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EP3473808B1 - Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale - Google Patents

Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale Download PDF

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Publication number
EP3473808B1
EP3473808B1 EP17197244.1A EP17197244A EP3473808B1 EP 3473808 B1 EP3473808 B1 EP 3473808B1 EP 17197244 A EP17197244 A EP 17197244A EP 3473808 B1 EP3473808 B1 EP 3473808B1
Authority
EP
European Patent Office
Prior art keywords
rib
tip
cooling hole
blade airfoil
cooling
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.)
Active
Application number
EP17197244.1A
Other languages
German (de)
English (en)
Other versions
EP3473808A1 (fr
Inventor
Tobias Buchal
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.)
Siemens Energy Global GmbH and Co KG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP17197244.1A priority Critical patent/EP3473808B1/fr
Priority to US16/145,792 priority patent/US10746027B2/en
Publication of EP3473808A1 publication Critical patent/EP3473808A1/fr
Application granted granted Critical
Publication of EP3473808B1 publication Critical patent/EP3473808B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • 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
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/24—Rotors for turbines
    • 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

Definitions

  • the invention relates to an airfoil for an internally cooled turbine blade according to the preamble of claim 1.
  • the invention further relates to a method for producing an airfoil.
  • Turbine blades and their airfoils have long been known from the extensive state of the art.
  • the turbine blades can withstand the high temperatures that occur during operation, they are designed to be coolable.
  • they have a cavity inside, through which a coolant, usually cooling air, can flow during operation.
  • a coolant usually cooling air
  • the cooling air heated up when flowing through is blown out and mixed into the working fluid of the gas turbine. If the cooling fluid is cooling air, it is taken from the compressor belonging to the gas turbine.
  • the compressor air can still contain dust and dirt particles which can accumulate in the compressor when it flows through and also when it flows through the turbine blade.
  • specially shaped inlets for cooling air openings can also be used.
  • an ovalization of the inlet area of the cooling air hole means that a particle carried along cannot penetrate into the hole.
  • film cooling holes with a diffuser-like opening can also be arranged between the contact edges in the tip base in such a way that a cooling film can form over the inner sides of the contact edge.
  • these film cooling holes have comparatively small inflow cross sections, they can tend to become blocked if dust particles are carried in the cooling air.
  • conventional cooling air holes can also lead the cooling air to the brushing edge.
  • the object of the invention is therefore to provide a blade for an internally cooled turbine blade, the cooling holes of which have a lower tendency to contaminate particles carried in the cooling air.
  • Another object of the invention is to provide a method by means of which the inventive blades can be produced simply and with greater reliability than before.
  • this first-mentioned object is achieved by an airfoil according to claim 1 and the second-mentioned object by a manufacturing method according to claim 11.
  • the present invention proposes that in the case of an airfoil for an internally cooled turbine blade, comprising a suction side wall and a pressure side wall, a cavity extending at least from a common front edge to a common rear edge and in a span direction from a foot end to a head end partially enclose, the head end comprising a tip wall delimiting the cavity on the head side, in which at least one cooling hole, preferably a plurality of cooling holes is provided for discharging cooling fluid which can flow inside, in the cavity at least one extending from the tip wall in the direction of the foot side End-extending rib, preferably a plurality of such ribs, protrudes from the inner surface of the suction-side wall surrounding this rib or from the inner surface of the pressure-side wall surrounding this rib, and that one - with respect to the ku hlfluid - inflow opening of the at least one cooling hole in the rib in question opens laterally.
  • the invention is based on the knowledge that the lateral arrangement of the inflow opening of the cooling hole in one rib protruding from the inner surface of the side wall significantly impedes the inflow of particles carried in the cooling air. Due to the difficult inflow of particles into the cooling hole, the risk of clogging is reduced, which can increase the service life of the airfoil and a turbine blade equipped with it.
