EP3475011A1 - Turbomachine blade cooling circuit - Google Patents
Turbomachine blade cooling circuitInfo
- Publication number
- EP3475011A1 EP3475011A1 EP17735190.5A EP17735190A EP3475011A1 EP 3475011 A1 EP3475011 A1 EP 3475011A1 EP 17735190 A EP17735190 A EP 17735190A EP 3475011 A1 EP3475011 A1 EP 3475011A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- core
- face
- symmetry
- blade
- cavity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title claims description 26
- 238000004519 manufacturing process Methods 0.000 claims abstract description 17
- 238000000465 moulding Methods 0.000 claims abstract description 8
- 238000000034 method Methods 0.000 claims description 8
- 238000005495 investment casting Methods 0.000 claims description 3
- 230000001419 dependent effect Effects 0.000 claims 1
- 239000002184 metal Substances 0.000 description 6
- 238000002347 injection Methods 0.000 description 3
- 239000007924 injection Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000011230 binding agent Substances 0.000 description 2
- 238000005266 casting Methods 0.000 description 2
- 229910010293 ceramic material Inorganic materials 0.000 description 2
- 238000000605 extraction Methods 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 238000002513 implantation Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 239000000843 powder Substances 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 239000011800 void material Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000007373 indentation Methods 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000010025 steaming Methods 0.000 description 1
- 238000000859 sublimation Methods 0.000 description 1
- 230000008022 sublimation Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
- B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/24—Three-dimensional ellipsoidal
- F05D2250/241—Three-dimensional ellipsoidal spherical
Definitions
- the present invention relates to the manufacture of a turbomachine blade by lost-wax molding, and more particularly to a blade comprising an internal cooling cavity.
- the moving blades of a turbomachine turbine each comprise an internal cooling circuit which enables them to withstand the thermal stresses to which the blades are subjected, when the turbomachine is in operation.
- the internal cooling circuit is traversed by a flow of cooling air.
- a cooling circuit comprises for example at least one intake opening located near the root of the blade, at least one internal cavity and at least one exhaust opening located near the top of the blade, the flow of air successively passing through the intake opening, the cavity and the exhaust opening.
- the cavity traditionally comprises disrupters, for example in the form of bridges or concave shapes.
- the disrupters must allow to evenly distribute the airflow over the entire dawn without slowing the latter.
- a blade is for example made by lost wax casting.
- a wax model is molded via a mold in which is placed a core (also called a foundry core) previously realized.
- the wax model is then covered, alternately, with slip and refractory powder so as to make a carapace.
- the wax is removed from the shell and the carapace is cooked at high temperature.
- the molten metal is then poured into the carapace, the metal thus occupying more precisely the void between the core and the inner face of the shell. After solidification of the metal, the dawn is obtained by unblocking the shell and the core.
- the core is for example ceramic material with porous structure.
- the core is generally obtained by injection molding to the press.
- the core is of complex shape and includes in particular thin recesses capable of forming the bridges after the casting of the molten metal.
- the complexity of the core requires the use of a mold (also called a core box) comprising a plurality of moving sub-pieces relative to each other, this architecture thus making it possible to avoid any undercut, and in other words to be able to demold suitably the nucleus.
- a mold also called a core box
- the filling is obtained by bonding material, this filling being conducive to the appearance of defects, and more generally to a scrapping of large quantities of nuclei.
- the shape of the core is simpler, thus making it easier to obtain the latter.
- the cooling of the dawn does not bring satisfaction. Indeed, the presence of concave shapes causes vortices in the cavity, the latter having adverse repercussions on the flow of the air flow. On the other hand, the concave shapes do not allow to distribute homogeneously the air flow over the entire blade, and in other words the airflow does not sufficiently cool the dawn.
- the object of the present invention is to provide a blade comprising an appropriate cooling circuit, while optimizing its manufacturing process.
