side wall near the top of this cavity and normally intended to cool the bath wall opening on the underside of the blade, is enlarged in a ratio of 2 to 5 to also act as a dust removal hole, so that the air flow taken for cooling is reduced.
  • the cavity devoid of dusting hole is the rising cavity 25.
  • the other rising cavities 23 and 29 can also be devoid of dust extraction holes in the measurement where these rising cavities are positioned adjacent the under-bath cavity 31 (for example, Figure 3 with cavities 23 and 25).
  • this cooling and dedusting bore 51 (corresponding to a ceramic rod 50) must be much greater than the diameter of a standard cooling bore which, as previously indicated, is conventionally much lower, in order to in addition to cooling, ensure good evacuation of the dust circulating in the internal cooling air.
  • this hole is disposed closer to the closed top of the rising cavity, until almost tangent this summit, and may possibly be close to the bath wall 18B.
  • the diameter of the inclined cooling and dedusting bore is chosen at least equal to the diameter of a standard dedusting hole.
  • this inclination of the top of the rising cavity thus makes it possible to guide the residual dust towards the inclined drilling and to avoid the formation of zones of accumulation of particles at the top of this cavity.
  • this inclination of the top of the rising cavity can take any concave shape like a stair step, to direct the flow in the same direction as the inclined drilling.
  • the creation of an inclined plane at the vertex of the cavity by subtracting a core volume causes a local increase in corresponding quantity of material at the top of the blade compared to a standard configuration as illustrated in FIG. 4, which is unfavorable. for the mechanical strength of the dawn because of nature to generate a phenomenon of creep.
  • this increase in volume of the sub-bath core portion 30 is substantially equal (i.e., plus or minus 10%) to the volume resulting from the introduction of the plan.
  • inclined at the top of the riser 24 is preferably a projecting portion centered on the riser with a width and height substantially equal to those of the inclined plane (that is to say plus or minus 10%), the high level of this core extension 52 not exceeding that of this inclined plane, to ensure mechanical behavior similar to the initial configuration.
  • FIG. 3 illustrates another embodiment of the invention in which, not one but two rising cavities 23 and 25, are provided with cooling and dedusting holes corresponding to ceramic rods 50 and 54 of the columns 22 and 24. As in the preferred embodiment, these two holes are arranged closer to the top of the two rising cavities.
  • the diameter of these inclined cooling and dedusting holes is chosen at least equal to the diameter of a standard dedusting hole to which they replace.
  • the apex of each of the two rising cavities 23, 25 has an angle substantially identical to that of the inclined bores, that is to say of the order of 45 to 75 °.
  • a core extension 52 disposed as close as possible to these rising cavities.
  • This core extension is preferably a projecting portion extending on the two risers with a height substantially equal to that of the inclined planes, the high level of this core extension not exceeding that of these inclined planes.
  • the conducto-convective thermal transfer which takes place in the bore between the cooling air and the walls surrounding metal provides cooling by pumping effect of the area at the top of the blade in general and the lower wall of intrados bathtub in particular.
  • the local lowering of the air temperature in the vein and the increase of the heat exchange coefficient, close to the wall in the zones just downstream of the bores, under the effect of the emission of air cooling by the holes, provides cooling by film effect, unlike a conventional dust extraction hole where given the angle of emission of the cooling air relative to the wall of the blade, only the pumping effect contributes to the cooling of the area at the top of the blade.
  • the inclination of the cooling and dedusting holes must be sufficient (preferably greater than 45 °) to take advantage of the cooling by film effect without being too much (preferably less than 75 °) for reasons of Manufacture according to the technique of foundry with lost wax.

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

Abstract

Turbomachine hollow turbine blade comprising a plurality of rising cavities (23, 25, 29, 31) communicating with a channel (18) of the blade via a plurality of standard dust-removal holes (21A, 21B, 21C) intended for the removal of dust, and via a plurality of inclined cooling bores (20A, 20B, 20C, 20D) intended for cooling a low wall (18B) of the channel, opening on a lower face (12C) of the blade, at least one rising cavity (25) having an apex that has no dust-removal hole, and an inclined cooling bore produced in its side wall and intended to cool the low wall of the channel is enlarged in order to have a diameter at least equal to the standard diameter of a dust-removal hole and to thus also serve as a dust-removal hole (51), such that the flow of air taken in for the cooling of the blade is reduced, at least one of the cavities of the blade arranged opposite the top of one of the rising cavities having an increased volume corresponding at least to a volume subtracted at the top of the rising cavity.

Description

Aube de turbine creuse à prélèvement d'air de refroidissement réduit  Hollow turbine blade with reduced cooling air sampling
Domaine de l'invention Field of the invention
La présente invention se rapporte au domaine général des aubages de turbomachine, et plus particulièrement aux aubes creuses de turbine munies de circuits de refroidissement intégrés réalisées par la technique de la fonderie à la cire perdue.  The present invention relates to the general field of turbomachine blades, and more particularly to hollow turbine blades provided with integrated cooling circuits produced by the lost wax casting technique.
Art antérieur Prior art
De façon connue en soi, une turbomachine comporte une chambre de combustion dans laquelle de l'air et du carburant sont mélangés avant d'y être brûlés. Les gaz issus de cette combustion s'écoulent vers l'aval de la chambre de combustion et alimentent ensuite une turbine haute pression et une turbine basse pression. Chaque turbine comporte une ou plusieurs rangées d'aubes fixes (appelées distributeurs) alternant avec une ou plusieurs rangées d'aubes mobiles (appelées roues), espacées de façon circonférentielle tout autour du rotor de la turbine. Ces aubes de turbine qu'elles soient fixes ou mobiles sont soumises aux températures très élevées des gaz de combustion qui atteignent des valeurs largement supérieures à celles que peuvent supporter sans dommages des aubes en contact direct avec ces gaz.  In a manner known per se, a turbomachine comprises a combustion chamber in which air and fuel are mixed before being burned. The gases from this combustion flow downstream of the combustion chamber and then feed a high pressure turbine and a low pressure turbine. Each turbine has one or more rows of stationary blades (called distributors) alternating with one or more rows of moving blades (called wheels), circumferentially spaced around the rotor of the turbine. These turbine blades, whether stationary or mobile, are subjected to the very high temperatures of the combustion gases, which reach values which are much higher than those which can be withstood without damage from the blades in direct contact with these gases.
