WO2014057187A1 - Method for brazing parts made from silicon carbide material with holding clamping members having anti-wetting properties - Google Patents

Method for brazing parts made from silicon carbide material with holding clamping members having anti-wetting properties Download PDF

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Publication number
WO2014057187A1
WO2014057187A1 PCT/FR2013/052315 FR2013052315W WO2014057187A1 WO 2014057187 A1 WO2014057187 A1 WO 2014057187A1 FR 2013052315 W FR2013052315 W FR 2013052315W WO 2014057187 A1 WO2014057187 A1 WO 2014057187A1
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WO
WIPO (PCT)
Prior art keywords
parts
assembly
brazing
orifices
sic
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Application number
PCT/FR2013/052315
Other languages
French (fr)
Inventor
Guilhem Roux
Valérie CHAUMAT
Eric Conete
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Commissariat A L'energie Atomique Et Aux Energies Alternatives
Herakles
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Publication of WO2014057187A1 publication Critical patent/WO2014057187A1/en

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
    • B23K1/0012—Brazing heat exchangers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K1/00—Soldering, e.g. brazing, or unsoldering
    • B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/16—Composite materials, e.g. fibre reinforced
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/16—Composite materials, e.g. fibre reinforced
    • B23K2103/166—Multilayered materials
    • B23K2103/172—Multilayered materials wherein at least one of the layers is non-metallic
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/50—Inorganic material, e.g. metals, not provided for in B23K2103/02 – B23K2103/26
    • B23K2103/52—Ceramics

Definitions

  • the invention relates to the soldering assembly of parts made of silicon carbide (SiC) material, that is to say parts made of a material comprising at least 50% by weight of silicon carbide up to parts made entirely of SiC.
  • SiC silicon carbide
  • the SiC-based materials may be in the form of silicon carbide fibers or silicon carbide powder sintered or bonded by a ceramic binder. These SiC-based materials may be in particular pure silicon carbide such as pure silicon carbide a (SiCa) or ⁇ (SiC), silicon carbide substrates infiltrated with silicon (Si / SiC), or composite materials SiC such as fiber composite materials and / or silicon-carbide matrix (composite SiC f / SiC or C f / SiC).
  • Brazing is an inexpensive and easy to implement technique.
  • Parts of complex shape can be made by assembling sub-elements by soldering, soldering operations are limited to placing a solder composition between the parts to be assembled (soldering type "sandwich") or close (soldering type " capillary ") of the solder joint to be made between the two parts and to melt this composition by heating at a temperature above its melting point.
  • the brazed solder composition will fill the brazing area on which the solder joint is to be formed. In the case of brazing in capillary configuration, it is necessary that the solder composition wets well, and therefore spreads well on the faces of the parts to be assembled to fill by capillarity the soldering zone.
  • solder After cooling, the solder solidifies to form a solder joint ensuring the cohesion of the assembly. It is known that it is difficult to assemble large ceramic parts, in particular SiC. In fact, the tolerances after sintering of the primary or massive silicon carbide components of large dimensions are poorly controlled and the machining of these components is unacceptable for reasons of cost.
  • tools can be used to better conform the parts to be assembled and avoid undesirable movements during the brazing cycle.
  • These tools are always external and are intended to apply a pressure force during the brazing cycle, using gravity (weights) or a tightening force (clamp, screw support).
  • these tools must have a creep limited to the temperature of development of the solder, to avoid a loss of support force hot. In addition, these tools must not react with the silicon carbide solder material. Ceramics (silicon carbide, graphite, alumina, mullite, etc.) as well as certain metals (molybdenum, TZM, etc.) can be used.
  • the aim of the invention is to provide a method for soldering between silicon carbide material parts which does not have the abovementioned disadvantages and which makes it possible in particular to accurately produce brazed bonds of good quality, and without having to machine the parts assembling parts and without resorting to tools of external maintenance.
  • the method further comprises a step of forming a plurality of orifices in the assembly portions of the first and second parts, the orifices being formed at predetermined positions to align the orifices of the portion of the assembling the first piece with the orifices of the assembly portion of the second piece during the docking step and in that a member of a clamping member is introduced into each pair of screw holes each clamping member applying a clamping force between the assembly portions, in that the elements of the clamping members are made of an anti-wetting material with respect to the solder composition or coated with an anti-wetting material with respect to the solder composition.
  • the method of the invention makes it possible to maintain the parts in a precise position during their brazing and thus to form a brazed connection of good quality ensuring the presence of a solder joint over the entire assembly area defined between the parts.
  • the elements of the clamping members being made of a material which is anti-wetting with respect to the solder composition or coated with such a material, these can be removed easily after soldering and can be optionally replaced by fixing members having a structure and / or a nature of material adapted to the conditions of use of the assembled parts.
  • the invention makes it possible to solve problems such as aerodynamic problems in the final assembly or temperature behavior when the clamping members used during soldering are not not adapted to withstand the operating temperatures of the assembly.
  • the nondestructive removal of the clamping members permitted by the invention has advantages over removal of the latter by machining or etching. Indeed, the elimination of the clamping members by machining or etching is a delicate and complex operation because it does not damage the brazed parts or weaken the brazed connection. In addition, the removal of these bodies by machining or etching leads to their destruction while with the method of the invention the clamping elements can be reused after brazing.
  • the soldering step comprises a heat treatment carried out at a soldering temperature capable of liquefying the solder composition, the elements of the clamping members having a creep temperature greater than the temperature of the solder. brazing.
  • spacers having a predetermined height are interposed between the assembly portions, each spacer being traversed by a clamping element.
  • the use of spacers makes it possible to correct the surface variations of the assembly portions in the brazing zone and to ensure a minimum thickness of the solder joint. This ensures the presence of a continuous solder joint over the entire brazing area, which avoids interruptions in the seal that can weaken the brazed connection.
  • the method of the invention comprises a step of interposing capillary elements between the assembly portions of the first and second parts and a step of placing a solder composition in contact with a part capillary elements.
  • These capillary elements allow the liquefied solder composition to spread over the entire brazing area and provide a thicker solder joint.
  • the capillary elements can be chosen from at least one of the following elements: SiC particles, SiC web, carbon matrix, carbon particles and carbon nanotubes.
  • the parts manufactured with the assembly method of the invention may in particular correspond to aircraft engine body parts or to heat exchangers.