- the invention proposes for this purpose a core intended for the manufacture of a turbomachine blade by lost-wax molding, this core comprising a convex first curved outer face and a second concave curved outer face, characterized in that the first and second faces comprise a plurality of depressions, each depression having a spherical portion,
- each of said depressions is at least partially defined by an axis of symmetry, the axes of symmetry of the spherical portions of the first face being parallel to a first direction, wherein said first direction is defined, in a transverse plane, by the bisector of the angle formed by the intersection of a first tangent, at the first face to the first junction point between the first face and a first connection between the first and second faces, and a second tangent to the first face at the second junction point between the first face and a second joint between the first and second faces, the first and second tangents being defined in the transverse plane, the first and second junction points being opposite to each other.
- the kernel structure is simple and thus minimizes the number of discarded kernels. Such a core also makes it possible to avoid a refilling filling.
- the core according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
- the depressions of the first face are offset with respect to the depressions of the second face;
- the transverse plane is substantially perpendicular to an axis of elongation of the core or may not be;
- the second direction is defined, in a transverse plane, by the bisector of the angle formed by the intersection of a first tangent to the second face at the third junction point between the second face and the first connection, and a second tangent to the second face to the fourth junction point between the second face and the second joint, the first and second tangents being defined in the transverse plane, the third and fourth junction points being opposite to each other.
- the subject of the invention is a mold intended for the manufacture of a core as described above, the mold comprising a first cavity and a second cavity movable relative to one another and delimiting an injection cavity of the core, the first imprint comprising a first concave curved inner surface adapted to form the first face of the core, the second indentation comprising a second convex curved inner surface capable of forming the second face of the core, the first and second surfaces comprising a plurality of protuberances capable of forming the depressions of the core, each protuberance comprising a spherical portion,
- each of the protuberances is at least partially defined by an axis of symmetry, the axes of symmetry of the spherical portions of the first surface are parallel to said first direction of said core, said first direction corresponding to a first demolding direction.
- the structure of the mold is simple to know a first imprint and a second imprint, so it is easy to position relative to each other. Such a structure makes it possible to considerably minimize the number of discarded nuclei.
- This cooling circuit is also compatible with different blade geometries, and in particular the blades having locally, in a transverse plane, a strong curvature.
- the mold according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
- the axes of symmetry of the spherical portions of the protuberances of the second surface are parallel to said direction of said core, said second direction corresponding to a second demolding direction;
- the first cavity is movable in the first demolding direction and / or the second cavity is movable in the second demolding direction;
- each of the bumps is defined by an axis of symmetry, the axes of symmetry of the spherical sections of the bumps of the first wall are parallel.
- the third subject of the invention is a method for manufacturing a turbine engine blade by lost-wax molding, this method comprising a step of manufacturing a core as described previously via a mold as described above, the method comprising preferably a demolding step in which the first imprint is moved in a first demolding direction and / or the second imprint is moved in a second demolding direction.
- the manufacturing process of the blade is simplified, and in particular obtaining the core, to the benefit of productivity.
- the fourth object of the invention is a blade obtained according to the manufacturing method as previously described, the blade comprising a cooling cavity delimited by a first concave curved inner wall and a second convex curved inner wall, the first and second walls comprising each a plurality of bumps, each bump comprising a spherical section.
- the cooling cavity distributes homogeneously the flow of cooling air over the first and second walls without slowing it down, and in other words, generally cooling the dawn effectively.
- the blade according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other:
- the bumps of the first wall are offset with respect to the bumps of the second wall;
- FIG. 1 is a schematic front view of a blade
- FIG. 2 is a sectional view of the blade shown in Figure 1, according to the plane ll-ll of Figure 1;
- FIG. 3 is a cross-sectional view of a core used for the manufacture of the blade, at a current portion;
- FIG. 4 is a simplified cross-sectional view of the core, illustrating the determination of the direction of the penetrations of a first face of the core, at a current portion;
- FIG. 5 is a simplified cross-sectional view of the core, illustrating the determination of the direction of the depressions of a second face of the core, at a current portion;
- FIG. 6 is a detail view of the core illustrating the implantation of the depressions
- FIG. 7 is a sectional view of a mold adapted to achieve the core.