Afin de résoudre ce problème, il est donc connu de munir ces aubes de circuits de refroidissement internes présentant des niveaux d'efficacité thermique élevés et visant à réduire la température de ces dernières en créant, à l'intérieur de l'aube, une circulation organisée de cet air (par exemple au moyen de cavités simples à alimentation directe ou de trombones munis de cavités montantes et descendantes) et, dans la paroi de l'aube, des perforations destinées à générer un film protecteur pour cette aube. Le débit d'air utilisé dans ces circuits de refroidissement est prélevé au niveau du compresseur haute pression du moteur, de sorte que ce prélèvement d'air dégrade la consommation spécifique du moteur. Il est donc particulièrement intéressant de minimiser ce débit d'air prélevé pour améliorer la consommation spécifique du moteur.  In order to solve this problem, it is therefore known to provide these vanes with internal cooling circuits having high levels of thermal efficiency and aimed at reducing the temperature of the latter by creating, inside the dawn, a circulation organized air (for example by means of simple direct feed cavities or paper clips with upward and downward cavities) and, in the wall of the blade, perforations for generating a protective film for this blade. The air flow used in these cooling circuits is taken from the high-pressure compressor of the engine, so that this air intake degrades the specific consumption of the engine. It is therefore particularly interesting to minimize this air flow taken to improve the specific consumption of the engine.
La figure 4 illustre schématiquement une partie de noyau 10 d'une aube de turbine haute pression de moteur à turbine à gaz comportant une surface aérodynamique ou pale 12 (en tracé fantôme) qui s'étend en direction radiale entre un pied d'aube (non représenté) et un sommet d'aube présentant une partie en forme dite de baignoire 18 constituée d'un fond 18A transversal à la pale et d'une paroi (ou muret 18B) formant son bord dans le prolongement de la paroi de la pale. La pale comprend une pluralité de cavités dont toutefois, pour les besoins de la description, seules quatre cavités latérales le long de la face intrados de l'aube et une cavité dite de « sous-baignoire » disposée en grande partie sous le fond de baignoire 18A sont illustrées par leur partie de noyau respective 22, 24, 26, 28, 30. Le noyau comporte également des premières tiges céramiques 32 - 40 s'étendant depuis les parois latérales (par exemple la paroi latérale 24A de la partie de noyau 24) des parties de noyau et destinées à former des perçages inclinés assurant le refroidissement du muret de baignoire 18B sur la face intrados de l'aube FIG. 4 schematically illustrates a core portion 10 of a gas turbine engine high-pressure turbine blade having an aerodynamic surface or blade 12 (in phantom tracing) which extends in a radial direction between a blade root (not shown) and a blade tip having a shaped part called tub 18 consisting of a bottom 18A transverse to the blade and a wall (or wall 18B ) forming its edge in the extension of the wall of the blade. The blade comprises a plurality of cavities, however, for the purposes of the description, only four lateral cavities along the intrados face of the blade and a so-called "sub-bath" cavity disposed largely under the bottom of the bathtub 18A are illustrated by their respective core portions 22, 24, 26, 28, 30. The core also includes first ceramic rods 32 - 40 extending from the sidewalls (e.g., the sidewall 24A of the core portion 24 ) core portions and intended to form inclined holes for cooling the bath wall 18B on the intrados face of the dawn
Compte tenu de l'environnement dans lequel évoluent les moteurs à turbine à gaz, il est aussi nécessaire de munir les circuits de refroidissement précités de trous de dépoussiérage permettant l'évacuation hors de l'aube de particules ou poussières ingérées par le moteur et transportées dans l'air de refroidissement jusqu'à l'entrée des différentes cavités. Du fait de cette fonction, les trous de dépoussiérage présentent un diamètre nettement supérieur (dans un rapport d'environ 2 à 5) à celui des perçages inclinés de refroidissement. La figure 3 montre quatre de ces trous de dépoussiérage débouchant dans le fond de baignoire 18A et illustrés par des secondes tiges céramiques respectives 42 - 48 s'étendant verticalement depuis le sommet (par exemple le sommet 24B de la partie de noyau 24) des seules parties de noyau 22, 24, 28, 30 formant des cavités montantes. La cavité descendante 26 ne comporte en effet pas de trou de dépoussiérage.  In view of the environment in which gas turbine engines operate, it is also necessary to provide the aforementioned cooling circuits with dust extraction holes allowing the evacuation out of the blade of particles or dust ingested by the engine and transported in the cooling air until the entrance of the different cavities. Because of this function, the dedusting holes have a much larger diameter (in a ratio of about 2 to 5) than that of inclined cooling bores. Figure 3 shows four of these dusting holes opening into the bath bottom 18A and illustrated by respective second ceramic rods 42 - 48 extending vertically from the top (e.g., the top 24B of the core portion 24) of the only core portions 22, 24, 28, 30 forming rising cavities. The downward cavity 26 does not in fact have a dusting hole.
La présence de ces trous de dépoussiérage n'est pas sans conséquence sur la consommation spécifique car le débit d'air de refroidissement évacué par ces trous n'est pas utilisé de la manière la plus efficace possible pour le refroidissement de l'aube. Cependant, il est impossible de les supprimer car alors le risque de créer des zones d'accumulation des poussières au niveau des cavités montantes devient trop important. Et la présence de telles zones d'accumulation de poussières est à l'origine de points chauds sur l'aube, de nature à engendrer des brûlures ou une oxydation locale accélérée de l'aube. Obiet et résumé de l'invention The presence of these dedusting holes is not without consequences on the specific consumption because the flow of cooling air discharged through these holes is not used in the most efficient manner for the cooling of the blade. However, it is impossible to remove them because then the risk of creating areas of accumulation of dust in the rising cavities becomes too important. And the presence of such areas of accumulation of dust is causing hot spots on the dawn, likely to cause burns or accelerated local oxidation of dawn. Obiet and summary of the invention
La présente invention vise donc à pallier les inconvénients précités en proposant une aube de turbine creuse dont le prélèvement d'air de refroidissement est réduit pour améliorer la consommation spécifique du moteur.  The present invention therefore aims to overcome the aforementioned drawbacks by proposing a hollow turbine blade whose cooling air intake is reduced to improve the specific consumption of the engine.