  • FIG. 1 is a diagrammatic exploded perspective view of two pieces of ceramic matrix composite material intended to be soldered in accordance with one embodiment of the invention
  • Figures 2 and 3 are respectively a schematic perspective view and a schematic partial sectional view showing the two parts of Figure 1 ready to be soldered;
  • Figure 4 is a schematic partial sectional view showing the parts of Figure 3 after brazing
  • FIG. 5 is a schematic partial sectional view showing the parts of Figure 4 after removal of the clamping members;
  • FIGS. 6 and 7 are respectively a diagrammatic view in partial section and in perspective showing the parts of FIG. 5 after placement of definitive fasteners,
  • FIG. 8 is a photograph showing two plates of SiC / SiC composite material intended to be brazed using a clamping member
  • FIG. 9 is a photograph showing the plates of FIG. 8 ready to be brazed together
  • FIG. 10 is a curve of the thermal brazing cycle applied to the plates of FIG. 9,
  • FIG. 11 is a photograph showing the plates of Figure 9 after soldering.
  • the solder assembly method according to the present invention is particularly, but not exclusively, applicable to ceramic materials and in particular based on silicon carbide.
  • material based on silicon carbide is meant a material whose SiC content is greater than or equal to 50% by weight, preferably greater than or equal to 80% by weight, or even 100% by weight.
  • SiC-based materials considered here is in particular the ceramic matrix thermostructural composite material (CMC), that is to say any material formed of a reinforcement of refractory fibers (carbon or ceramic) densified by a matrix at less partially SiC, such as C / SiC, SiC / SiC, C / C-SiC, etc.
  • CMC ceramic matrix thermostructural composite material
  • the structures manufactured according to the assembly method of the invention correspond in particular to sets of rear bodies of aircraft engines or to heat exchangers.
  • Figure 1 shows a first part consisting of a shell 10 and a second part consisting of a cone 20 which are intended to form, once assembled together, a central body or exhaust cone, also called "plug".
  • the ferrule 10 and the cone 20 are made of SiC / SiC material, namely a material comprising a SiC fiber reinforcement densified by an SiC matrix.
  • the ferrule 10 comprises an assembly portion 11 which is intended to be assembled by brazing with an assembly portion 21 of the cone 20.
  • a plurality of orifices 110 have been formed in the assembly portion 11 of the ferrule 10 while another plurality of orifices 210 have been formed in the assembly portion 21 of the cone 20.
  • the orifices 110 and 210 are formed on the assembly portions 11 and 21 at locations determined so as to coincide with each other during the docking of the assembly portions as described below.
  • the orifices 110 and 210 may be pierced directly into the parts after manufacture or be made during manufacture thereof by inserting inserts into the fibrous reinforcement at the locations of the orifices and removing the inserts after densification of the reinforcement.
  • the orifices 110 and 210 may be obtained by simultaneous drilling of the ferrule 10 and the cone 20 held in their assembly position.
  • the number and the distribution of the orifices are determined according to the maintenance and the necessary tightening to be applied during brazing.
  • the orifices are further intended to be used to strengthen or secure the connection after brazing, the number and positioning of the orifices on the parts are also determined according to the dimensioning and mechanical characteristics of the assembly.
  • clamping members 30 each consisting of a screw 31 and a nut 32 made of graphite are used to hold the assembly portions 11 and 21 respectively of the shell 10 and the cone 20 in their docking position and to apply a clamping force on these portions during brazing.
  • a screw 31 is inserted into each pair of orifices 110 and 210 vis-à-vis when the assembly portion 11 of the shell 10 is placed in its position d the coupling with the assembly portion 21 of the cone 20.
  • the holding in position and the clamping force to conform the assembly portions of the parts together are provided by tightening a nut 32 on each screw 31.
  • the clamping members 30 are intended to be removed after brazing.
  • the screws and nuts may be covered with an anti-wetting agent such as boron nitride (BN).
  • an anti-wetting agent such as boron nitride (BN).
  • the screws and nuts can be made directly from an anti-wetting material vis-à-vis the solder composition.
  • spacers 33 are further placed between the assembly portions 11 and 21 at the clamping members 30 (FIGS. 1 and 3).
  • Each spacer 33 has a central bore 330 allowing the passage of a screw 31 which maintains the position of the spacer.
  • each spacer 33 has a determined height H (FIG. 3).
  • H the height of the spacers 33 may all have the same height which makes it possible to adjust the thickness of the solder joint obtained.
  • the height of each spacer is determined so as to maintain a substantially uniform spacing between the assembly portions over the entire brazing zone so as to obtain a substantially uniform solder joint thickness and to guarantee a uniform good liaison.
  • the brazing is carried out by adding solder to the soldering zone 40, that is to say the overlap portion between the assembly portions 11 and 21.
  • a composition of solder 41 in the form of a solid paste is placed on the outer surface of the cone 20 near the assembly portion 21 and in contact with the edge 11b of the assembly portion 11 of the shell 10.
  • the edge 11b can be coated with an anti-wetting agent to prevent the solder composition from penetrating into the material at this location and thus promote its distribution in the brazing zone 40.
  • Capillary elements for example SiC grains, can also be arranged in the docking zone to facilitate the transport and diffusion of the liquefied solder between the assembly portions 11 and 21 during the soldering step.
  • Other capillary elements such as in particular an SiC web, a carbon mat, carbon particles or carbon nanotubes can be used.
  • solder is made in particular as a function of its compatibility with the composite material of the parts to be assembled, that is to say that a non-reactive or non-reactive composition is preferably chosen.
  • silicon-based compositions as described in documents EP 806 402, US Pat. No. 5,975,407, US 2008/190552 and US Pat. No. 7,497,918 will be used for alloys of silicon + metal silicides, silicon + germanium, whether or not alloyed, as well as metal compositions known under the trade name Cusil-ABA®, Ticusil®, Incusil® or Brasic®.
  • compositions corresponding to mixtures of oxides chosen from the following oxides: SiO 2 , Al 2 O 3 , MgO and CaO.
  • the following step consists in implementing the brazing cycle by raising the temperature until the solder composition 41 is liquid, which is then distributed over the brazing zone 40 present between the two assembly portions 11 and 21.
  • solder joint 42 is obtained in contact with the faces 11a and 21a of the assembly portions 11 and 21 respectively of the ferrule 10 and the cone 20 as illustrated schematically in FIG. 4.
  • the clamping members 30 are then removed ( Figure 5) to be replaced by final fasteners 50 ( Figure 6) adapted to the conditions in which the piece obtained (plug) is intended to be used.