- FIG. 1 shows a blade 1 of a turbomachine turbine, for example a high pressure turbine or a low pressure turbine.
- the blade 1 comprises a running portion of aerodynamic profile which extends longitudinally along an axis X between a root 2 of blade 1 and a vertex 3 of blade 1.
- the blade root 2 is intended to be mounted on a rotor (not shown) of the turbine.
- the top 3 of the blade 1 comprises sealing strips 4 arranged opposite an abradable coating mounted on the casing (not shown) of the turbine.
- the aerodynamic running portion of the vane 1 has a leading edge 5 arranged upstream in the direction of gas flow in the turbine, a trailing edge 6 opposite the leading edge 5, a side face 7 and an extrados side face 8, these faces 7, 8 intrados and extrados connecting the leading edge 5 and the trailing edge 6.
- the blade 1 in a transverse plane, is profiled along an average line M connecting the leading edge 5 and the trailing edge 6.
- the faces 7, 8 intrados and extrados are curved, and respectively concave and convex.
- Dawn 1 has a strong curvature locally.
- the blade 1 further comprises an internal cooling circuit 9 which enables it to withstand the thermal stresses to which it is subjected, this circuit 9 including at least one cooling cavity 10 extending longitudinally between the blade root 2 1 and the top 3 of blade 1, at least one opening 1 1 intake and at least one opening 12 exhaust.
- the internal cooling circuit 9 is traversed by a flow of cooling air.
- the opening 1 1 intake is located in the foot 2 of blade 1 and opens on the underside of the foot 2 of blade 1 in the for example, a plurality of channels.
- the exhaust opening 12 is located at the top of blade 1 1 and opens on the upper face of the blade 1 in the form for example of a plurality of channels.
- the flow of cooling air successively passes through the opening 1 1 intake, the cavity 10 and the opening 12 exhaust.
- the cooling cavity 10 is centered on the mean line M of the blade 1 and is delimited by a first lateral wall 13 oriented on the extrados side of the blade 1 and by a second wall 14. lateral oriented on the intrados side of the blade 1. More precisely, the first and second walls 13, 14 are curved, and respectively concave and convex. The first and second walls 13, 14 comprise bumps 15a, 15b intended to direct the flow of air into the cavity 10, and more precisely to distribute it homogeneously over the first and second walls 13, 14 without, however, slowing it down.
- the bumps 15a of the first wall 13 are offset, longitudinally and transversely, relative to the bumps 15b of the second wall 14.
- Each bump 15a, 15b comprises a spherical portion 1 6 and is defined at least partially along an axis B of symmetry passing through the axis B1 of symmetry spherical section 16.
- the axes B1 of symmetry spherical sections 1 6 of the first wall 13 are parallel.
- the axes B1 of symmetry of the spherical sections 1 6 of the second wall 14 are parallel.
- Some boss 15a, 15b further comprises a conical section 17, more or less extended along the bumps 15a, 15b, the axis B2 of symmetry passes through the axis B of symmetry of the boss 15a, 15b and therefore by the B1 axis of symmetry spherical section 16.
- the bumps 15a are substantially staggered relative to the bumps 15b in the current part, in a longitudinal projection plane perpendicular to the axis B.
- the blade 1 is made by a method of lost wax casting, and the cooling cavity 10 of the blade 1 is obtained via a core 18 illustrated in particular in Figure 3, the latter being itself obtained via a mold 19 (also known as a box). core) illustrated in FIG. 7.
- the cavity 10 of the blade 1 is thus the reproduction of the core 18, and in other words the cavity 10 has identical dimensional and geometrical characteristics to those of the core 18.
- the method of manufacturing blade 1 comprises the following steps: A step of molding the core 18 (illustrated in FIG. 3) via the mold 19 (illustrated in FIG. 7);
- a heating step in which, simultaneously, the wax is removed from the shell and the shell is cooked, for example by steaming;
- the cavity 10 of the cooling circuit 9 has the same dimensional and geometric characteristics as the core 18.