  • the lateral arrangement of the inflow opening in the rib in the case of straight cooling holes can preferably be realized if a channel axis of the cooling hole is arranged at an incline with respect to the longitudinal direction of the rib between the head-side and foot-side ends. It is irrelevant whether the cooling hole or the rib is strictly radial.
  • the lateral arrangement can be realized if the cooling hole along its channel axis is not straight, but curved. It is then sufficient if the cooling hole in the region of the inflow opening - ie immediately downstream thereof - is inclined with respect to the local longitudinal extent of the rib.
  • Such curved cooling holes can easily be produced by eroding.
  • the orientation of the rib is of minor relevance. In both cases, a grinding or oblique cut results with the formation of an elliptical inflow opening.
  • the inflow opening particularly preferably has an elliptical shape with a smaller axis and a larger axis, the smaller axis being smaller than the diameter of the remaining cooling hole.
  • Such an inflow opening can be produced in the airfoil or in the turbine blade by eroding or by laser drilling. Due to the further reduced size of the inflow opening, particles which are very similar or larger to the diameter of the remaining cooling hole do not get into the cooling hole. Only those get into it that are so small that they are discharged again with the cooling fluid without adhering to them. This reduces the risk of the cooling hole becoming blocked.
  • the rib in question has a curved contour in a cross-sectional plane normal to the span direction, with a - in relation to the remaining inner surface - maximum rib height H, the inflow-side end of the cooling hole in question being arranged to the side of the location of the maximum rib height .
  • the rib can also have an angular, for example triangular or rectangular, contour instead of the curved contour.
  • a contour for the inflow opening can be achieved by drilling the cooling hole, which contour resembles an employed ellipse.
  • the longer axis of the ellipse is arranged parallel or at an acute angle to the inner surface of the side wall in question, but in the surface of the rib.
  • a comparatively narrow inlet slot can be provided to achieve a comparatively large inflow cross section, the shorter axis of which is chosen to be smaller than the diameter of particles typically carried in the cooling air. The risk of constipation can therefore be reduced.
  • the rib in question is further preferably inclined from its head-side end to its foot-side end in the direction of the front edge or in the direction of the rear edge.
  • the rib in question preferably extends in a straight line from its head-side end to its foot-side end, the longitudinal extension of the rib has an angle greater than 0 °, for example 25 °, with respect to the span direction. Due to the inclined or inclined arrangement, the problem of the exact axial positioning of the cooling hole to be drilled with respect to the rib can be reduced in particular. If there is an axial misalignment of the rib due to manufacturing-related casting tolerances, then lengthen or the length of the drilled cooling hole to be grasped is shortened.
  • the cavity adjoining the rib in question is such that its essential coolant supply is arranged on that side of the rib in question which faces away from the surface of the rib which has the inflow-side end of the cooling hole.
  • the relevant partial cavity of the airfoil, in which the relevant rib is arranged is supplied with coolant at a specific position.
  • the rib in question is located downstream of this specific position of the coolant supply, the upstream end of the cooling hole being arranged on the side of the rib which is opposite the incoming cooling air flow; the inflow opening is arranged in the lee of the rib in question.
  • At least one sealing tip is arranged on the outwardly facing surface of the tip wall, with the one in question being further preferred Cooling hole extends at least partially, preferably completely, through said sealing tip.
  • sealing tips can be provided which, despite their comparatively small wall thickness, can be internally cooled.
  • the wall thicknesses of such sealing tips can have a size of approximately 2 mm, the cooling holes being able to have a diameter of 1.0 mm and smaller.
  • the following goals are achieved with the invention:
  • the cooling hole By producing the cooling hole by means of laser drilling or eroding, the projected diameter of the cooling hole in the inflow region can also be kept smaller than downstream of it or in the outlet region. In this way, the length of the shorter axis of the ellipse can be reduced compared to the diameter of a round cooling hole.
