WO2016001564A1 - Procédé de fabrication d'un noyau pour le moulage d'une aube - Google Patents
Procédé de fabrication d'un noyau pour le moulage d'une aube Download PDFInfo
- Publication number
- WO2016001564A1 WO2016001564A1 PCT/FR2015/051775 FR2015051775W WO2016001564A1 WO 2016001564 A1 WO2016001564 A1 WO 2016001564A1 FR 2015051775 W FR2015051775 W FR 2015051775W WO 2016001564 A1 WO2016001564 A1 WO 2016001564A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- ceramic sheet
- ceramic
- core
- mold
- blade
- Prior art date
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
- B22C1/00—Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds
-
- 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
- B22C9/103—Multipart cores
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/12—Treating moulds or cores, e.g. drying, hardening
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D25/00—Special casting characterised by the nature of the product
- B22D25/02—Special casting characterised by the nature of the product by its peculiarity of shape; of works of art
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B28—WORKING CEMENT, CLAY, OR STONE
- B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
- B28B1/00—Producing shaped prefabricated articles from the material
- B28B1/24—Producing shaped prefabricated articles from the material by injection moulding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B28—WORKING CEMENT, CLAY, OR STONE
- B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
- B28B11/00—Apparatus or processes for treating or working the shaped or preshaped articles
- B28B11/04—Apparatus or processes for treating or working the shaped or preshaped articles for coating or applying engobing layers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B28—WORKING CEMENT, CLAY, OR STONE
- B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
- B28B3/00—Producing shaped articles from the material by using presses; Presses specially adapted therefor
- B28B3/02—Producing shaped articles from the material by using presses; Presses specially adapted therefor wherein a ram exerts pressure on the material in a moulding space; Ram heads of special form
- B28B3/025—Hot pressing, e.g. of ceramic materials
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/0072—Heat treatment
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
- C04B41/5024—Silicates
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
- C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
- C04B41/5025—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials with ceramic materials
- C04B41/5035—Silica
-
- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
- C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
- C04B41/81—Coating or impregnation
- C04B41/85—Coating or impregnation with inorganic materials
- C04B41/87—Ceramics
-
- 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
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
Definitions
- the present invention relates to a method of manufacturing a core intended to be used for molding a blade of a turbomachine.
- the thickness of the trailing edge of the blades depends on the one hand on the thickness of the trailing edge slot through which the cooling air circuit of the blade opens and on the other hand with the thickness of the two metal walls of the dawn, arranged on both sides of the trailing edge slot.
- a reduction in the thickness of the trailing edge of the vanes can be achieved by decreasing the thickness of the trailing edge slot.
- this decrease in the thickness of the trailing edge slot necessitates a reduction in the thickness of the ceramic core traditionally used in the molding of the blade.
- such a reduction in thickness poses problems of fragility of the core used for the manufacture of the blades. Indeed, the cores used to mold the vanes of turbojets are very fragile during their manufacture.
- the cores for blade molding are generally manufactured by the following steps:
- the core obtained in the previous step is used to mold a dawn.
- the presence of the core allows to create a cavity in the thickness of the blade, thus allowing a circulation of air inside the dawn.
- cracks can be created during the handling of the cores between the exit of the mold and the cooking, since the cores are then in a transient state between a viscous state required for the injection and a solid state following the cooking making them particularly fragile, particularly at the level of the thin zone.
- cracker is meant the step of baking together the ceramic sheet and the ceramic paste forming the frame at a temperature such that the binder included in the sheet and the paste evaporates, which has the effect of solder them together.
- the proposed method makes it possible to reduce the thickness of the core without increasing the risk of cracking by providing sufficient flexibility to the core to solve the problems of cracking due to their handling, without increasing the number of steps in the process.
- the method comprises a preliminary step of cutting recess patterns in the ceramic sheet.
- the recess patterns are of rectangular, triangular and / or sinusoidal shape.
- the space between the recess patterns is less than 5 millimeters.
- the ceramic sheet comprises silica and alumina.
- the ceramic paste in which the frame is formed comprises silica and zircon.
- the ceramic sheet has a Young's modulus less than 5 GigaPascals.
- the ceramic sheet has a thickness of between 0.04 millimeters and 0.5 millimeters.
- the invention in another aspect, relates to a method of manufacturing a core for molding a blade of a turbomachine, comprising steps of: - cutting at least one recess pattern in a flexible ceramic sheet;
- the invention relates to a method for manufacturing a turbomachine blade comprising at least one step consisting in:
- the invention relates to a turbomachine comprising a blade manufactured according to a manufacturing method as defined above.