  • the fasteners 50 are constituted here rivets 51 of stainless metal.
  • the fasteners, or the clamping members when held after brazing strengthen the connection between the parts and improve the mechanical strength of the assembly.
  • an exhaust cone or plug 100 consisting of the shell 10 and the cone 20 bonded together by the solder joint 42 and the fasteners 50 is obtained.
  • Example 1 Examples of solder assembly were made in accordance with the method of the invention.
  • This example describes the preparation and the production of bonds brazed between two composite parts, more precisely composite SiC / SiC (SiC matrix and SiC fibers) each pierced with a hole of 5 mm, by implementing the method of brazing according to the invention, that is to say using clamping members during brazing.
  • the parts to be soldered are two plates 60, 61 of SiC / SiC composite material each respectively drilled with a hole 600 and 610 ( Figure 8).
  • Such a composite material is available from Snecma Propulsion Solid under the name Cerasep A40C®.
  • solder composition consisting of 58 atomic% silicon (Si), 32 atomic% nickel (Ni), and 10 atomic% aluminum (Al).
  • the amount of solder composition placed at the edge of the brazing zone is 929.2 mg.
  • the solder composition (58 atomic% Si, 32 atomic% Ni, and 10 atomic% Al) was prepared from pieces of Si, pieces of Ni, and pieces of pure Al. These pieces were weighed respecting the proportions of the solder composition and placed in an alumina crucible. The assembly was placed in a graphite furnace and subjected to a thermal cycle with a plateau at 1300 ° C. under secondary vacuum for 30 minutes. Thus, after cooling, an ingot. This ingot is crushed to obtain a powder. An organic binder, for example a NICROBRAZ® type cement, has been added to this powder mixture to form a viscous solder composition. The parts are cleaned with acetone then with ethanol and finally dried.
  • NICROBRAZ® type cement for example a NICROBRAZ® type cement
  • the parts 60 and 61 are brought into contact so as to define a brazing zone 62 defined by the portions of the plates 60 and 61 facing one another.
  • the plate 60 has a part 60a which protrudes 5 mm outside the brazing zone 62 and on which a solder composition 63 has been deposited. corresponding to the viscous solder composition described above (this configuration is called the capillary configuration).
  • Solder composition 63 is deposited with a spatula on portion 60a in the form of a solder bead (FIG. 9) having a mass of 929.2 mg.
  • a clamping member 70 consisting of a screw 71 and a nut 72, coated with an anti-wetting agent such as BN, was used to apply a clamping force between the two plates.
  • the screw 71 was introduced into the holes 600 and 610 vis-a-vis, the tightening of the nut 72 ensuring the application of the clamping force between the two plates ( Figure 9).
  • the assembly was then placed in a secondary vacuum brazing furnace (graphite furnace) and subjected to a vacuum brazing heat cycle which includes a first 180-minute plateau at 980 ° C followed by a second plateau of 60 ° C. minutes at 1100 ° C, which is the soldering bearing (Figure 10).
  • an assembly 70 formed of two plates 60 and 61 which are interconnected by a solder joint 64.
  • the screw After brazing, the screw is removed without difficulty despite the presence of the solder joint to the edge of the holes 600 and 610.
  • the brazed connection obtained is of good quality with a filling ratio of the solder zone of 95% (controlled by tomography).
  • This example differs from Example 1 described above in that SiC particles are interposed between the two plates prior to soldering in order to produce a thicker solder joint than in Example 1.
  • the plates used here are of the same nature and dimensions as the plates 60 and 61 described above.
  • the solder composition used is also identical in constitution (58 atomic% Si powder, 32 atomic% Ni, and 10 atomic% Al bound in NICROBRAZ® type cement) to that used in Example 1.
  • SiC particles having a particle size of about 50 ⁇ . These particles were heat-treated at 1460 ° C under a secondary vacuum for two hours.
  • the SiC particles are stored under argon until they are used.
  • the SiC particles are bonded to each other by an organic binder such as a NICROBRAZ® type cement, which makes it possible to obtain a paste that is easy to deposit on the plates.
  • an organic binder such as a NICROBRAZ® type cement, which makes it possible to obtain a paste that is easy to deposit on the plates.
  • the amount of particles deposited with a spatula is 229 mg, this amount being distributed between the two plates by exceeding the brazing zone at the portion of the plate that protrudes from the brazing zone and on which the solder composition is filed.
  • the amount of solder composition, deposited in bead form with a spatula is 826 mg.
  • a clamping member identical to that already described in Example 1 is used to apply a clamping force between the two plates.
  • the assembly is then placed in a brazing furnace (graphite furnace) under secondary vacuum and subjected to a thermal brazing cycle identical to that described in Example 1.
  • a brazing furnace graphite furnace
  • the brazed bond obtained is of good quality with a filling rate of the solder zone of 83% (controlled by tomography).

Abstract

The present application describes a brazing method for assembling a first part (10) and a second part (20) made from silicon carbide material, the first and second parts (10, 20) each comprising an assembly portion (11; 21) intended to be brazed with the assembly portion (21; 11) of the other part. The method comprises clamping together the assembly portions (11, 21) of the first and second parts (10, 20), interposing a brazing composition (41) between the assembly portions or close to said assembly portions, and brazing the assembly portions. The method further comprises a step of forming a plurality of ports (110, 210) in the assembly portions (11, 21) of the first and second parts. The ports are formed at predefined positions so as to align the ports (110) of the assembly portion (11) of the first part (10) with the ports (210) of the assembly portion (21) of the second parts (20) during the clamping step. An element (31) of a clamping member (30) is inserted through each pair of opposing ports (110, 210), each clamping member (30) applying a clamping force between the assembly portions (11, 21).

Description

PROCEDE DE BRASAGE DE PIECES EN MATERIAU A BASE DE CARBURE DE SILICIUM AVEC DES ORGANES DE SERRAGE DE MAINTIEN AYANT DES PROPRIETES METHOD FOR BRAZING SILICON CARBIDE MATERIAL PARTS WITH MAINTAINING CLAMPING DEVICES HAVING PROPERTIES
ANTI-MOUILLAGE ANTI-TACKLE
Arrière-plan de l'invention Background of the invention
L'invention concerne l'assemblage par brasage de pièces en matériau à base de carbure de silicium (SiC), c'est-à-dire des pièces en un matériau comprenant au moins de 50% en masse de carbure de silicium jusqu'à des pièces entièrement constituées de SiC. The invention relates to the soldering assembly of parts made of silicon carbide (SiC) material, that is to say parts made of a material comprising at least 50% by weight of silicon carbide up to parts made entirely of SiC.