- the core 18 thus comprises a first lateral face 20, a second lateral face 21, a first connector 22 defining a connecting radius of the edge of the and a second connector 23 defining a connecting radius of the trailing edge, the first and second faces 20, 21 connecting the first connector 22 and the second connector 23.
- the first and second faces 20, 21 of the core 18 comprise depressions 24a. , 24b able to form the bumps 15a, 15b of the cavity 10.
- the first and second faces 20, 21 of the core 18 are respectively able to form the first wall 13 and the second wall 14 of the cavity 10.
- the first and second faces 20, 21 are curved, and respectively convex and concave.
- Each depression 24a, 24b comprises a spherical portion and is defined at least partially along an axis E of symmetry passing through the axis E1 of symmetry of the spherical portion.
- the axes E1 of symmetry of the spherical portions of the first face 20 are parallel in a first direction D1.
- the axes E1 of symmetry of the spherical portions of the second face 21 are parallel to a second direction D2.
- certain recesses 24a, 24b further comprise a conical portion 26 , more or less extended according to the recesses 24a, 24b, the axis E2 of symmetry passes through the axis E of symmetry of the depression 24a, 24b and therefore by the axis E1 of symmetry of the spherical portion.
- the first direction D1 is defined, in a transverse plane, by the bisector 27 of the angle formed by the intersection of a first tangent 28, the first face 20 with the first J1 junction point between the first face 20 and the first connector 22, and a second tangent 29 to the first face 20 to the second point J2 junction between the first face 20 and the second connector 23, the first and second tangents 28 , 29 being defined in the transverse plane.
- the second direction D2 is defined, in a transverse plane, by the bisector 30 of the angle formed by the intersection of a first tangent 31 to the second face 21 to the third point J3 junction between the second face 21 and the first connection 22, and a second tangent 32 to the second face 21 to the fourth point J4 junction between the second face 21 and the second connection 23, the first and second tangents 31, 32 being defined in the transverse plane.
- the depressions 24a, 24b comprise connecting fillet (not shown).
- the thickness of the core 18 is constant, the first and second directions D1, D2 thus being parallel.
- the thickness of the core 18 is for example between 0.2 mm and 1 mm.
- the maximum depth of the recesses 24a, 24b is for example equal to half the thickness of the core 18.
- FIG. 6 illustrates, in a plane perpendicular to the first direction D1 (or the second direction D2), the implantation of the depressions 24a of the first face 20 with respect to the depressions 24b of the second face 21.
- the depressions 24a of the first face 20 are offset, longitudinally and transversely, with respect to the depressions 24b of the second face 21.
- the recesses 24a are positioned substantially staggered with respect to the depressions 24b.
- the radius of the spherical portions is for example between 0.2 mm and 0.5 mm.
- the depressions 24a must not be in contact and / or open in the depressions 24b, a minimum thickness of material being to be respected between the depressions 24a and 24b. Thus, it avoids any connection between the bumps 15a and 15b of the blade.
- the core 18 may comprise depressions 24a, 24b on all of the first and second faces 20, 21 or locally on the faces 20, 21.
- the core 18 comprises only recesses 24a, 24b on the faces 20, 21 at the second connector 23 (for example one or more rows of depressions 24a, 24b).
- the cooling cavity 10 comprises only bumps 15a, 15b on the walls 13, 14 at the trailing edge 6.
- the core 18 is obtained via the mold 19 shown in the open position in FIG. 7, the mold 19 comprises a first cavity 33 and a second cavity 34 movable relative to each other and delimiting an injection cavity 35 of the core 18.
- the first recess 33 comprises a first inner surface 36, curved, concave adapted to form the first face 20 of the core 18.
- the second recess 34 comprises a second inner surface, curved, convex, capable of forming the second face 21 of the core 18, the first and second surfaces 36, 37 comprising a plurality of protuberances 38 able to form the recesses 24a, 24b of the core 18.
- each protrusion 38 comprises a spherical portion 39 and is defined at least partially along a symmetry axis P passing through the axis P1 of symmetry of the spherical portion 39.
- the axes P1 of symmetry of the spherical portions 39 of the first surface 36 are parallel to a first demolding direction A1 corresponding to the first direction D1 of the core 18.
