EP3414031B1 - Verfahren zur bildung von entstaubungslöchern für eine turbinenschaufel und zugehöriger keramikkern - Google Patents

Verfahren zur bildung von entstaubungslöchern für eine turbinenschaufel und zugehöriger keramikkern Download PDF

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Publication number
EP3414031B1
EP3414031B1 EP17709141.0A EP17709141A EP3414031B1 EP 3414031 B1 EP3414031 B1 EP 3414031B1 EP 17709141 A EP17709141 A EP 17709141A EP 3414031 B1 EP3414031 B1 EP 3414031B1
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Prior art keywords
core
orifice
dust
blade
ceramic
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EP17709141.0A
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English (en)
French (fr)
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EP3414031A1 (de
Inventor
Adrien Bernard Vincent ROLLINGER
Mirna Bechelany
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Safran SA
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Safran SA
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    • 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
    • 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
    • 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
    • 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 turbine blades, and more particularly to 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 there.
  • the gases resulting from this combustion flow downstream of the combustion chamber and then supply a high pressure turbine and a low pressure turbine.
  • Each turbine has one or more rows of fixed blades (called distributors) alternating with one or more rows of moving blades (called moving wheels), spaced circumferentially around the turbine rotor.
  • These turbine blades are subjected to very high temperatures of the combustion gases, which reach values well above those which these blades which are in direct contact with these gases can withstand without damage, which necessarily implies ensuring their continuous cooling.
  • an integrated cooling circuit which, when it is desired to ensure efficient and precise cooling without significantly increasing the air flow and without penalizing engine performance, includes multiple cavities.
  • the hollow blades thus formed are manufactured by the so-called “lost wax” foundry process which requires the use of a model part or core whose external surface corresponds to the internal surface of the finished blade, as described in the applications FR2986982 Or FR2961552 filed in the name of the plaintiff.
  • the air necessary for the operation of the engine generally contains various dusts (in particular fine sand) which can accumulate in the cooling circuits of the turbine blades, causing the evacuation orifices at the outlet of the cavities to be blocked and thus threatening the air. integrity of dawn.
  • the blades of turbine are equipped at the top of the cavity with calibrated dust removal holes, obtained by high precision machining or from connecting rods in alumina or quartz inserted in the ceramic core, and whose role is to generate these holes and guarantee the evacuation of these particles after their release (that is to say their dissolution).
  • alumina rods are very difficult to remove with basic solutions (or under the standard shaking conditions of ceramic cores) and require a significant residence time, a very high sodium or potash concentration and high temperatures and pressures. very high levels likely to be aggressive towards the alloy (stress corrosion).
  • quartz rods have low mechanical strength, thus penalizing their use in a lost wax casting process where the core, which has a different coefficient of thermal expansion (CTE) and is also often of a different composition, undergoes several mechanical stresses. .
  • CTE coefficient of thermal expansion
  • rods In the case, for example, of cores produced by additive manufacturing or cores obtained by machining in a ceramic block, the rods cannot be embedded in the core during manufacturing (unlike the injection molding process). Finally, the use of rods is not applicable to all core geometries, particularly those using thin plates whose rods must then conform to the shape.
  • the present invention therefore aims to overcome the aforementioned drawbacks by proposing a geometric arrangement of the core making it possible to simply obtain dust removal holes more reliably than currently and in particular without harming the robustness of this core. Another aim is to eliminate the final operation of drilling the bathtub of the prior art to obtain these orifices.
  • a ceramic core used for the manufacture of a hollow turbine blade of a turbomachine using the lost wax casting technique, said blade comprising calibrated dust removal holes emanating from a top of at less one cavity and opening into a bathtub of said blade, characterized in that each of said calibrated dust removal holes is formed in a core part of a determined height sufficient to guarantee its mechanical strength, said core part comprising a through orifice of axis perpendicular to a longitudinal axis of said calibrated dust removal hole and delimiting on either side of said through orifice on the one hand a core cylinder of a determined diameter corresponding to said dust removal hole to be formed and on the other hand a remaining core volume intended to be filled after casting, so that said calibrated dust removal hole is obtained without drilling and without the use of connecting rods.
  • dust removal holes can be obtained directly from the foundry by injection, additive manufacturing or machining of ceramic cores without drilling or the use of connecting rods. Any possible source of differential thermal expansion is eliminated, the mechanical strength of the core is improved and correlatively the mechanical properties of the blade are thus maintained. With this core, the machining operation of the prior art having to take into account restrictive uncertainties and which can have a detrimental impact on the geometry of the plates of a multi-cavity circuit is also eliminated.