Les matériaux à base de SiC peuvent se présenter sous la forme de fibres de carbure de silicium ou de poudre de carbure de silicium frittée ou liée par un liant en céramique. Ces matériaux à base de SiC peuvent être notamment du carbure de silicium pur tel que du carbure de silicium pur a (SiCa) ou β (SiC ), des substrats en carbure de silicium infiltré de silicium (Si/SiC), ou des matériaux composites à base de SiC tels que des matériaux composites à fibres et/ou à matrice de carbure de silicium (composites SiCf/SiC ou Cf/SiC). The SiC-based materials may be in the form of silicon carbide fibers or silicon carbide powder sintered or bonded by a ceramic binder. These SiC-based materials may be in particular pure silicon carbide such as pure silicon carbide a (SiCa) or β (SiC), silicon carbide substrates infiltrated with silicon (Si / SiC), or composite materials SiC such as fiber composite materials and / or silicon-carbide matrix (composite SiC f / SiC or C f / SiC).
Lors de la formation de pièces en matériau à base de SiC, il est fréquent de réaliser celles-ci à partir d'éléments en matériau à base de SiC indépendants qui sont assemblés entre eux par brasage, en particulier dans le cadre de la fabrication de pièces de grandes dimensions et/ou de géométrie complexe.  When forming parts of SiC-based material, it is common practice to make them from elements made of independent SiC material which are assembled together by brazing, particularly in the context of the manufacture of parts of large dimensions and / or complex geometry.
Le brasage est une technique peu coûteuse et facile à mettre en œuvre. Des pièces de forme complexe peuvent être réalisées par assemblage de sous-éléments par brasage, les opérations de brasage se limitent à placer une composition de brasure entre les pièces à assembler (brasage de type « sandwich ») ou à proximité (brasage de type « capillaire ») du joint de brasure à réaliser entre les deux pièces et à faire fondre cette composition par chauffage à une température supérieure à son point de fusion. La composition de brasure ainsi fondue va remplir la zone brasage sur laquelle le joint de brasure doit être formé. Dans le cas du brasage en configuration capillaire, il est nécessaire que la composition de brasure mouille bien, et donc s'étale bien, sur les faces des pièces à assembler pour remplir par capillarité la zone de brasage. Après refroidissement, la brasure se solidifie pour former un joint de brasure assurant la cohésion de l'assemblage. On sait qu'il est difficile d'assembler des pièces de grandes dimensions en céramique, en particulier en SiC. En effet, les tolérances après frittage des composants primaires ou massifs en carbure de silicium de grandes dimensions sont mal maîtrisées et l'usinage de ces composants est inacceptable pour des raisons de coût. Brazing is an inexpensive and easy to implement technique. Parts of complex shape can be made by assembling sub-elements by soldering, soldering operations are limited to placing a solder composition between the parts to be assembled (soldering type "sandwich") or close (soldering type " capillary ") of the solder joint to be made between the two parts and to melt this composition by heating at a temperature above its melting point. The brazed solder composition will fill the brazing area on which the solder joint is to be formed. In the case of brazing in capillary configuration, it is necessary that the solder composition wets well, and therefore spreads well on the faces of the parts to be assembled to fill by capillarity the soldering zone. After cooling, the solder solidifies to form a solder joint ensuring the cohesion of the assembly. It is known that it is difficult to assemble large ceramic parts, in particular SiC. In fact, the tolerances after sintering of the primary or massive silicon carbide components of large dimensions are poorly controlled and the machining of these components is unacceptable for reasons of cost.
Il est donc souvent préférable, comme indiqué ci-avant, de fabriquer les pièces ou structures de grande dimension et/ou de forme complexe à partir d'éléments en céramique de forme simple et/ou de petite taille, puis d'assembler par brasage ces éléments pour réaliser la structure finale. Une telle technique est notamment nécessaire pour fabriquer des structures du type échangeur de chaleur, et des composants de structure en SiC ayant une température d'utilisation pouvant aller par exemple, jusqu'à 900°C voire 1000°C et même 1300°C.  It is therefore often preferable, as indicated above, to fabricate large and / or complex parts or structures from ceramic elements of simple shape and / or small size, and then to assemble by brazing these elements to achieve the final structure. Such a technique is in particular necessary to manufacture structures of the heat exchanger type, and SiC structure components having a use temperature of, for example, up to 900 ° C. or even 1000 ° C. and even 1300 ° C.
L'utilisation d'un matériau composite à base de SiC permet d'obtenir des pièces de géométrie complexe avec des tolérances dimensionnelles moins larges. En revanche, la présence d'un renfort fibreux et souvent de couches protectrices en surface (seal coat) rend l'usinage des faces d'assemblage impossible. Cela pose un problème pour l'opération de brasage, car pour assurer un bon remplissage et une bonne tenue du joint de brasage, il est nécessaire d'avoir une épaisseur de brasure la plus régulière et fine possible sur l'ensemble de l'interface d'assemblage.  The use of an SiC-based composite material makes it possible to obtain pieces of complex geometry with smaller dimensional tolerances. On the other hand, the presence of a fibrous reinforcement and often of protective layers on the surface (seal coat) makes the machining of the faces of assembly impossible. This poses a problem for the soldering operation, because to ensure a good filling and good resistance of the solder joint, it is necessary to have the most uniform and fine solder thickness over the entire interface. assembly.
Afin de limiter ces problèmes, des outillages peuvent être utilisés pour conformer au mieux les pièces à assembler et éviter des mouvements indésirables lors du cycle de brasage. Ces outillages sont toujours externes et ont pour but d'appliquer un effort de pression pendant le cycle de brasage, utilisant la gravité (masselottes) ou un effort de serrage (serre joint, vis d'appui).  To limit these problems, tools can be used to better conform the parts to be assembled and avoid undesirable movements during the brazing cycle. These tools are always external and are intended to apply a pressure force during the brazing cycle, using gravity (weights) or a tightening force (clamp, screw support).
Mécaniquement, ces outillages doivent avoir un fluage limité à la température d'élaboration de la brasure, afin d'éviter une perte d'effort d'appui à chaud. De plus, ces outillages ne doivent pas réagir avec le matériau à base de carbure silicium à braser. Des céramiques (carbure de silicium, Graphite, alumine, mullite,...) ainsi que certains métaux (Molybdène, TZM,...) peuvent être utilisés.  Mechanically, these tools must have a creep limited to the temperature of development of the solder, to avoid a loss of support force hot. In addition, these tools must not react with the silicon carbide solder material. Ceramics (silicon carbide, graphite, alumina, mullite, etc.) as well as certain metals (molybdenum, TZM, etc.) can be used.