- the axes P1 of symmetry of the spherical portions 39 of the second surface 37 are parallel to a second direction of demolding A2 corresponding to the second direction D2 of the core 18.
- first and second directions D1, D2 of the core 18 correspond to the first and second directions A1, A2 demolding the mold 19 simplifies the structure of the mold 19 and facilitate the extraction of the core 18 out of the mold 19.
- some protuberances 38 further comprise a conical portion 40, more or less extended along the protuberances 38, whose axis P2 of symmetry passes through the axis P of symmetry of the protuberance 38 and therefore by the axis P1 of symmetry of the spherical portion 39.
- the use of conical shape facilitates the extraction of the core 18 out of the mold 19.
- the half-angle at the top of the conical portion 40 of the protrusion 38 is for example 15 °.
- the first cavity 33 is movable in the first direction of release A1 and the second cavity 34 is fixed.
- the second cavity 34 is movable in the second direction of demolding A2 and the first cavity 33 is fixed.
- the first cavity 33 is movable along the first demolding direction A1 and the second cavity 34 is movable along the second demolding direction A2.
- the core 18 is for example made of ceramic material having a porous structure, this material being obtained from a mixture comprising a refractory filler and an organic fraction forming a binder.
- the method of manufacturing the core 18 via the mold 19 comprises the following steps:
- a debinding step in which the binder is removed for example by sublimation or thermal degradation
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1656042A FR3052990B1 (en) | 2016-06-28 | 2016-06-28 | COOLING CIRCUIT OF A TURBOMACHINE BLADE |
PCT/FR2017/051438 WO2018002466A1 (en) | 2016-06-28 | 2017-06-07 | Turbomachine blade cooling circuit |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3475011A1 true EP3475011A1 (en) | 2019-05-01 |
EP3475011B1 EP3475011B1 (en) | 2022-03-30 |
Family
ID=57583140
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17735190.5A Active EP3475011B1 (en) | 2016-06-28 | 2017-06-07 | Turbomachine blade cooling circuit |
Country Status (4)
Country | Link |
---|---|
US (1) | US10682687B2 (en) |
EP (1) | EP3475011B1 (en) |
FR (1) | FR3052990B1 (en) |
WO (1) | WO2018002466A1 (en) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3629910A1 (en) * | 1986-09-03 | 1988-03-17 | Mtu Muenchen Gmbh | METAL HOLLOW COMPONENT WITH A METAL INSERT, IN PARTICULAR TURBINE BLADE WITH COOLING INSERT |
US7758314B2 (en) * | 2003-03-12 | 2010-07-20 | Florida Turbine Technologies, Inc. | Tungsten shell for a spar and shell turbine vane |
FR2870560B1 (en) * | 2004-05-18 | 2006-08-25 | Snecma Moteurs Sa | HIGH TEMPERATURE RATIO COOLING CIRCUIT FOR GAS TURBINE BLADE |
US20070201980A1 (en) * | 2005-10-11 | 2007-08-30 | Honeywell International, Inc. | Method to augment heat transfer using chamfered cylindrical depressions in cast internal cooling passages |
US9243502B2 (en) * | 2012-04-24 | 2016-01-26 | United Technologies Corporation | Airfoil cooling enhancement and method of making the same |
-
2016
- 2016-06-28 FR FR1656042A patent/FR3052990B1/en active Active
-
2017
- 2017-06-07 WO PCT/FR2017/051438 patent/WO2018002466A1/en unknown
- 2017-06-07 US US16/314,341 patent/US10682687B2/en active Active
- 2017-06-07 EP EP17735190.5A patent/EP3475011B1/en active Active
Also Published As
Publication number | Publication date |
---|---|
WO2018002466A1 (en) | 2018-01-04 |
US20190240725A1 (en) | 2019-08-08 |
FR3052990A1 (en) | 2017-12-29 |
EP3475011B1 (en) | 2022-03-30 |
FR3052990B1 (en) | 2020-07-03 |
US10682687B2 (en) | 2020-06-16 |
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