  • said core part can form part of a lateral column intended to create a cavity side of said blade or an inter-cavity connection zone between said at least one cavity and said bathtub.
  • a recessed zone is provided to allow centering of said through orifice in said connection zone, so as to guarantee better holding of said core portion during the casting.
  • said remaining core volume comprises at least one lateral stiffener (two stiffeners giving it a four-lobed shape) dimensioned so as to guarantee better resistance of said core part during casting.
  • the invention also relates to the method of forming calibrated dust removal holes in a hollow turbomachine turbine blade produced using the lost wax casting technique using a ceramic core as explained previously and any turbomachine turbine provided with a plurality of cooled blades manufactured from such a process.
  • FIG. 1 represents, at the level of its head assembly, a ceramic core intended for the production of a hollow turbine blade of a turbomachine.
  • the ceramic core 10 in the example illustrated, has seven parts or columns.
  • the latter receives a flow of cooling air through a pipe resulting, after foundry, from the presence of a first column base of the core.
  • Three other columns 16, 18, 20 correspond to adjacent cavities which receive a second flow of cooling air brought by another pipe coming from the presence of a second column base of the core.
  • the core further comprises sixth and seventh lateral columns 22, 24 corresponding to lateral cavities created after foundry and both separated from the second and third columns 14, 16 by a determined spacing necessary for the creation of 'a solid inter-cavity wall when pouring the molten metal.
  • the first and second columns 12 and 14 are connected to each other by a series of bridges 26, to which will correspond, after foundry, air supply orifices for cooling the leading edge cavity.
  • the size of the different bridges is determined to avoid their breakage when handling the core 10, which would render it unusable.
  • the bridges are, in the example considered, distributed by being spaced substantially regularly over the height of the core, particularly at the level of the first column of the core.
  • the dust removal holes in the turbine blades necessary for the evacuation of dust (in particular fine sand) which can accumulate in the cooling circuits are obtained by a geometric arrangement of a part of core, directly raw from the foundry, without drilling and without the use of connecting rods, whether they are the holes present at the level of the side cavities of the core or those ensuring the connection with the bathtub.
  • the manufacturing process lost wax of the dawn once this core has been produced is classic and consists first of all in forming an injection mold in which the core is placed before injecting the wax.
  • the wax model thus created is then dipped in slips made of ceramic suspension to make a casting mold (also called a shell mold). Finally, the wax is removed and the shell mold is fired into which the molten metal can then be poured.
  • Final machining operations (however simplified compared to those of the prior art) described further below will then make it possible to obtain the finished blade.
  • This geometry can be obtained conventionally by integrating a bridge type disruptor in the mold of the plate (at a through hole with a longitudinal axis delimiting in a direction perpendicular to this axis the cylinder 30 and the remaining volume 33) for the case of ceramic injection or without additional constraints for the case of additive manufacturing or by machining of cores.
  • FIG. 2A illustrates the upper part of the blade (bathtub) obtained at the end of the casting (as foundry) with the two cavities 32, 34 corresponding to the two lateral columns and the excess material which surrounds them due to the assembly of these columns.
  • FIG 2B we find the same bathtub after machining this excess material and we see that, with the invention, two holes 36A, 38A; 36B, 38B are formed at each cavity (instead of just one in the prior art).
  • connection with the bathtub is illustrated in Figure 3 .
  • the side plates to obtain a dust removal hole, a local geometric arrangement of the connection is provided, by forming on either side of the through orifice 41 on the one hand a core cylinder 40 of a determined diameter corresponding to the diameter of the dust removal hole to be made and on the other hand the remaining volume of core 43 intended to be resealed after casting.
  • the core cylinder also has the lowest possible height to guarantee good hold of the core and to avoid the formation of cracks.
  • the through orifice can be formed by the use of a bridge type disruptor integrated into the foundry mold.
  • the space available between the cavities and the bathtub being very limited and the inter-cavity connection being thin (therefore with a small section), it is also planned to arrange on a portion of the core at the level of the bathtub create a recessed area so as to provide more space.
  • the through orifice 41 intended to receive the disruptor therefore finds itself centered on the inter-cavity connection, better robustness is also obtained during casting.
  • FIG. 3A illustrates the upper part of the blade (bath) obtained at the end of the casting (as foundry) with the extension 42 resulting from the removal of the core from space d.
  • FIG. 3B we find the same bathtub after machining this extension and we see that, with the invention, two holes 44, 46 are formed at the level of the bathtub.
  • two lateral stiffeners 48A, 48B giving a quadrilobed shape to the second hole (corresponding to a section of volume 43) and sized so as to guarantee the robustness of the core.
  • the stiffeners stiffen the connection and prevent deformation of the nuclei.