A cet effet, il est prévu une aube de turbine creuse de turbomachine comportant une pluralité de cavités montantes communiquant d'une part avec une baignoire de l'aube par une pluralité de trous de dépoussiérage d'un diamètre standard destinée à l'évacuation de poussières et d'autre part par une pluralité de perçages de refroidissement inclinés destinée à refroidir un muret de ladite baignoire en débouchant sur une face intrados de l'aube, au moins une cavité montante dont un sommet est dépourvue d'un trou de dépoussiérage comprend un perçage de refroidissement incliné pratiqué dans sa paroi latérale et destiné à refroidir ledit muret de baignoire et dont le diamètre est agrandi pour présenter un diamètre au moins égal audit diamètre standard d'un trou de dépoussiérage et faire ainsi aussi office de trou de dépoussiérage, de sorte que le débit d'air prélevé pour le refroidissement de l'aube est réduit, aube caractérisée en ce que l'une au moins des cavités de l'aube disposée en regard dudit sommet de ladite au moins une cavité montante présente un volume augmenté correspondant au moins à un volume soustrait audit sommet de ladite au moins une cavité montante.  For this purpose, there is provided a turbomachine hollow turbine blade having a plurality of rising cavities communicating on the one hand with a bath of the blade by a plurality of dusting holes of a standard diameter for the evacuation of dust and secondly by a plurality of inclined cooling holes for cooling a wall of said tub by opening on an underside face of the blade, at least one rising cavity whose apex is devoid of a dedusting hole comprises an inclined cooling bore formed in its side wall and intended to cool said bath wall and whose diameter is enlarged to have a diameter at least equal to said standard diameter of a dedusting hole and thus also act as a dedusting hole, so that the flow of air taken for the cooling of the blade is reduced, dawn characterized in that at least one cavities of the blade disposed opposite said top of said at least one rising cavity has an increased volume corresponding at least to a volume subtracted from said top of said at least one rising cavity.
Par cette configuration qui optimise la forme et le positionnement d'un trou de dépoussiérage particulier, il est possible de refroidir une aube mobile de turbine haute pression avec un débit de refroidissement moins important mais avec la même efficacité thermique qu'une aube mobile classique. Le débit d'air évacué par les trous de dépoussiérage est ainsi utilisé pour refroidir par effet de film et de pompage le muret de baignoire intrados de l'aube, qui est une zone soumise aux températures élevées de l'air de la veine moteur et donc à de fortes contraintes thermiques.  By this configuration which optimizes the shape and positioning of a particular dusting hole, it is possible to cool a high pressure turbine turbine blade with a lower cooling rate but with the same thermal efficiency as a conventional moving blade. The air flow evacuated through the dust extraction holes is thus used to cool by filming and pumping the vane's lower bath wall, which is an area subjected to the high temperatures of the engine vein air and therefore to strong thermal stresses.
Selon le mode de réalisation envisagé, le perçage de refroidissement incliné ainsi agrandi faisant aussi office de trou de dépoussiérage présente une inclinaison orientée vers la baignoire comprise entre 45 et 75°. According to the embodiment envisaged, the inclined cooling bore thus enlarged also acting as a hole for Dusting has a slope oriented towards the bath between 45 and 75 °.
De préférence, ledit sommet de ladite au moins une cavité montante présente une forme concave, typiquement un plan incliné avec un angle sensiblement égal à celui dudit perçage de refroidissement incliné ou une marche d'escalier permettant d'orienter le flux dans le même sens que ledit perçage de refroidissement incliné.  Preferably, said apex of said at least one rising cavity has a concave shape, typically an inclined plane with an angle substantially equal to that of said inclined cooling bore or a step of stepping to direct the flow in the same direction as said inclined cooling bore.
Avantageusement, ledit perçage de refroidissement incliné ainsi agrandi est disposé au plus près dudit sommet de ladite au moins une cavité montante jusqu'à venir tangenter ledit sommet.  Advantageously, said inclined cooling bore thus enlarged is disposed closer to said apex of said at least one rising cavity until it comes tangent to said vertex.
L'invention concerne également un noyau céramique utilisé pour la fabrication d'une aube de turbine creuse de turbomachine selon la technique de la fonderie à la cire perdue, l'aube comportant une pluralité de cavités montantes communiquant d'une part avec une baignoire de l'aube par une pluralité de trous de dépoussiérage destinée à l'évacuation de poussières et d'autre part par une pluralité de perçages de refroidissement inclinés destinée à refroidir un muret de ladite baignoire en débouchant sur une face intrados de l'aube, le noyau comportant : The invention also relates to a ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost-wax foundry technique, the blade comprising a plurality of rising cavities communicating on the one hand with a bath of the dawn by a plurality of dust extraction holes for the evacuation of dust and secondly by a plurality of inclined cooling holes for cooling a wall of said bathtub opening on an intrados face of the blade, the core comprising:
- une pluralité de parties de noyau destinée à former ladite pluralité de cavités montantes, a plurality of core portions for forming said plurality of upstanding cavities,
- une pluralité de premières tiges céramiques d'un premier diamètre déterminé s'étendant depuis une paroi latérale de ladite pluralité de parties de noyau et destinée à former ladite pluralité de perçages de refroidissement, et  a plurality of first ceramic rods of a determined first diameter extending from a side wall of said plurality of core portions and for forming said plurality of cooling bores, and
- une pluralité de secondes tiges céramiques d'un second diamètre déterminé s'étendant verticalement depuis un sommet de ladite pluralité de parties de noyau et destinée à former ladite pluralité de trous de dépoussiérage, ledit second diamètre déterminé étant supérieur audit premier diamètre déterminé, a plurality of second ceramic rods of a determined second diameter extending vertically from an apex of said plurality of core portions and intended to form said plurality of dusting holes, said determined second diameter being greater than said determined first diameter,
caractérisé en ce qu'une partie de noyau destinée à former une cavité montante de l'aube est dépourvue à son sommet d'une seconde tige céramique destinée à former un trou de dépoussiérage et une première tige céramique destinée à former dans sa paroi latérale un perçage de refroidissement incliné faisant également office de trou de dépoussiérage afin d'assurer le refroidissement dudit muret de baignoire, présente un premier diamètre au moins égal audit second diamètre prédéterminé, et en ce que ladite partie de noyau présente à son sommet un volume soustrait et l'une au moins des autres parties de noyau de ladite pluralité de parties de noyau disposée en regard dudit sommet de ladite partie de noyau présente un volume augmenté correspondant au moins au dit volume soustrait au dit sommet de ladite au moins une cavité montante. characterized in that a core portion for forming a rising cavity of the blade is devoid at its top of a second ceramic rod for forming a dedusting hole and a first ceramic rod for forming in its side wall a inclined cooling bore also serving as a dusting hole for cooling said bath wall, has a first diameter at least equal to said second predetermined diameter, and in that said core portion has a subtracted volume at its apex and at least one of the other core portions of said plurality of core portions disposed opposite said apex of said core portion has an increased volume corresponding at least to said volume subtracted from said top of said at least one rising cavity.