- FIG. 1 is a logic diagram illustrating steps of a method of manufacturing a core according to a first embodiment of the invention
- - Figures 2a and 2b each show a pattern of molding ceramic paste around a ceramic sheet
- - Figures 3a and 3b each show a pattern of molding ceramic paste around a ceramic sheet in which the deformation of the ceramic sheet is schematized
- FIG. 4a, 4b and 4c each show a ceramic sheet in which patterns have been cut according to a second embodiment of the invention
- FIG. 5 is a logic diagram illustrating steps of a method of manufacturing a core according to another aspect of the invention. DETAILED DESCRIPTION OF A MODE OF IMPLEMENTATION
- the method of manufacturing a core for the manufacture of a blade of a turbomachine according to the first embodiment of the invention comprises steps from:
- the method according to the first embodiment makes it possible to reduce the minimum thickness of the core to the thickness of the ceramic sheet 1 used, and to locally increase the thickness of the core by the injections of frames ceramic. In this way, it is possible to reduce the minimum thickness of the core to a thickness of about 0.04 mm, a thickness now achievable with ceramic sheets.
- the thickness of the ceramic sheet is between 0.04 mm and 0.5 mm.
- the method according to the first embodiment also makes it possible, by injecting frames 3 made of ceramic paste around the ceramic sheet 1, to solve the problems of cracking due to handling before cooking.
- the ceramic sheet 1 is flexible enough to withstand this manipulation, unlike a thin zone made according to a standard injection method.
- the ceramic sheet 1 has a Young's modulus of less than 5 GPa, in order to have flexibility to resist the stresses encountered during handling before cooking.
- the method according to the first implementation mode also makes it possible to solve the problems of cracks occurring during firing due to problems occurring during the injection step, by substituting the injection of ceramic paste in a thin zone by The ceramic sheet 1, thanks to its flexibility, adapts to the shape of the mold 2.
- the ceramic sheet to a lower Young's modulus at 5 GPa, thus allowing the ceramic sheet 1 to have sufficient flexibility to adapt to complex shapes in order to be able to realize a complex cavities structure inside the dawn.
- the method according to the first embodiment also makes it possible to limit the number of manufacturing steps, and thus to limit the cost of manufacture. Indeed, by injecting 3 ceramic paste frames around the ceramic sheet 1 while the ceramic sheet 1 is shaped in the mold 2, the ceramic sheet 1 does not return to its original shape and keeps the shape imposed by the mold 2. In addition, such a method also makes it possible to eliminate the assembly step after firing of several cores, forming at the outlet of the mold 2 a core whose shape corresponds to the desired final shape, and baking the core thus obtained by cofinding the ceramic sheet 1 and ceramic frames 3.
- the manufacturing method comprises a step (b ') of cutting recess patterns 41, 42, 43 in the ceramic sheet 1, carried out before the step (b) of shaping in the mold 2.
- These recess patterns 41, 42, 43 make it possible to create a core with a network of recesses. After the foundry process, these recesses correspond to dawn metal zones, and the ceramic core to internal cavities of dawn.
- the realization of the recess patterns 41, 42, 43 makes it possible to create a cavity circuit in the blade, the ceramic core being the perfect negative of this cavity circuit.
- the current cutting techniques allow to make recess patterns 41, 42, 43 whose size may be less than 5 mm, and whose spacing between each pattern of course 41, 42, 43 may be less than 5 mm . It is then possible to produce metal layers (corresponding to the recess patterns 41, 42, 43) of a size less than 5 mm disposed on either side of trailing edge slots whose width is less than 5 mm (corresponding to the spaces between the recess patterns 41, 42, 43).
- a first recess pattern 41, 42, 43 may be rectangular in shape.
- a second pattern of course 42, as shown in Figure 4b, may be triangular.
- a third pattern of course 43, as shown in Figure 4c, may be sinusoidal.
- the manufacturing process is carried out according to the first or second embodiment using a ceramic sheet 1 comprises a mixture of silica and alumina, and frames 3 into a paste ceramic comprising a mixture of silica and zircon.
- a ceramic sheet 1 comprises a mixture of silica and alumina, and frames 3 into a paste ceramic comprising a mixture of silica and zircon.
- a core made according to the third implementation therefore has good rigidity thanks to the alumina-based ceramic sheet which, once fired, forms a rigid core, and is both easy to remove chemically because by dissolving the ceramic based on zircon, the alumina ceramic sheet is no longer supported and is more easily removed from the interior of the blade.
- the method of manufacturing a ceramic core for a blade of a turbomachine comprises the following steps:
- This method makes it possible to obtain a core whose minimum thickness (for example the trailing edge thickness) is particularly fine (from 0.04 mm to 0.5 mm), and whose recess patterns 41, 42 , 43 allow, eventually, to create a complex circuit of cavities inside the blade which will be molded from this core.
- the complex circuit of cavities inside the blade serving, once the molded dawn and in operation, to circulate air to cool the dawn and avoid merging.
- Other embodiments are possible, such as for example the use of several ceramic sheets 1 to make the same core, the use of other ceramic compositions, or the cutting of recess patterns of different shapes.