Cependant, l'utilisation de tels outillages peut impacter de façon significative le coût de fabrication des pièces, notamment pour des pièces produites en petites séries comme c'est généralement le cas aujourd'hui pour les pièces de grandes dimensions. However, the use of such tools can significantly impact the cost of manufacturing parts, especially for parts produced in small series as is generally the case today for large parts.
Objet et résumé de l'invention Object and summary of the invention
L'invention a pour but de fournir un procédé permettant un assemblage par brasage entre des pièces en matériau à base de carbure de silicium qui ne présente pas les inconvénients précités et qui permet notamment de réaliser avec précision des liaisons brasées de bonne qualité, et ce sans avoir à usiner les parties d'assemblages des pièces et sans recourir à un outillage de maintien externe. The aim of the invention is to provide a method for soldering between silicon carbide material parts which does not have the abovementioned disadvantages and which makes it possible in particular to accurately produce brazed bonds of good quality, and without having to machine the parts assembling parts and without resorting to tools of external maintenance.
Ce but est atteint avec un procédé d'assemblage par brasage entre une première pièce et une deuxième pièce en matériau à base de carbure de silicium, les première et deuxième pièces comportant chacune une portion d'assemblage destinée à être brasée avec la portion d'assemblage de l'autre pièce, le procédé comprenant les étapes suivantes :  This object is achieved with a solder joining method between a first part and a second part made of silicon carbide material, the first and second parts each comprising an assembly portion intended to be brazed with the portion of silicon. assembling the other part, the method comprising the following steps:
accostage des portions d'assemblage des première et deuxième pièces, une composition de brasure étant disposée entre les portions d'assemblage ou à proximité desdites portions d'assemblage, brasage des portions d'assemblage,  docking the assembly portions of the first and second parts, a solder composition being disposed between the assembly portions or in the vicinity of said assembly portions, brazing the assembly portions,
caractérisé en ce que le procédé comprend en outre une étape de formation d'une pluralité d'orifices dans les portions d'assemblage des première et deuxième pièces, les orifices étant formés à des positions déterminées de manière à aligner les orifices de la portion d'assemblage de la première pièce avec les orifices de la portion d'assemblage de la deuxième pièce lors de l'étape d'accostage et en ce qu'un élément d'un organe de serrage est introduit dans chaque paire d'orifices en vis-à-vis, chaque organe de serrage appliquant un effort de serrage entre les portions d'assemblage, en ce que les éléments des organes de serrage sont en un matériau anti-mouillant vis-à-vis de la composition de brasure ou revêtus d'un matériau anti-mouillant vis-à-vis de la composition de brasure.  characterized in that the method further comprises a step of forming a plurality of orifices in the assembly portions of the first and second parts, the orifices being formed at predetermined positions to align the orifices of the portion of the assembling the first piece with the orifices of the assembly portion of the second piece during the docking step and in that a member of a clamping member is introduced into each pair of screw holes each clamping member applying a clamping force between the assembly portions, in that the elements of the clamping members are made of an anti-wetting material with respect to the solder composition or coated with an anti-wetting material with respect to the solder composition.
Ainsi, grâce à l'utilisation d'organes de serrage dans des orifices ménagés au niveau des portions d'assemblage des pièces, le procédé de l'invention permet de maintenir les pièces dans une position précise lors de leur brasage et de former ainsi une liaison brasée de bonne qualité assurant la présence d'un joint de brasure sur toute la zone d'assemblage définie entre les pièces. Thus, thanks to the use of clamping members in orifices formed at the portions of assembly of the parts, the method of the invention makes it possible to maintain the parts in a precise position during their brazing and thus to form a brazed connection of good quality ensuring the presence of a solder joint over the entire assembly area defined between the parts.
En outre, les éléments des organes de serrage étant en un matériau anti-mouillant vis-à-vis de la composition de brasure ou revêtus d'un tel matériau, ceux-ci peuvent être retirés facilement après brasage et peuvent être éventuellement remplacés par des organes de fixation ayant une structure et/ou une nature de matériau adaptées aux conditions d'utilisation des pièces assemblées.  In addition, the elements of the clamping members being made of a material which is anti-wetting with respect to the solder composition or coated with such a material, these can be removed easily after soldering and can be optionally replaced by fixing members having a structure and / or a nature of material adapted to the conditions of use of the assembled parts.
En prévoyant un démontage aisé des organes de serrage utilisés lors du brasage, l'invention permet résoudre des problèmes par exemple d'aérodynamisme au niveau de l'assemblage final ou de comportement en température lorsque les des organes de serrage utilisés lors du brasage ne sont pas adaptés pour supporter les températures de fonctionnement de l'assemblage.  By providing for easy disassembly of the clamping members used during brazing, the invention makes it possible to solve problems such as aerodynamic problems in the final assembly or temperature behavior when the clamping members used during soldering are not not adapted to withstand the operating temperatures of the assembly.
Par ailleurs, le retrait non destructif des organes de serrage permis par l'invention présente des avantages par rapport à un retrait de ceux-ci par usinage ou attaque chimique. En effet, l'élimination des organes de serrage par usinage ou attaque chimique est une opération délicate et complexe car il ne faut pas endommager les pièces brasées ni fragiliser la liaison brasée. En outre, le retrait de ces organes par usinage ou attaque chimique conduit à leur destruction alors qu'avec le procédé de l'invention les éléments de serrage peuvent être réutilisés après le brasage.  Furthermore, the nondestructive removal of the clamping members permitted by the invention has advantages over removal of the latter by machining or etching. Indeed, the elimination of the clamping members by machining or etching is a delicate and complex operation because it does not damage the brazed parts or weaken the brazed connection. In addition, the removal of these bodies by machining or etching leads to their destruction while with the method of the invention the clamping elements can be reused after brazing.
Selon un autre aspect du procédé de l'invention, l'étape de brasage comprend un traitement thermique réalisé à une température de brasage apte à liquéfier la composition de brasure, les éléments des organes de serrage présentant une température de fluage supérieure à la température de brasage. According to another aspect of the process of the invention, the soldering step comprises a heat treatment carried out at a soldering temperature capable of liquefying the solder composition, the elements of the clamping members having a creep temperature greater than the temperature of the solder. brazing.