Claims (9)

  1. Keramikkern (10), der für die Fertigung einer hohlen Turbinentriebwerksschaufel nach der Wachsausschmelztechnik verwendet wird, wobei die Schaufel kalibrierte Entstaubungslöcher umfasst, die von einer Spitze mindestens eines Hohlraums ausgehen und in eine Wanne der Schaufel münden, dadurch gekennzeichnet, dass jedes der kalibrierten Entstaubungslöcher in einem Kernteil (22A) mit einer bestimmten Höhe gebildet ist, die ausreicht, um dessen mechanische Festigkeit zu gewährleisten, wobei der Kernteil eine Durchgangsöffnung (31, 41) umfasst, deren Achse senkrecht zu einer Längsachse des kalibrierten Entstaubungslochs ist und die auf beiden Seiten der Durchgangsöffnung einerseits einen Kernzylinder (30, 40) mit einem bestimmten Durchmesser, der dem zu bildenden Entstaubungsloch entspricht, und andererseits ein Restkernvolumen (33, 43) abgrenzt, das dazu bestimmt ist, nach dem Guss wieder verschlossen zu werden, derart dass das kalibrierte Entstaubungsloch ohne Bohrung und ohne Verwendung von Verbindungsstangen erhalten wird.
  2. Keramikkern nach Anspruch 1, dadurch gekennzeichnet, dass der Kernteil einen Teil (22A) einer seitlichen Säule (22, 24) bildet, die dazu bestimmt ist, einen seitlichen Hohlraum der Schaufel zu schaffen.
  3. Keramikkern nach Anspruch 1, dadurch gekennzeichnet, dass der Kernteil eine Zone (e) zur Verbindung zwischen Hohlräumen zwischen dem mindestens einen Hohlraum und der Wanne bildet.
  4. Keramikkern nach Anspruch 3, dadurch gekennzeichnet, dass er an einem Kernabschnitt, welcher der zu schaffenden Wanne entspricht, eine vertiefte Zone (d) umfasst, um eine Zentrierung der Durchgangsöffnung in der Verbindungszone zu ermöglichen, derart dass eine bessere Festigkeit des Kernteils beim Guss gewährleistet wird.
  5. Keramikkern nach Anspruch 2 oder Anspruch 3, dadurch gekennzeichnet, dass das Volumen des Restkerns mindestens eine seitliche Aussteifung (39; 48A, 48B) umfasst, die derart bemessen ist, dass eine bessere Festigkeit des Kernteils beim Guss gewährleistet wird.
  6. Keramikkern nach Anspruch 5, dadurch gekennzeichnet, dass das Restkernvolumen zwei seitliche Aussteifungen (48A, 48B) umfasst, die einander gegenüberliegen und ihm eine vierblättrige Form verleihen.
  7. Nutzung eines Keramikkerns nach einem der Ansprüche 1 bis 6 für die Herstellung einer hohlen Turbinentriebwerksschaufel nach der Wachsausschmelztechnik.
  8. Verfahren zur Bildung kalibrierter Entstaubungslöcher in einer hohlen Turbinentriebwerksschaufel, die nach der Wachsausschmelztechnik hergestellt wird, mittels eines Keramikkerns, dessen äußere Oberfläche dazu bestimmt ist, die innere Oberfläche der fertigen Schaufel zu bilden, dadurch gekennzeichnet, dass es einen Schritt zur Bildung, in einem Kernteil (22A) mit einer bestimmten Höhe, die ausreicht, um seine mechanische Festigkeit zu gewährleisten, und in dem jedes der kalibrierten Entstaubungslöcher gebildet wird, einer Durchgangsöffnung (31, 41) umfasst, deren Achse senkrecht zu einer Längsachse des kalibrierten Entstaubungslochs ist und die auf beiden Seiten der Durchgangsöffnung einerseits einen Kernzylinder (30, 40) mit einem bestimmten Durchmesser, der dem zu bildenden Entstaubungsloch entspricht, und andererseits ein Restkernvolumen (33, 43) abgrenzt, das dazu bestimmt ist, nach dem Guss wieder verschlossen zu werden, derart dass das kalibrierte Entstaubungsloch ohne Bohrung und ohne Verwendung von Verbindungsstangen erhalten wird.
  9. Verfahren nach Anspruch 8, dadurch gekennzeichnet, dass die Durchgangsöffnung durch die Nutzung eines Störelements vom Typ Steg gebildet wird.
EP17709141.0A 2016-02-12 2017-02-10 Verfahren zur bildung von entstaubungslöchern für eine turbinenschaufel und zugehöriger keramikkern Active EP3414031B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1651134A FR3047767B1 (fr) 2016-02-12 2016-02-12 Procede de formation de trous de depoussierage pour aube de turbine et noyau ceramique associe
PCT/FR2017/050310 WO2017137709A1 (fr) 2016-02-12 2017-02-10 Procédé de formation de trous de dépoussiérage pour aube de turbine et noyau céramique associé