De préférence, ledit volume soustrait au sommet de ladite au moins une cavité montante présente une forme concave, typiquement un plan incliné ou une marche d'escalier dont l'inclinaison correspond à celle de ladite première tige céramique.  Preferably, said subtracted volume at the top of said at least one rising cavity has a concave shape, typically an inclined plane or a stair step whose inclination corresponds to that of said first ceramic rod.
Avantageusement, ladite augmentation de volume est une partie en saillie centrée sur ladite partie de noyau avec une largeur et une hauteur sensiblement égales à celle dudit plan incliné sans toutefois dépasser le sommet de ladite partie de noyau.  Advantageously, said volume increase is a projecting portion centered on said core portion with a width and height substantially equal to that of said inclined plane without exceeding the top of said core portion.
L'invention concerne encore l'utilisation d'un tel noyau céramique pour la fabrication d'une aube de turbine creuse de turbomachine selon la technique de la fonderie à la cire perdue et toute turbine de turbomachine munie de plusieurs aubes de turbine creuses.  The invention also relates to the use of such a ceramic core for the manufacture of a turbomachine hollow turbine blade according to the lost wax foundry technique and any turbomachine turbine provided with a plurality of hollow turbine blades.
Brève description des dessins Brief 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 et sur lesquels :  Other characteristics and advantages of the present invention will emerge from the description given below, with reference to the appended drawings which illustrate an embodiment of this embodiment devoid of any limiting character and in which:
- la figure 1 est une vue en perspective externe d'une aube mobile de turbine haute pression selon l'invention,  FIG. 1 is an external perspective view of a moving blade of a high pressure turbine according to the invention,
- la figure 2 est une vue schématique d'un premier exemple de réalisation d'une partie de noyau de l'aube de turbine de la figure 1,  FIG. 2 is a schematic view of a first exemplary embodiment of a core portion of the turbine blade of FIG. 1,
- la figure 2A est une vue en coupe au niveau d'un perçage incliné de refroidissement et de dépoussiérage,  FIG. 2A is a sectional view at an inclined cooling and dusting hole,
- la figure 3 est une vue schématique d'un second exemple de réalisation d'une partie de noyau de l'aube de turbine de la figure 1, et  FIG. 3 is a schematic view of a second exemplary embodiment of a core portion of the turbine blade of FIG. 1, and
- la figure 4 est une vue schématique d'une partie de noyau d'une aube de turbine de l'art antérieur. Description détaillée d'un mode de réalisation - Figure 4 is a schematic view of a core portion of a turbine blade of the prior art. Detailed description of an embodiment
La figure 1 illustre une aube creuse de turbine haute pression de turbomachine s'étendant classiquement radialement par rapport à un axe de rotation d'une roue mobile sur laquelle cette aube de turbine creuse est destinée à être enchâssée avec une pluralité d'autres.  FIG. 1 illustrates a turbine engine high pressure turbine hollow blade conventionally extending radially with respect to an axis of rotation of a mobile wheel on which this hollow turbine blade is intended to be encased with a plurality of others.
L'aube comprend une pale 12 formant la surface aérodynamique de l'aube, une plateforme 14 supportant cette pale et un pied d'aube 16 portant l'ensemble et assurant son enchâssement au rotor de la roue de turbine (non représenté). La pale 12 comporte comme il est connu un bord d'attaque 12A, un bord de fuite 12B, une face intrados 12C et une face extrados (face cachée sur la figure). Au sommet de l'aube (correspondant à l'extrémité de tête opposée au pied d'aube) est disposée la baignoire 18 constituée du fond 18A transversal à la pale et du muret 18B formant son bord dans le prolongement de la paroi de la pale. L'aube comporte également des perforations (perçages sur les deux faces ou fentes sur le bord de fuite) destinées à générer un film d'air de refroidissement protecteur pour cette aube. Le nombre et la position des perforations sont optimisés pour maximiser le refroidissement dans les zones les plus sensibles à la chaleur des gaz de combustion dans lesquelles ces aubes sont plongées et notamment pour sa face intrados 12C qui subit les plus fortes contraintes thermiques.  The blade comprises a blade 12 forming the aerodynamic surface of the blade, a platform 14 supporting the blade and a blade root 16 carrying the assembly and ensuring its entrenchment to the rotor of the turbine wheel (not shown). The blade 12 comprises, as is known, a leading edge 12A, a trailing edge 12B, an intrados face 12C and an extrados face (face hidden in the figure). At the top of the blade (corresponding to the head end opposite the blade root) is disposed the bath 18 consisting of the bottom 18A transverse to the blade and the wall 18B forming its edge in the extension of the wall of the blade . The blade also has perforations (holes on both sides or slots on the trailing edge) for generating a protective cooling air film for this blade. The number and the position of the perforations are optimized to maximize the cooling in the most heat-sensitive areas of the combustion gases in which these vanes are immersed and in particular for its intrados face 12C which undergoes the highest thermal stresses.
Pour ne pas surcharger la figure et assurer une meilleure compréhension de l'invention, seules les perforations en rapport avec l'invention ont été représentées, à savoir les perçages inclinés 20A à 20D assurant le refroidissement du muret de baignoire 18B en débouchant sur la face intrados 12C de l'aube et les trous de dépoussiérage 21A à 21C permettant l'évacuation des poussières.  In order not to overload the figure and to ensure a better understanding of the invention, only the perforations in connection with the invention have been represented, namely the inclined bores 20A to 20D ensuring the cooling of the tub wall 18B by opening on the face 12C intrados of the blade and 21A 21C dust removal holes for the evacuation of dust.