Selon encore un autre aspect du procédé de l'invention, des entretoises ayant une hauteur déterminée sont interposées entre les portions d'assemblage, chaque entretoise étant traversée par un élément de serrage. L'utilisation d'entretoises permet de corriger les variations de surface des portions d'assemblage dans la zone de brasage et d'assurer une épaisseur minimum du joint de brasure. On assure ainsi la présence d'un joint de brasure continu sur toute la zone de brasage, ce qui permet d'éviter des interruptions dans le joint qui peuvent affaiblir la liaison brasée. According to yet another aspect of the method of the invention, spacers having a predetermined height are interposed between the assembly portions, each spacer being traversed by a clamping element. The use of spacers makes it possible to correct the surface variations of the assembly portions in the brazing zone and to ensure a minimum thickness of the solder joint. This ensures the presence of a continuous solder joint over the entire brazing area, which avoids interruptions in the seal that can weaken the brazed connection.
Selon un aspect du procédé de l'invention, celui-ci comprend une étape d'interposition d'éléments capillaires entre les portions d'assemblage des première et deuxième pièces et une étape de placement d'une composition de brasure en contact avec une partie des éléments capillaires. Ces éléments capillaires permettent à la composition de brasure liquéfiée de se répandre sur toute la zone de brasage et d'obtenir un joint de brasure plus épais. Les éléments capillaires peuvent être choisis parmi au moins un des éléments suivants : particules de SiC, voile de SiC, mat de carbone, particules de carbone et nanotubes de carbone.  According to one aspect of the method of the invention, it comprises a step of interposing capillary elements between the assembly portions of the first and second parts and a step of placing a solder composition in contact with a part capillary elements. These capillary elements allow the liquefied solder composition to spread over the entire brazing area and provide a thicker solder joint. The capillary elements can be chosen from at least one of the following elements: SiC particles, SiC web, carbon matrix, carbon particles and carbon nanotubes.
Les pièces fabriquées avec le procédé d'assemblage de l'invention peuvent notamment correspondre à des pièces d'arrière-corps de moteur aéronautique ou à des échangeurs de chaleur.  The parts manufactured with the assembly method of the invention may in particular correspond to aircraft engine body parts or to heat exchangers.
Brève description des dessins Brief description of the drawings
D'autres caractéristiques et avantages de l'invention ressortiront de la description suivante de modes particuliers de réalisation de l'invention, donnés à titre d'exemples non limitatifs, en référence aux dessins annexés, sur lesquels: Other characteristics and advantages of the invention will emerge from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, in which:
- la figure 1 est une vue schématique en perspective éclatée de deux pièces en matériau composite à matrice céramique destinées à être brasées conformément à un mode de réalisation de l'invention,  FIG. 1 is a diagrammatic exploded perspective view of two pieces of ceramic matrix composite material intended to be soldered in accordance with one embodiment of the invention,
- les figures 2 et 3 sont respectivement une vue schématique en perspective et une vue schématique en coupe partielle montrant les deux pièces de la figure 1 prêtes à être brasées ;  - Figures 2 and 3 are respectively a schematic perspective view and a schematic partial sectional view showing the two parts of Figure 1 ready to be soldered;
- la figure 4 est une vue schématique en coupe partielle montrant les pièces de la figure 3 après brasage ;  - Figure 4 is a schematic partial sectional view showing the parts of Figure 3 after brazing;
- la figure 5 est une vue schématique en coupe partielle montrant les pièces de la figure 4 après retrait des organes de serrage ; - les figures 6 et 7 sont respectivement une vue schématique en coupe partielle et en perspective montrant les pièces de la figure 5 après mise en place d'organes de fixation définitifs, - Figure 5 is a schematic partial sectional view showing the parts of Figure 4 after removal of the clamping members; FIGS. 6 and 7 are respectively a diagrammatic view in partial section and in perspective showing the parts of FIG. 5 after placement of definitive fasteners,
- la figure 8 est une photographie présentant deux plaques en matériau composite SiC/SiC destinées à être brasées en utilisant un organe de serrage,  FIG. 8 is a photograph showing two plates of SiC / SiC composite material intended to be brazed using a clamping member,
- la figure 9 est une photographie montrant les plaques de la figure 8 prêtes à être brasées ensemble,  FIG. 9 is a photograph showing the plates of FIG. 8 ready to be brazed together,
- la figure 10 est une courbe du cycle de brasage thermique appliqué aux plaques de la figure 9,  FIG. 10 is a curve of the thermal brazing cycle applied to the plates of FIG. 9,
- la figure 11 est une photographie montrant les plaques de la figure 9 après brasage.  - Figure 11 is a photograph showing the plates of Figure 9 after soldering.
Description détaillée de mode de réalisation Detailed Description of Embodiment
Le procédé d'assemblage par brasage selon la présente invention s'applique en particulier, mais non exclusivement, à des matériaux céramiques et notamment à base de carbure de silicium. Par matériau à base de carbure de silicium (SiC), on entend un matériau dont la teneur en SiC est supérieure ou égale à 50% en masse, de préférence supérieure ou égale à 80% en masse, voire encore 100% en masse. The solder assembly method according to the present invention is particularly, but not exclusively, applicable to ceramic materials and in particular based on silicon carbide. By material based on silicon carbide (SiC) is meant a material whose SiC content is greater than or equal to 50% by weight, preferably greater than or equal to 80% by weight, or even 100% by weight.
Un des matériaux à base de SiC considéré ici est notamment le matériau composite thermostructural à matrice céramique (CMC), c'est-à- dire à tout matériau formé d'un renfort en fibres réfractaires (carbone ou céramique) densifié par une matrice au moins partiellement en SiC, tels que des matériaux C/SiC, SiC/SiC, C/C-SiC, etc.  One of the SiC-based materials considered here is in particular the ceramic matrix thermostructural composite material (CMC), that is to say any material formed of a reinforcement of refractory fibers (carbon or ceramic) densified by a matrix at less partially SiC, such as C / SiC, SiC / SiC, C / C-SiC, etc.
Les structures fabriquées selon le procédé d'assemblage de l'invention correspondent notamment à des ensembles d'arrière-corps de moteurs d'avion ou à des échangeurs thermiques.  The structures manufactured according to the assembly method of the invention correspond in particular to sets of rear bodies of aircraft engines or to heat exchangers.