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/323,300 US9981308B2 (en) | 2014-06-30 | 2015-06-29 | Method for manufacturing a core for moulding a blade |
GB1622359.6A GB2541847B (en) | 2014-06-30 | 2015-06-29 | Method for manufacturing a core for moulding a blade |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1456168 | 2014-06-30 | ||
FR1456168A FR3022810B1 (fr) | 2014-06-30 | 2014-06-30 | Procede de fabrication d'un noyau pour le moulage d'une aube |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2016001564A1 true WO2016001564A1 (fr) | 2016-01-07 |
Family
ID=52273211
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2015/051775 WO2016001564A1 (fr) | 2014-06-30 | 2015-06-29 | Procédé de fabrication d'un noyau pour le moulage d'une aube |
Country Status (4)
Country | Link |
---|---|
US (1) | US9981308B2 (fr) |
FR (2) | FR3022810B1 (fr) |
GB (1) | GB2541847B (fr) |
WO (1) | WO2016001564A1 (fr) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10280761B2 (en) * | 2014-10-29 | 2019-05-07 | United Technologies Corporation | Three dimensional airfoil micro-core cooling chamber |
GB201610783D0 (en) * | 2016-06-21 | 2016-08-03 | Rolls Royce Plc | Trailing edge ejection cooling |
EP3476820A4 (fr) * | 2016-06-23 | 2019-12-25 | Adamant Namiki Precision Jewel Co., Ltd. | Composite céramique et procédé de production d'un composite céramique |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2785836A1 (fr) * | 1998-11-12 | 2000-05-19 | Snecma | Procede de fabrication de noyaux ceramiques minces pour fonderie |
EP1652603A2 (fr) * | 2004-10-29 | 2006-05-03 | United Technologies Corporation | Noyaux pour la moulage de précision et procédés |
EP1671720A1 (fr) * | 2004-12-20 | 2006-06-21 | Howmet Corporation | Noyau de coulée céramique et méthode de production associée |
EP1854569A1 (fr) * | 2006-05-10 | 2007-11-14 | Snecma | Procédé de fabrication de noyaux céramiques de fonderie pour aubes de turbomachine |
EP2335845A1 (fr) * | 2009-12-04 | 2011-06-22 | United Technologies Corporation | Moulages, noyaux de moulage et procédés |
EP2468433A2 (fr) * | 2010-12-22 | 2012-06-27 | United Technologies Corporation | Mini-coeur de perçage vers flux |
WO2013167847A2 (fr) * | 2012-05-11 | 2013-11-14 | Snecma | Outillage de fabrication d'un noyau de fonderie pour une aube de turbomachine |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6720028B1 (en) * | 2001-03-27 | 2004-04-13 | Howmet Research Corporation | Impregnated ceramic core and method of making |
US7014424B2 (en) * | 2003-04-08 | 2006-03-21 | United Technologies Corporation | Turbine element |
US20050087319A1 (en) * | 2003-10-16 | 2005-04-28 | Beals James T. | Refractory metal core wall thickness control |
-
2014
- 2014-06-30 FR FR1456168A patent/FR3022810B1/fr active Active
- 2014-12-19 FR FR1463016A patent/FR3022812B1/fr active Active
-
2015
- 2015-06-29 WO PCT/FR2015/051775 patent/WO2016001564A1/fr active Application Filing
- 2015-06-29 US US15/323,300 patent/US9981308B2/en active Active
- 2015-06-29 GB GB1622359.6A patent/GB2541847B/en active Active
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2785836A1 (fr) * | 1998-11-12 | 2000-05-19 | Snecma | Procede de fabrication de noyaux ceramiques minces pour fonderie |
EP1652603A2 (fr) * | 2004-10-29 | 2006-05-03 | United Technologies Corporation | Noyaux pour la moulage de précision et procédés |
EP1671720A1 (fr) * | 2004-12-20 | 2006-06-21 | Howmet Corporation | Noyau de coulée céramique et méthode de production associée |
EP1854569A1 (fr) * | 2006-05-10 | 2007-11-14 | Snecma | Procédé de fabrication de noyaux céramiques de fonderie pour aubes de turbomachine |
EP2335845A1 (fr) * | 2009-12-04 | 2011-06-22 | United Technologies Corporation | Moulages, noyaux de moulage et procédés |
EP2468433A2 (fr) * | 2010-12-22 | 2012-06-27 | United Technologies Corporation | Mini-coeur de perçage vers flux |
WO2013167847A2 (fr) * | 2012-05-11 | 2013-11-14 | Snecma | Outillage de fabrication d'un noyau de fonderie pour une aube de turbomachine |
Also Published As
Publication number | Publication date |
---|---|
US9981308B2 (en) | 2018-05-29 |
FR3022810B1 (fr) | 2019-09-20 |
GB2541847B (en) | 2018-09-19 |
FR3022810A1 (fr) | 2016-01-01 |
GB2541847A (en) | 2017-03-01 |
GB201622359D0 (en) | 2017-02-15 |
FR3022812B1 (fr) | 2019-09-20 |
US20170151604A1 (en) | 2017-06-01 |
FR3022812A1 (fr) | 2016-01-01 |
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