La figure 2 représente une partie d'un noyau céramique 10 destiné à la réalisation de l'aube mobile de la figure 1. Ce noyau ne montre en effet, dans l'exemple illustré, que cinq parties de noyau ou colonnes pouvant être montantes ou descendantes. La première colonne montante 22 est par exemple destinée à former, une fois l'aube achevée, une cavité latérale de l'aube (référencée 23 sur la figure 1) recevant un premier flux d'air de refroidissement amené par une première canalisation alors que les trois autres colonnes adjacentes faisant un aller-retour sur la face intrados (avec deux colonnes montantes 24, 28 et une, au centre, descendante 26) sont destinées à former des cavités latérales de l'aube (référencées respectivement 25, 29 et 27 sur la figure 1) qui peuvent recevoir un second flux d'air de refroidissement amené par une autre canalisation par exemple. La dernière partie de noyau 30 est destinée à former une cavité dite de « sous-baignoire » (référencée 31 sur la figure 1) disposée en grande partie sous le fond de baignoire 18A. FIG. 2 shows a portion of a ceramic core 10 intended for producing the moving blade of FIG. 1. This core does indeed show, in the illustrated example, only five core portions or columns that can be rising or down. The first riser 22 is for example intended to form, once the blade has been completed, a lateral cavity of the blade (referenced 23 in FIG. 1) receiving a first flow of cooling air brought by a first pipe while the other three adjacent columns going back and forth on the intrados face (with two risers 24, 28 and one, in the center, 26) are intended to form lateral cavities of the blade (referenced respectively 25, 29 and 27 in Figure 1) which can receive a second flow of cooling air supplied by another pipe for example. The last core portion 30 is intended to form a cavity called "sub-bath" (referenced 31 in Figure 1) disposed largely under the bath floor 18A.
Le noyau comporte également les premières tiges céramiques 32, 36, 38, 40 s'étendant depuis une paroi latérale (par exemple 24A) des colonnes montantes et destinées à former les perçages inclinés assurant le refroidissement du muret de baignoire 18B sur la face intrados de l'aube et les tiges secondes céramiques 42, 46, 48 s'étendant verticalement depuis le sommet (par exemple 24B) de ces colonnes montantes et destinées à former les trous de dépoussiérage permettant l'évacuation dans la baignoire des poussières traversant avec l'air de refroidissement les cavités montantes 23, 29, 31 formées à partir de ces colonnes.  The core also comprises the first ceramic rods 32, 36, 38, 40 extending from a side wall (for example 24A) of the risers and intended to form the inclined bores for cooling the bath wall 18B on the lower face of the bath. the dawn and the second ceramic rods 42, 46, 48 extending vertically from the top (for example 24B) of these risers and intended to form the dedusting holes for the evacuation into the bath of the dust passing through with the cooling air the rising cavities 23, 29, 31 formed from these columns.
Un tel noyau céramique multi-cavités comporte bien entendu d'autres parties de noyau destinées à former d'autres cavités non représentées comme une cavité située dans la partie de l'aube près du bord d'attaque 12A et une ou plusieurs cavités se succédant en ligne dans la partie de l'aube près du bord de fuite 12B, toutes permettant l'acheminement de l'air de refroidissement depuis le pied d'aube 16 vers des parties d'aube associées à refroidir. Les tiges céramiques permettent quant à elles de créer les perçages inclinés par lequel cet air passe pour atteindre la paroi de la pale ou évacuer les poussières pour celles destinées à former les trous de dépoussiérage. Les colonnes sont séparées les unes des autres par des espacements déterminés laissant ainsi la place pour la création d'une paroi inter-cavités pleine lors de la coulée du métal fondu.  Such a multi-cavity ceramic core naturally includes other core portions intended to form other cavities, not shown, such as a cavity situated in the part of the blade near the leading edge 12A and one or more successive cavities. in line in the portion of the blade near the trailing edge 12B, all allowing the routing of the cooling air from the blade root 16 to parts of the blade associated with cooling. The ceramic rods make it possible to create the inclined holes through which this air passes to reach the wall of the blade or to remove dust for those intended to form the dusting holes. The columns are separated from each other by determined spacings thus leaving room for the creation of a full inter-cavity wall during the casting of the molten metal.
Conformément à l'invention, au moins l'une des cavités montantes est dépourvue à son sommet d'un trou de dépoussiérage et le perçage de refroidissement incliné (avec une inclinaison orientée vers la baignoire de l'ordre de 45 à 75°), pratiqué dans sa paroi latérale près du sommet de cette cavité et destiné normalement à refroidir le muret de baignoire en débouchant sur la face intrados de l'aube, est agrandi dans un rapport de 2 à 5 pour faire également office de trou de dépoussiérage, de sorte que le débit d'air prélevé pour le refroidissement est ainsi réduit. Dans un mode de réalisation préférentiel de l'invention illustré à la figure 2, la cavité dépourvue de trou de dépoussiérage est la cavité montante 25. Cependant, les autres cavités montantes 23 et 29 peuvent elles aussi être dépourvues de trou de dépoussiérage dans la mesure où ces cavités montantes sont positionnées à côté de la cavité de sous- baignoire 31 (par exemple la figure 3 avec les cavités 23 et 25). According to the invention, at least one of the rising cavities is devoid of a dedusting hole at its top and the inclined cooling bore (with an inclination oriented towards the bath of the order of 45 to 75 °), made in its side wall near the top of this cavity and normally intended to cool the bath wall opening on the underside of the blade, is enlarged in a ratio of 2 to 5 to also act as a dust removal hole, so that the air flow taken for cooling is reduced. In a preferred embodiment of the invention illustrated in FIG. 2, the cavity devoid of dusting hole is the rising cavity 25. However, the other rising cavities 23 and 29 can also be devoid of dust extraction holes in the measurement where these rising cavities are positioned adjacent the under-bath cavity 31 (for example, Figure 3 with cavities 23 and 25).
En effet, le diamètre de ce perçage de refroidissement et de dépoussiérage 51 (correspondant à une tige céramique 50) doit être bien supérieur au diamètre d'un perçage de refroidissement standard qui, comme il a été indiqué précédemment est classiquement nettement inférieur, afin d'assurer, outre le refroidissement, la bonne évacuation des poussières circulant dans l'air de refroidissement interne. Comme illustré et pour assurer un dépoussiérage efficace, ce perçage est disposé au plus près du sommet fermé de la cavité montante, jusqu'à venir quasiment tangenter ce sommet, et peut éventuellement être rapproché du muret de baignoire 18B. De préférence, le diamètre du perçage incliné de refroidissement et de dépoussiérage est choisi au moins égal au diamètre d'un trou de dépoussiérage standard.  Indeed, the diameter of this cooling and dedusting bore 51 (corresponding to a ceramic rod 50) must be much greater than the diameter of a standard cooling bore which, as previously indicated, is conventionally much lower, in order to in addition to cooling, ensure good evacuation of the dust circulating in the internal cooling air. As illustrated and to ensure effective dedusting, this hole is disposed closer to the closed top of the rising cavity, until almost tangent this summit, and may possibly be close to the bath wall 18B. Preferably, the diameter of the inclined cooling and dedusting bore is chosen at least equal to the diameter of a standard dedusting hole.