  • pairs of rib and cooling hole according to the invention can be applied to both side walls of the airfoil. It is also a matter of course to manufacture such blades or turbine blades by means of additive processes, for example selective laser melting or the like.
  • FIG. 1 shows a turbine blade 10 in a perspective view.
  • the turbine blade 10 is in accordance with Figure 1 designed as a moving blade. It comprises a fir-tree-shaped blade root 12 and a platform 14 arranged thereon.
  • the airfoil 16 comprises a suction side wall 22 and a pressure side wall 24. Relative to a hot gas flowing around the airfoil 16, these walls extend from a front edge 18 to a rear edge 20.
  • a plurality of openings 28 for blowing out coolant are provided, which are separated from one another by webs 30 arranged therebetween.
  • the airfoil 16 extends along a span direction, which coincides with a radial direction of a turbine, from a foot-side end 26 to a head-side end 27.
  • the latter is also known as the blade tip.
  • the span direction coincides with the radial direction R of the gas turbine.
  • Figure 2 shows a sectional view through the airfoil 16 according to the section line II - II as the first embodiment of an airfoil 16 according to the invention
  • Figure 2 only the radially outer end of the airfoil 16 with respect to the span or radial direction R of the gas turbine, ie the airfoil tip, is shown.
  • the airfoil 1 Installed in a gas turbine, the airfoil 1 extends in the radial direction R.
  • Further axes of the gas turbine are denoted by A and U, where A stands for the axial direction and U represents the circumferential direction. These are used below, if necessary, to describe the arrangement more easily.
  • the airfoil 16 has a tip wall 34 at the head-side end 27, which delimits a cavity 32 towards the outside.
  • the tip wall 34 is essentially at a right angle to the suction side wall 22 and merges into it.
  • a rib 38 is arranged on an inner surface 40 of the suction side wall 22 facing the cavity 32.
  • the rib 38 extends in a straight line from its end 46 arranged on the head side to its end 44 arranged on the foot side.
  • a further rib 39 extending in the axial direction is provided radially inward at a distance from the rib 38 in order to deflect particles in the event of a radially occurring cooling flow.
  • a sealing tip 48 is also arranged on the radially outward-facing surface 52 of the tip wall 34 and is part of this.
  • Such sealing tips also known as “squealer tips” in English, are usually perceived as radial extensions of the side walls 22, 24 of the turbine blade 10. They serve to reduce a gap between the blade tip and the hot gas path limitation of the gas turbine opposite this.
  • the sealing tips 48 can be arranged in a stepless manner with respect to the outer side surfaces of the suction side wall 22 or pressure side wall 24, as shown.
  • a cooling hole 36 extends through the tip wall 34 together with the sealing tip 48 into the rib 38.
  • the cooling hole 36 has an inflow opening 42 for a cooling fluid.
  • a cooling fluid that can be supplied to the cavity 32 can flow into said opening 42, flow along the cooling hole 36 and exit at the outer end.
  • the cooling fluid cools the local area of the suction side wall 22, the tip wall 34 and in particular the sealing tip 48.
  • the cooling hole 36 does not necessarily have to extend through the sealing tip 48. According to an alternative embodiment, the cooling hole 36 can also end at the side of the sealing tip 48. For example, it can end on the hot gas side or also in the tip free space 39.
  • Figure 3 shows the top view of the interior of the blade tip according to the section line III-III Figure 2 .
  • the rib 38 is designed to be inclined with respect to the radial direction.
  • the rib 38 according to the exemplary embodiment shown here extends in a straight line from its head-side end 46 to its foot-side end 44.
  • the cooling hole 36 extending through the sealing tip 48, the tip wall 34 into the rib 38 is parallel to the radial direction R aligned, but inclined in the circumferential direction ( Fig. 2 ).
  • the outlined orientations of the cooling hole 36 and the rib 37 are not absolutely necessary, but rather in each case depending on the orientation of the aerodynamically curved airfoil in the space on the one hand and the location of the cooling hole on the other hand.
  • a channel axis 37 of the cooling hole 36 is preferably inclined at an obtuse angle in the region of the inflow opening 42 with respect to the longitudinal extent of the rib 38.
  • the cooling hole 36 for example, as well as the rib 38, can be inclined in the circumferential direction U and / or in the axial direction A.