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EP3414031A1 EP3414031A1 (de) 2018-12-19
EP3414031B1 true EP3414031B1 (de) 2023-09-20

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US (1) US10537935B2 (de)
EP (1) EP3414031B1 (de)
CN (1) CN108698117B (de)
BR (1) BR112018016416B1 (de)
CA (1) CA3014022C (de)
FR (1) FR3047767B1 (de)
RU (1) RU2745073C2 (de)
WO (1) WO2017137709A1 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3079551B1 (fr) * 2018-03-29 2020-04-24 Safran Helicopter Engines Aube de distributeur de turbine comportant une paroi interne de refroidissement issue de fabrication additive
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
FR3100143B1 (fr) * 2019-08-30 2021-11-12 Safran Procédé amélioré de fabrication d’un noyau céramique pour la fabrication d’aubes de turbomachine
US20220212276A1 (en) * 2021-01-06 2022-07-07 General Electric Company Contact matrix for grounding a ceramic component during electrical discharge machining

Citations (1)

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Publication number Priority date Publication date Assignee Title
US20100303625A1 (en) * 2009-05-27 2010-12-02 Craig Miller Kuhne Recovery tip turbine blade

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RU2093304C1 (ru) * 1995-12-28 1997-10-20 Всероссийский научно-исследовательский институт авиационных материалов Охлаждаемая лопатка турбины и способ ее получения
US6637500B2 (en) * 2001-10-24 2003-10-28 United Technologies Corporation Cores for use in precision investment casting
FR2889088B1 (fr) * 2005-07-29 2008-08-22 Snecma Noyau pour aubes de turbomachine
FR2900850B1 (fr) * 2006-05-10 2009-02-06 Snecma Sa Procede de fabrication de noyaux ceramiques de fonderie pour aubes de turbomachine
FR2943092B1 (fr) * 2009-03-13 2011-04-15 Snecma Aube de turbine avec un trou de depoussierage en base de pale
FR2961552B1 (fr) * 2010-06-21 2014-01-31 Snecma Aube de turbine a cavite de bord d'attaque refroidie par impact
FR2986982A1 (fr) * 2012-02-22 2013-08-23 Snecma Ensemble de noyau de fonderie pour la fabrication d'une aube de turbomachine, procede de fabrication d'une aube et aube associes
FR2990367B1 (fr) * 2012-05-11 2014-05-16 Snecma Outillage de fabrication d'un noyau de fonderie pour une aube de turbomachine
FR3021697B1 (fr) * 2014-05-28 2021-09-17 Snecma Aube de turbine a refroidissement optimise
WO2015195110A1 (en) * 2014-06-18 2015-12-23 Siemens Energy, Inc. Turbine blade investment casting using film hole protrusions for integral wall thickness control

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100303625A1 (en) * 2009-05-27 2010-12-02 Craig Miller Kuhne Recovery tip turbine blade

Also Published As

Publication number Publication date
CN108698117B (zh) 2020-08-21
FR3047767A1 (fr) 2017-08-18
WO2017137709A1 (fr) 2017-08-17
CA3014022A1 (fr) 2017-08-17
US20190022743A1 (en) 2019-01-24
RU2745073C2 (ru) 2021-03-18
RU2018132349A3 (de) 2020-04-17
BR112018016416B1 (pt) 2023-03-07
CA3014022C (fr) 2023-12-05
US10537935B2 (en) 2020-01-21
EP3414031A1 (de) 2018-12-19
CN108698117A (zh) 2018-10-23
RU2018132349A (ru) 2020-03-12
BR112018016416A2 (pt) 2018-12-26
FR3047767B1 (fr) 2019-05-31

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