Toutefois, pour assurer correctement le dépoussiérage de la cavité à l'aide de ce perçage incliné, il est nécessaire d'incliner le sommet de la cavité montante avec un angle sensiblement identique à celui de ce perçage incliné (c'est-à-dire à plus ou moins 5° près). L'inclinaison du sommet de la cavité montante permet ainsi de guider les poussières résiduelles vers le perçage incliné et d'éviter la formation de zones d'accumulation de particules au sommet de cette cavité. En pratique, cette inclinaison du sommet de la cavité montante peut prendre toute forme concave comme une marche d'escalier, permettant d'orienter le flux dans le même sens que le perçage incliné. Cependant, la création d'un plan incliné en sommet de cavité en soustrayant un volume de noyau entraine une augmentation locale de quantité de matière correspondante en haut de pale par rapport à une configuration standard telle qu'illustrée à la figure 4, laquelle est défavorable pour la tenue mécanique de l'aube car de nature à engendrer un phénomène de fluage.  However, to ensure proper dust removal of the cavity using this inclined bore, it is necessary to tilt the top of the rising cavity with an angle substantially identical to that of this inclined bore (that is to say to plus or minus 5 °). The inclination of the top of the rising cavity thus makes it possible to guide the residual dust towards the inclined drilling and to avoid the formation of zones of accumulation of particles at the top of this cavity. In practice, this inclination of the top of the rising cavity can take any concave shape like a stair step, to direct the flow in the same direction as the inclined drilling. However, the creation of an inclined plane at the vertex of the cavity by subtracting a core volume causes a local increase in corresponding quantity of material at the top of the blade compared to a standard configuration as illustrated in FIG. 4, which is unfavorable. for the mechanical strength of the dawn because of nature to generate a phenomenon of creep.
Aussi, afin de ne pas dégrader la durée de vie mécanique de l'aube, il est nécessaire de corriger cette augmentation locale de quantité de matière dû à la réduction de la partie haute de la colonne 24 par l'adjonction d'une extension de noyau 52 disposée le plus proche possible de la cavité montante avec le plan incliné et générant une augmentation du volume de la partie de noyau de sous-baignoire 30 située en regard du plan incliné réalisé au sommet 24A de la colonne montante 24. Also, in order not to degrade the mechanical life of the blade, it is necessary to correct this local increase in quantity of material due to the reduction of the upper part of the column 24 by the addition of a core extension 52 disposed as close as possible to the rising cavity with the inclined plane and generating an increase in the volume of the sub-bath core portion 30 facing the inclined plane made at the top 24A of the riser 24.
Comme le montrent les figures 2 et 2A, cette augmentation de volume de la partie de noyau de sous-baignoire 30 est sensiblement égale (c'est-à-dire à plus ou moins 10%) au volume issu de l'introduction du plan incliné en sommet de la colonne montante 24 et est de préférence une partie en saillie centrée sur la colonne montante avec une largeur et une hauteur sensiblement égales à celles du plan incliné (c'est-à-dire à plus ou moins 10%), le niveau haut de cette extension de noyau 52 ne dépassant pas celui de ce plan incliné, pour assurer un comportement mécanique similaire à la configuration initiale.  As shown in FIGS. 2 and 2A, this increase in volume of the sub-bath core portion 30 is substantially equal (i.e., plus or minus 10%) to the volume resulting from the introduction of the plan. inclined at the top of the riser 24 and is preferably a projecting portion centered on the riser with a width and height substantially equal to those of the inclined plane (that is to say plus or minus 10%), the high level of this core extension 52 not exceeding that of this inclined plane, to ensure mechanical behavior similar to the initial configuration.
La figure 3 illustre un autre mode de réalisation de l'invention dans lequel, non pas une mais deux cavités montantes 23 et 25, sont pourvus de perçages de refroidissement et de dépoussiérage correspondant à des tiges céramiques 50 et 54 des colonnes 22 et 24. Comme dans le mode de réalisation préférentiel, ces deux perçages sont disposés au plus près du sommet des deux cavités montantes. Le diamètre de ces perçages inclinés de refroidissement et de dépoussiérage est choisi au moins égal au diamètre d'un trou de dépoussiérage standard auxquels ils se substituent. Pareillement, le sommet de chacune des deux cavités montantes 23, 25 présente un angle sensiblement identique à celui des perçages inclinés, c'est-à-dire de l'ordre de 45 à 75°. Comme précédemment, il est nécessaire de corriger l'augmentation locale de quantité de matière dû à la réduction de la partie haute des colonnes 22 et 24 par l'adjonction d'une extension de noyau 52 disposée le plus proche possible de ces cavités montantes à plans inclinés et dont le volume est sensiblement égal au volume issu de l'introduction des deux plans inclinés en sommet des colonnes montantes 22 et 24. Cette extension de noyau est de préférence une partie en saillie s'étendant sur les deux colonnes montantes avec une hauteur sensiblement égale à celle des plans inclinés, le niveau haut de cette extension de noyau ne dépassant pas celui de ces plans inclinés.  FIG. 3 illustrates another embodiment of the invention in which, not one but two rising cavities 23 and 25, are provided with cooling and dedusting holes corresponding to ceramic rods 50 and 54 of the columns 22 and 24. As in the preferred embodiment, these two holes are arranged closer to the top of the two rising cavities. The diameter of these inclined cooling and dedusting holes is chosen at least equal to the diameter of a standard dedusting hole to which they replace. Similarly, the apex of each of the two rising cavities 23, 25 has an angle substantially identical to that of the inclined bores, that is to say of the order of 45 to 75 °. As previously, it is necessary to correct the local increase in quantity of material due to the reduction of the upper part of the columns 22 and 24 by the addition of a core extension 52 disposed as close as possible to these rising cavities. inclined planes and whose volume is substantially equal to the volume from the introduction of the two inclined planes at the top of the risers 22 and 24. This core extension is preferably a projecting portion extending on the two risers with a height substantially equal to that of the inclined planes, the high level of this core extension not exceeding that of these inclined planes.