  • FIG Figure 5 A cooling hole 36 inclined in the axial direction is shown in FIG Figure 5 shown and opens into the rib 38, which is curved in the radial direction Figure 5
  • Figure 4 shows the section through the blade tip-side end 27 of the blade 16 according to the section line IV-IV Figure 2 .
  • two ribs 38 according to the invention are provided on the suction side, of which the first asymmetrically curved protrudes from the inner surface 40 of the suction side wall 22.
  • the second of the two ribs 38 according to the invention is triangular in shape. It is not necessary for the rib to protrude from the inner surface like turbulators, the transition from the inner surface 40 to the side surface of the rib 38 can also be designed in a stepless manner and thus with low aerodynamic losses, particularly on its upstream side.
  • the cooling holes 36 open into one of the side surfaces of the ribs 38.
  • the position of the opening 42 is in that side surface of the rib 38 which is arranged away from a maximum rib height H.
  • the rib height H is based on the remaining inner surface 40 of the suction-side wall 22.
  • a cooling fluid preferably cooling air
  • the cooling fluid consequently flows through the cavity 32 and the cooling fluid has a predetermined main flow direction 50 due to the topology of the cavity 32 and the position of a cooling air supply and the position of adjacent outflow channels.
  • This main flow direction is to be determined in the immediate vicinity of the rib 38 according to the invention. Since the cooling fluid can never be completely free of dirt particles, it is advantageous if the inflow opening 42 of the cooling hole 36 is arranged on that side of the rib 38 in question which faces away from the cooling fluid flowing into the rib in question.
  • the inflow opening 42 of the cooling hole 36 is more or less in the slipstream - in the lee - of the maximum fin height H. From the cooling fluid entrained particles are directed into a flow path due to the shape of the rib 38, in which they move away with increasing distance from the inner surfaces of the side walls 22, 24 to the location of the maximum rib height H. Then they flow due to their inertia and that of the flow direction facing away from the inflow opening 42; they can only flow into the cooling hole 36 under difficult conditions. As a result, air with less particles - compared to the prior art - flows into the cooling holes 36 and thus the risk of clogging is reduced. This enables the use of cooling holes 36 with a particularly small diameter, for example also smaller than one millimeter, with a reduced risk of the inflow openings 42 or the cooling holes 36 being blocked by entrained particles.
  • the inflow opening 42 of the cooling holes 36 opening into the rib 38 is not circular, but rather is elliptically inclined with one longer axis and a shorter axis. Even this would make it difficult for particles flowing in cooling air to flow in a straight line toward cooling hole 36 to flow into cooling hole 36 in question.
  • the cooling hole 36 can be subsequently produced by drilling.
  • the orientation of the rib 38 which is inclined with respect to the radial direction R is particularly advantageous.
  • the inclined rib 38 offers ( Fig. 3 ) the advantage that the cooling hole 36 can be located in a comparatively large axial section AB.
  • the cooling hole 36 has an elliptically shaped inflow opening 42, which is always arranged on the side lying downstream of the incoming cooling fluid in the lee. This improves the manufacturability of such a turbine blade 10, since the section AB in which the cooling hole is to be drilled is comparatively large and therefore easier to hit.
  • the invention provides an airfoil 16 for an internally cooled turbine blade 10, comprising a suction-side wall 22 and a pressure-side wall 24, which extend from a common front edge 18 to a common rear edge 20 and in a span direction from a foot-side end 26 to a head-side End 27 extends at least partially enclosing a cavity, the head-side end 27 comprising a tip wall 34 delimiting the cavity 32 on the head side, in which at least one cooling hole 36, preferably a plurality of cooling holes 36 is provided for discharging cooling fluid that can flow inside.
  • a turbine blade in which the risk of clogging of cooling holes is reduced and the service life of the turbine blade 10 can be extended, it is proposed that in the cavity 32 preferably at least one rib extending from the tip wall 34 towards the foot-side end 42 is preferred a plurality of such ribs 38, from which this rib surrounding inner surfaces 40 of the suction side wall 22 and / or the inner surface 40 of the pressure side wall 24 protrudes and that - in relation to the cooling fluid - inflow opening 42 of the at least one cooling hole 36 opens laterally into the relevant rib 38 .