La figure 1 montre une première pièce constituée d'une virole 10 et une seconde pièce constituée d'un cône 20 qui sont destinées à former, une fois assemblées entre elles, un corps central ou cône d'échappement, encore appelé "plug". Dans l'exemple décrit ici, la virole 10 et le cône 20 sont réalisés en matériau SiC/SiC, à savoir un matériau comprenant un renfort en fibres de SiC densifié par une matrice SiC. La virole 10 comporte une portion d'assemblage 11 qui est destinée à être assemblée par brasage avec une portion d'assemblage 21 du cône 20. Figure 1 shows a first part consisting of a shell 10 and a second part consisting of a cone 20 which are intended to form, once assembled together, a central body or exhaust cone, also called "plug". In the example described here, the ferrule 10 and the cone 20 are made of SiC / SiC material, namely a material comprising a SiC fiber reinforcement densified by an SiC matrix. The ferrule 10 comprises an assembly portion 11 which is intended to be assembled by brazing with an assembly portion 21 of the cone 20.
Conformément à l'invention, une pluralité d'orifices 110 ont été formés dans la portion d'assemblage 11 de la virole 10 tandis qu'une autre pluralité d'orifices 210 ont été formés dans la portion d'assemblage 21 du cône 20. Les orifices 110 et 210 sont ménagés sur les portions d'assemblage 11 et 21 à des emplacements déterminés de manière à coïncider les uns avec les autres lors de l'accostage des portions d'assemblage comme décrit ci-après.  According to the invention, a plurality of orifices 110 have been formed in the assembly portion 11 of the ferrule 10 while another plurality of orifices 210 have been formed in the assembly portion 21 of the cone 20. The orifices 110 and 210 are formed on the assembly portions 11 and 21 at locations determined so as to coincide with each other during the docking of the assembly portions as described below.
Les orifices 110 et 210 peuvent être percés directement dans les pièces après leur fabrication ou être réalisés durant la fabrication de celles-ci en introduisant des inserts dans le renfort fibreux aux endroits de formation des orifices et en retirant les inserts après densification du renfort. Les orifices 110 et 210 peuvent être obtenus par perçage simultané de la virole 10 et du cône 20 maintenus dans leur position d'assemblage. Le nombre et la répartition des orifices sont déterminés en fonction du maintien et du serrage nécessaire à appliquer lors du brasage. Par ailleurs, lorsque les orifices sont en outre destinés à être utilisés pour renforcer ou sécuriser la liaison après brasage, le nombre et le positionnement des orifices sur les pièces sont également déterminés en fonction du dimensionnement et des caractéristiques mécaniques de l'assemblage.  The orifices 110 and 210 may be pierced directly into the parts after manufacture or be made during manufacture thereof by inserting inserts into the fibrous reinforcement at the locations of the orifices and removing the inserts after densification of the reinforcement. The orifices 110 and 210 may be obtained by simultaneous drilling of the ferrule 10 and the cone 20 held in their assembly position. The number and the distribution of the orifices are determined according to the maintenance and the necessary tightening to be applied during brazing. Furthermore, when the orifices are further intended to be used to strengthen or secure the connection after brazing, the number and positioning of the orifices on the parts are also determined according to the dimensioning and mechanical characteristics of the assembly.
Toujours conformément à l'invention, des organes de serrage 30 constitués chacun ici d'une vis 31 et d'un écrou 32 en graphite sont utilisés pour maintenir les portions d'assemblage 11 et 21 respectivement de la virole 10 et du cône 20 dans leur position d'accostage et pour appliquer un effort de serrage sur ces portions lors du brasage. A cet effet, comme représentée sur les figures 2 et 3, une vis 31 est introduite dans chaque paire d'orifices 110 et 210 en vis-à-vis lorsque la portion d'assemblage 11 de la virole 10 est placée dans sa position d'accostage avec la portion d'assemblage 21 du cône 20. Le maintien en position et l'effort de serrage permettant de conformer les portions d'assemblage des pièces entre elles sont assurés par serrage d'un écrou 32 sur chaque vis 31. Dans le mode de réalisation décrit ici, les organes de serrage 30 sont destinés à être retirés après brasage. Ainsi, afin d'empêcher la brasure de se fixer sur les vis 31 et sur les écrous 32 et de faciliter leur retrait après brasage, ceux-ci peuvent être recouverts d'un agent anti-mouillant comme par exemple du nitrure de bore (BN). Selon une variante de réalisation, les vis et les écrous peuvent être réalisés directement en un matériau anti- mouillant vis-à-vis de la composition de brasure. Still in accordance with the invention, clamping members 30 each consisting of a screw 31 and a nut 32 made of graphite are used to hold the assembly portions 11 and 21 respectively of the shell 10 and the cone 20 in their docking position and to apply a clamping force on these portions during brazing. For this purpose, as shown in Figures 2 and 3, a screw 31 is inserted into each pair of orifices 110 and 210 vis-à-vis when the assembly portion 11 of the shell 10 is placed in its position d the coupling with the assembly portion 21 of the cone 20. The holding in position and the clamping force to conform the assembly portions of the parts together are provided by tightening a nut 32 on each screw 31. In the embodiment described here, the clamping members 30 are intended to be removed after brazing. Thus, in order to prevent the solder from being fixed on the screws 31 and on the nuts 32 and to facilitate their withdrawal after brazing, they may be covered with an anti-wetting agent such as boron nitride (BN). According to an alternative embodiment, the screws and nuts can be made directly from an anti-wetting material vis-à-vis the solder composition.
Dans le mode de réalisation décrit ici, des entretoises 33 sont en outre placées entre les portions d'assemblage 11 et 21 au niveau des organes de serrage 30 (figures 1 et 3). Chaque entretoise 33 comporte un perçage central 330 permettant le passage d'une vis 31 qui assure le maintien en position de l'entretoise. En outre, chaque entretoise 33 présente une hauteur H déterminée (figure 3). Lorsque les variations de forme et/ou d'état de surface entre les portions d'assemblage ne sont pas trop importantes, les entretoises 33 peuvent toutes présenter une même hauteur qui permet d'ajuster l'épaisseur de joint de brasure obtenu. Lorsque ces variations sont plus importantes, la hauteur de chaque entretoise est déterminée de manière à maintenir un espacement sensiblement uniforme entre les portions d'assemblage sur toute la zone de brasage afin d'obtenir une épaisseur de joint de brasure également sensiblement uniforme et garantir une bonne liaison.  In the embodiment described here, spacers 33 are further placed between the assembly portions 11 and 21 at the clamping members 30 (FIGS. 1 and 3). Each spacer 33 has a central bore 330 allowing the passage of a screw 31 which maintains the position of the spacer. In addition, each spacer 33 has a determined height H (FIG. 3). When the variations in shape and / or surface condition between the assembly portions are not too great, the spacers 33 may all have the same height which makes it possible to adjust the thickness of the solder joint obtained. When these variations are greater, the height of each spacer is determined so as to maintain a substantially uniform spacing between the assembly portions over the entire brazing zone so as to obtain a substantially uniform solder joint thickness and to guarantee a uniform good liaison.