Avec l'invention, le transfert thermique conducto-convectif qui s'effectue dans le perçage entre l'air de refroidissement et les parois métalliques environnantes assure un refroidissement par effet de pompage de la zone en sommet d'aube en général et du muret de baignoire intrados en particulier. L'abaissement local de la température de l'air dans la veine et l'augmentation du coefficient d'échange thermique, proche de la paroi dans les zones situées juste en aval des perçages, sous l'effet de l'émission d'air de refroidissement par les perçages, assure un refroidissement par effet de film, au contraire d'un trou de dépoussiérage classique où compte-tenu de l'angle d'émission de l'air de refroidissement par rapport à la paroi de l'aube, seul l'effet de pompage contribue au refroidissement de la zone en sommet d'aube. With the invention, the conducto-convective thermal transfer which takes place in the bore between the cooling air and the walls surrounding metal provides cooling by pumping effect of the area at the top of the blade in general and the lower wall of intrados bathtub in particular. The local lowering of the air temperature in the vein and the increase of the heat exchange coefficient, close to the wall in the zones just downstream of the bores, under the effect of the emission of air cooling by the holes, provides cooling by film effect, unlike a conventional dust extraction hole where given the angle of emission of the cooling air relative to the wall of the blade, only the pumping effect contributes to the cooling of the area at the top of the blade.
On notera que l'inclinaison des trous de refroidissement et de dépoussiérage doit être suffisante (de préférence supérieure à 45°) pour profiter du refroidissement par effet de film sans toutefois l'être trop (de préférence inférieure à 75°) pour des raisons de fabrication selon la technique de la fonderie à la cire perdue.  It should be noted that the inclination of the cooling and dedusting holes must be sufficient (preferably greater than 45 °) to take advantage of the cooling by film effect without being too much (preferably less than 75 °) for reasons of Manufacture according to the technique of foundry with lost wax.

Claims

REVENDICATIONS
1. Aube de turbine creuse de turbomachine comportant une pluralité de cavités montantes (23, 25, 29, 31) communiquant d'une part avec une baignoire (18) de l'aube par une pluralité de trous de dépoussiérage d'un diamètre standard (21A, 21B, 21C) destinée à l'évacuation de poussières et d'autre part par une pluralité de perçages de refroidissement inclinés (20A, 20B, 20C, 20D) destinée à refroidir un muret (18B) de ladite baignoire en débouchant sur une face intrados (12C) de l'aube, au moins une cavité montante (25) dont un sommet (22B, 24B) est dépourvu d'un trou de dépoussiérage comprend un perçage de refroidissement incliné pratiqué dans sa paroi latérale et destiné à refroidir ledit muret de baignoire et dont le diamètre est agrandi pour présenter un diamètre au moins égal audit diamètre standard d'un trou de dépoussiérage et faire ainsi aussi office de trou de dépoussiérage (51), de sorte que le débit d'air prélevé pour le refroidissement de l'aube est réduit, aube caractérisée en ce que l'une au moins des cavités de l'aube disposée en regard dudit sommet de ladite au moins une cavité montante présente un volume augmenté correspondant au moins à un volume soustrait au dit sommet de ladite au moins une cavité montante. A turbomachine hollow turbine blade having a plurality of upstanding cavities (23, 25, 29, 31) communicating on the one hand with a bath (18) of the blade by a plurality of dusting holes of a standard diameter (21A, 21B, 21C) for the evacuation of dust and secondly by a plurality of inclined cooling holes (20A, 20B, 20C, 20D) for cooling a wall (18B) of said bath, opening on a lower face (12C) of the vane, at least one rising cavity (25) whose apex (22B, 24B) is devoid of a dedusting hole comprises an inclined cooling bore formed in its side wall and intended to cool said bath wall and whose diameter is enlarged to have a diameter at least equal to said standard diameter of a dedusting hole and thus also act as a dedusting hole (51), so that the air flow taken for the cooling of the blade is reduced, blade characterized in that at least one of the cavities of the blade disposed opposite said top of said at least one rising cavity has an increased volume corresponding at least to a volume subtracted from said top of said less a rising cavity.
2. Aube de turbine creuse selon la revendication 1, caractérisée en ce que le perçage de refroidissement incliné ainsi agrandi faisant aussi office de trou de dépoussiérage présente une inclinaison orientée vers la baignoire (18) comprise entre 45 et 75°. 2. hollow turbine blade according to claim 1, characterized in that the inclined cooling bore thus enlarged also serving as dust removal hole has a slope oriented towards the bath (18) between 45 and 75 °.
3. Aube de turbine creuse selon la revendication 1, caractérisé en ce que ledit sommet de ladite au moins une cavité montante présente une forme concave, typiquement un plan incliné avec un angle sensiblement égal à celui dudit perçage de refroidissement incliné. 3. hollow turbine blade according to claim 1, characterized in that said apex of said at least one rising cavity has a concave shape, typically an inclined plane with an angle substantially equal to that of said inclined cooling bore.
4. Aube de turbine creuse selon la revendication 1, caractérisée en ce que ledit sommet de ladite au moins une cavité montante présente une forme concave, typiquement une marche d'escalier, permettant d'orienter le flux dans le même sens que ledit perçage de refroidissement incliné. 4. hollow turbine blade according to claim 1, characterized in that said apex of said at least one rising cavity has a concave shape, typically a stair step, for directing the flow in the same direction as said drilling of inclined cooling.
5. Aube de turbine creuse selon l'une quelconque des revendications 1 à 4, caractérisée en ce que ledit perçage de refroidissement incliné ainsi agrandi est disposé au plus près dudit sommet de ladite au moins une cavité montante jusqu'à venir tangenter ledit sommet. 5. A hollow turbine blade according to any one of claims 1 to 4, characterized in that said inclined cooling bore thus enlarged is disposed closer to said top of said at least one rising cavity to come tangent said summit.
6. Turbomachine comportant une pluralité d'aubes de turbine creuses selon l'une quelconque des revendications 1 à 5. 6. A turbomachine comprising a plurality of hollow turbine blades according to any one of claims 1 to 5.