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

Claims (11)

  1. Corps (16) d'une aube (10) mobile de turbine à refroidissement intérieur,
    comprenant un extrados (22) et un intrados (24), qui, en s'étendant d'un bord (18) avant à un bord (20) arrière et dans une direction d'envergure d'une extrémité (26) du côté de l'emplanture à une extrémité (27) du côté de la tête, entourent, au moins en partie, une cavité (32),
    l'extrémité (27) du côté de la tête comprenant une paroi (34) de pointe, qui délimite la cavité (32) du côté de la tête, et dans laquelle est ou sont prévus au moins un trou (36) de refroidissement, de préférence plusieurs trous (36) de refroidissement, pour faire sortir du fluide de refroidissement pouvant passer à l'intérieur,
    caractérisé
    en ce que, dans la cavité (32), fait saillie ou font saillie, de la surface (40) intérieure de l'extrados (22) ou de la surface (40) intérieur de l'intrados (24), au moins une ailette (38), de préférence plusieurs ailettes (38), s'étendant de la paroi (34) de pointe en direction de l'extrémité du côté de l'emplanture, et
    en ce qu'une ouverture (42) d'entrée du au moins un trou (36) de refroidissement débouche latéralement dans l'ailette (38) concernée.
  2. Corps (16) d'aube suivant la revendication 1,
    dans lequel le trou (36) de refroidissement a un axe (37) de canalisation, qui est incliné, au moins dans la partie de l'ouverture (42) d'entrée du trou (36) de refroidissement, par rapport à l'étendue longitudinale de l'ailette (38).
  3. Corps (16) d'aube suivant la revendication 1 ou 2,
    dans lequel l'ouverture (42) d'entrée a une forme en ellipse ayant un petit axe et un grand axe, le petit axe étant plus petit que le diamètre du reste du trou (36) de refroidissement.
  4. Corps (16) d'aube suivant la revendication 1, 2 ou 3,
    dans lequel l'ailette (38) concernée a, dans un plan en section transversale normale à la direction d'envergure, un contour incurvé ayant une hauteur (H) d'ailette maximum - rapporté au reste de la surface intérieure - et l'extrémité (42) du côté de l'entrée du trou (36) de refroidissement concerné est disposée latéralement à l'emplacement de la hauteur maximum de l'ailette.
  5. Corps (16) d'aube suivant la revendication 1, 2 ou 3,
    dans lequel l'ailette (38) concernée a, dans un plan en section transversale normale à la direction d'envergure, un contour polygonal ayant une hauteur (H) d'ailette maximum - rapporté au reste de la surface intérieure - et l'ouverture d'entrée du trou de refroidissement concerné est disposée sur une surface disposée latéralement de l'ailette.
  6. Corps (16) d'aube suivant au moins l'une des revendications précédentes,
    dans lequel l'ailette (38) concernée est, de son extrémité (46) du côté de la tête à son extrémité (44) du côté de l'emplanture, inclinée en direction du bord avant ou en direction du bord arrière.
  7. Corps (16) d'aube suivant au moins l'une des revendications précédentes,
    dans lequel la cavité (32) voisine de l'ailette (38) concernée est telle que son arrivée de fluide de refroidissement se trouve sensiblement du côté de l'ailette concernée, qui est loin de la surface de l'ailette ayant l'ouverture d'entrée du trou de refroidissement.
  8. Corps (16) d'aube suivant au moins l'une des revendications précédentes,
    dans lequel la paroi 34 de pointe comprend au moins une pointe (48) d'étanchéité sur la surface tournée vers l'extérieur.
  9. Corps (16) d'aube suivant au moins la revendication 8,
    dans lequel le trou (36) de refroidissement concerné s'étend, au moins en partie, de préférence complètement, dans la pointe (48) d'étanchéité.
  10. Aube (10) mobile de turbine, ayant un corps (16) d'aube, dont le corps (16) d'aube correspond à un corps d'aube suivant les revendications 1 à 9.
  11. Procédé de fabrication d'un corps (16) d'aube suivant l'une des revendications 1 à 9,
    - on se procure un corps (16) d'aube fabriqué de préférence par coulée de précision et comprenant un extrados (22) et un intrados (24), qui, en s'étendant suivant une ligne médiane de profil d'un bord avant commun à un bord arrière commun, et dans une direction d'envergure, d'une extrémité du côté de l'emplanture à une extrémité du côté de la tête, entourent, au moins en partie, une cavité,
    dans lequel l'extrémité du côté de la tête comprend une paroi de pointe délimitant, du côté de la tête, la cavité,
    dans lequel, dans la cavité du corps de l'aube, fait ou font saillie au moins une ailette, de préférence plusieurs ailettes, s'étendant de la paroi de pointe en direction de l'extrémité du côté de l'emplanture, et
    - on perce le au moins un trou de refroidissement, de manière à ce que son ouverture d'entrée débouche dans l'une des ailettes concernées.
EP17197244.1A 2017-10-19 2017-10-19 Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale Active EP3473808B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17197244.1A EP3473808B1 (fr) 2017-10-19 2017-10-19 Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale
US16/145,792 US10746027B2 (en) 2017-10-19 2018-09-28 Blade airfoil for an internally cooled turbine rotor blade, and method for producing the same