7. Noyau céramique utilisé pour la fabrication d'une aube de turbine creuse de turbomachine selon la technique de la fonderie à la cire perdue, l'aube comportant une pluralité de cavités montantes (23, 29, 31) communiquant d'une part avec une baignoire (18) de l'aube par une pluralité de trous de dépoussiérage (21A, 21B, 21C) destinée à l'évacuation de poussières et d'autre part par une pluralité de perçages de refroidissement inclinés (20A, 20B, 20C, 20D) destinée à refroidir un muret (18B) de ladite baignoire en débouchant sur une face intrados (12C) de l'aube, le noyau comportant : 7. Ceramic core used for the manufacture of a turbomachine hollow turbine blade according to the lost-wax foundry technique, the blade comprising a plurality of upstanding cavities (23, 29, 31) communicating on the one hand with a bath (18) of the blade by a plurality of dust extraction holes (21A, 21B, 21C) for dust removal and secondly by a plurality of inclined cooling bores (20A, 20B, 20C, 20D) intended to cool a wall (18B) of said tub by opening on an intrados face (12C) of the blade, the core comprising:
- une pluralité de parties de noyau (22, 24, 28, 30) destinée à former ladite pluralité de cavités montantes, a plurality of core portions (22, 24, 28, 30) for forming said plurality of upstanding cavities,
- une pluralité de premières tiges céramiques (32, 36, 38, 40) d'un premier diamètre déterminé s'étendant depuis une paroi latérale (24A) de ladite pluralité de parties de noyau et destinée à former ladite pluralité de perçages de refroidissement, et  a plurality of first ceramic rods (32, 36, 38, 40) of a first determined diameter extending from a side wall (24A) of said plurality of core portions and for forming said plurality of cooling bores, and
- une pluralité de secondes tiges céramiques (42, 46, 48) d'un second diamètre déterminé s'étendant verticalement depuis un sommet (22B, 24B) de ladite pluralité de parties de noyau et destinée à former ladite pluralité de trous de dépoussiérage, ledit second diamètre déterminé étant supérieur audit premier diamètre déterminé,  a plurality of second ceramic rods (42, 46, 48) of a second determined diameter extending vertically from a vertex (22B, 24B) of said plurality of core portions and for forming said plurality of dusting holes, said determined second diameter being greater than said determined first diameter,
caractérisé en ce qu'une partie de noyau (24) destinée à former une cavité montante (25) de l'aube est dépourvue à son sommet (22B, 24B) d'une seconde tige céramique destinée à former un trou de dépoussiérage et une première tige céramique (50) destinée à former dans sa paroi latérale (24A) un perçage de refroidissement incliné faisant également office de trou de dépoussiérage afin d'assurer le refroidissement dudit muret de baignoire, présente un premier diamètre au moins égal audit second diamètre prédéterminé, et en ce que ladite partie de noyau (24) présente à son sommet (24B) un volume soustrait et l'une au moins (30) des autres parties de noyau de ladite pluralité de parties de noyau disposée en regard dudit sommet de ladite partie de noyau présente un volume augmenté (52) correspondant au moins au dit volume soustrait au dit sommet de ladite au moins une cavité montante. characterized in that a core portion (24) for forming a rising cavity (25) of the blade is free at its top (22B, 24B) of a second ceramic rod for forming a dusting hole and a first ceramic rod (50) intended to form in its side wall (24A) an inclined cooling bore also serving as a dusting hole to ensure the cooling of said tub wall, has a first diameter at least equal to said second predetermined diameter, and in that said core portion (24) has at its top (24B) a subtracted volume and at least one (30) of the other parts of core of said plurality of core portions disposed opposite said apex of said core portion has an increased volume (52) corresponding at least to said volume subtracted from said at least one upstanding cavity.
8. Noyau céramique selon la revendication 7, caractérisé en ce que ledit volume soustrait au sommet de ladite au moins une cavité montante présente une forme concave, typiquement un plan incliné ou une marche d'escalier dont l'inclinaison correspond à celle de ladite première tige céramique. 8. Ceramic core according to claim 7, characterized in that said volume subtracted from the top of said at least one rising cavity has a concave shape, typically an inclined plane or a stair step whose inclination corresponds to that of said first ceramic rod.
9. Noyau céramique selon la revendication 7 ou la revendicationCeramic core according to claim 7 or claim
8, caractérisé en ce que ladite augmentation de volume (52) est une partie en saillie centrée sur ladite partie de noyau (24) ayant une largeur et une hauteur sensiblement égales à celles dudit plan incliné sans toutefois dépasser le sommet de ladite partie de noyau (24). 8, characterized in that said volume increase (52) is a projecting portion centered on said core portion (24) having a width and height substantially equal to those of said inclined plane without, however, exceeding the apex of said core portion (24).
10. Utilisation d'un noyau céramique selon l'une quelconque des revendications 7 à 9 pour la fabrication d'une aube de turbine creuse de turbomachine selon la technique de la fonderie à la cire perdue. 10. Use of a ceramic core according to any one of claims 7 to 9 for the manufacture of a turbomachine hollow turbine blade according to the lost-wax casting technique.
EP18799584.0A 2017-10-17 2018-10-11 Hollow turbine blade with reduced cooling air consumption Active EP3697552B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1759722A FR3072415B1 (en) 2017-10-17 2017-10-17 HOLLOW TURBINE BLADE WITH REDUCED COOLING AIR INTAKE
PCT/FR2018/052536 WO2019077237A1 (en) 2017-10-17 2018-10-11 Hollow turbine blade with reduced intake of cooling air

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US10787932B2 (en) * 2018-07-13 2020-09-29 Honeywell International Inc. Turbine blade with dust tolerant cooling system
FR3095834B1 (en) * 2019-05-09 2021-06-04 Safran Improved cooling turbine engine blade
US11053803B2 (en) * 2019-06-26 2021-07-06 Raytheon Technologies Corporation Airfoils and core assemblies for gas turbine engines and methods of manufacture
US11041395B2 (en) 2019-06-26 2021-06-22 Raytheon Technologies Corporation Airfoils and core assemblies for gas turbine engines and methods of manufacture
US11773726B2 (en) 2019-10-16 2023-10-03 Rtx Corporation Angled tip rods
US11143035B2 (en) * 2019-10-16 2021-10-12 Raytheon Technologies Corporation Angled tip rods
US11913353B2 (en) 2021-08-06 2024-02-27 Rtx Corporation Airfoil tip arrangement for gas turbine engine
FR3130881B1 (en) * 2021-12-20 2024-02-02 Safran Aircraft Engines Vane comprising a dust removal hole comprising an extended inlet portion
FR3137316A1 (en) * 2022-06-29 2024-01-05 Safran Aircraft Engines Ceramic core for hollow turbine blade with external holes

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EP3697552B1 (en) 2021-09-01
WO2019077237A1 (en) 2019-04-25
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FR3072415A1 (en) 2019-04-19
FR3072415B1 (en) 2020-11-06
CN111163877A (en) 2020-05-15
US20210187594A1 (en) 2021-06-24

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