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17197244.1A EP3473808B1 (fr) 2017-10-19 2017-10-19 Pale d'aube pour une aube mobile de turbine à refroidissement intérieur ainsi que procédé de fabrication d'une telle pale

Publications (2)

Publication Number Publication Date
EP3473808A1 EP3473808A1 (fr) 2019-04-24
EP3473808B1 true EP3473808B1 (fr) 2020-06-17

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US (1) US10746027B2 (fr)
EP (1) EP3473808B1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10551327B2 (en) * 2018-04-11 2020-02-04 General Electric Company Cooling hole inspection system
US11274559B2 (en) * 2020-01-15 2022-03-15 Raytheon Technologies Corporation Turbine blade tip dirt removal feature
GB2591298B (en) * 2020-01-27 2022-06-08 Gkn Aerospace Sweden Ab Outlet guide vane cooler
KR102466386B1 (ko) * 2020-09-25 2022-11-10 두산에너빌리티 주식회사 터빈 블레이드 및 이를 포함하는 터빈

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4142824A (en) * 1977-09-02 1979-03-06 General Electric Company Tip cooling for turbine blades
JPH0663442B2 (ja) * 1989-09-04 1994-08-22 株式会社日立製作所 タービン翼
GB2343486B (en) 1998-06-19 2000-09-20 Rolls Royce Plc Improvemnts in or relating to cooling systems for gas turbine engine airfoil
US6224336B1 (en) * 1999-06-09 2001-05-01 General Electric Company Triple tip-rib airfoil
WO2003080998A1 (fr) * 2002-03-25 2003-10-02 Alstom Technology Ltd Aube de turbine refroidie
GB0524735D0 (en) 2005-12-03 2006-01-11 Rolls Royce Plc Turbine blade
US7287959B2 (en) * 2005-12-05 2007-10-30 General Electric Company Blunt tip turbine blade
US8734107B2 (en) * 2011-05-31 2014-05-27 General Electric Company Ceramic-based tip cap for a turbine bucket
GB201120273D0 (en) * 2011-11-24 2012-01-04 Rolls Royce Plc Aerofoil cooling arrangement
US10227876B2 (en) * 2015-12-07 2019-03-12 General Electric Company Fillet optimization for turbine airfoil

Non-Patent Citations (1)

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None *

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Publication number Publication date
US10746027B2 (en) 2020-08-18
EP3473808A1 (fr) 2019-04-24
US20190120066A1 (en) 2019-04-25

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