Dans l'exemple décrit ici, le brasage est réalisé par apport de brasure dans la zone de brasage 40, c'est-à-dire la partie de recouvrement entre les portions d'assemblage 11 et 21. A cet effet, une composition de brasure 41 sous forme d'une pâte solide est placée sur la surface externe du cône 20 à proximité de la portion d'assemblage 21 et en contact avec le bord 11b de la portion d'assemblage 11 de la virole 10. Le bord 11b peut être recouvert d'un agent anti-mouillant pour empêcher la composition de brasure de pénétrer dans le matériau à cet endroit et favoriser ainsi sa répartition dans la zone de brasage 40. Des éléments capillaires, par exemple des grains de SiC, peuvent être en outre disposés dans la zone d'accostage afin de faciliter le transport et la diffusion de la brasure liquéfiée entre les portions d'assemblage 11 et 21 lors de l'étape de brasage. D'autres éléments capillaires comme notamment un voile de SiC, un mat de carbone, des particules de carbone ou des nanotubes de carbone peuvent être utilisés.  In the example described here, the brazing is carried out by adding solder to the soldering zone 40, that is to say the overlap portion between the assembly portions 11 and 21. For this purpose, a composition of solder 41 in the form of a solid paste is placed on the outer surface of the cone 20 near the assembly portion 21 and in contact with the edge 11b of the assembly portion 11 of the shell 10. The edge 11b can be coated with an anti-wetting agent to prevent the solder composition from penetrating into the material at this location and thus promote its distribution in the brazing zone 40. Capillary elements, for example SiC grains, can also be arranged in the docking zone to facilitate the transport and diffusion of the liquefied solder between the assembly portions 11 and 21 during the soldering step. Other capillary elements such as in particular an SiC web, a carbon mat, carbon particles or carbon nanotubes can be used.
Le choix de la brasure est effectué notamment en fonction de sa compatibilité avec le matériau composite des pièces à assembler, c'est-à- dire qu'on choisit de préférence une composition non réactive ou à réactivité contrôlée avec le matériau des pièces à braser et ayant un coefficient de dilatation thermique proche de celui de ce matériau. On utilisera par exemple des compositions à base de silicium telles que décrites dans les documents EP 806 402, US 5 975 407, US 2008/190552 et US 7 497 918 des alliages de silicium+siliciures métalliques, du silicium+germanium allié ou non, ainsi que des compositions métalliques connues sous le nom commercial Cusil-ABA®, Ticusil®, Incusil® ou Brasic®. The choice of the solder is made in particular as a function of its compatibility with the composite material of the parts to be assembled, that is to say that a non-reactive or non-reactive composition is preferably chosen. controlled reactivity with the material of the parts to be brazed and having a coefficient of thermal expansion close to that of this material. For example, silicon-based compositions as described in documents EP 806 402, US Pat. No. 5,975,407, US 2008/190552 and US Pat. No. 7,497,918 will be used for alloys of silicon + metal silicides, silicon + germanium, whether or not alloyed, as well as metal compositions known under the trade name Cusil-ABA®, Ticusil®, Incusil® or Brasic®.
On peut également utiliser des compositions correspondant à des mélanges d'oxydes choisis parmi les oxydes suivants : SiO2, AI2O3, MgO et CaO. It is also possible to use compositions corresponding to mixtures of oxides chosen from the following oxides: SiO 2 , Al 2 O 3 , MgO and CaO.
L'étape suivante consiste à mettre en œuvre le cycle de brasage en élevant la température jusqu'à rendre liquide la composition de brasure 41 qui se répartie alors sur la zone de brasage 40 présente entre les deux portions d'assemblage 11 et 21.  The following step consists in implementing the brazing cycle by raising the temperature until the solder composition 41 is liquid, which is then distributed over the brazing zone 40 present between the two assembly portions 11 and 21.
Une fois l'ensemble refroidi, on obtient un joint de brasure 42 en contact avec les faces lia et 21a des portions d'assemblage 11 et 21 respectivement de la virole 10 et du cône 20 comme illustré schématiquement sur la figure 4.  Once the assembly has cooled, a solder joint 42 is obtained in contact with the faces 11a and 21a of the assembly portions 11 and 21 respectively of the ferrule 10 and the cone 20 as illustrated schematically in FIG. 4.
Les organes de serrage 30 sont ensuite retirés (figure 5) pour être remplacés par des organes de fixation définitifs 50 (figure 6) adaptés aux conditions dans lesquelles la pièce obtenue (plug) est destinée à être utilisée. Dans l'exemple décrit ici, la pièce finale n'étant pas destinée à être utilisée à de hautes températures, les organes de fixation 50 sont constitués ici de rivets 51 en métal inoxydable.  The clamping members 30 are then removed (Figure 5) to be replaced by final fasteners 50 (Figure 6) adapted to the conditions in which the piece obtained (plug) is intended to be used. In the example described here, the final part is not intended to be used at high temperatures, the fasteners 50 are constituted here rivets 51 of stainless metal.
Les organes de fixation, ou les organes de serrage lorsqu'ils sont maintenus après brasage, permettent de renforcer la liaison entre les pièces et d'améliorer la tenue mécanique de l'assemblage.  The fasteners, or the clamping members when held after brazing, strengthen the connection between the parts and improve the mechanical strength of the assembly.
On obtient ainsi, tel que représenté sur la figure 7, un cône d'échappement ou plug 100 constitué de la virole 10 et du cône 20 liés ensemble par le joint de brasure 42 et les organes de fixation 50.  Thus, as shown in FIG. 7, an exhaust cone or plug 100 consisting of the shell 10 and the cone 20 bonded together by the solder joint 42 and the fasteners 50 is obtained.
Des exemples d'assemblage par brasage ont été réalisés conformément au procédé de l'invention. Exemple 1 : Examples of solder assembly were made in accordance with the method of the invention. Example 1
Cet exemple décrit la préparation et la réalisation de liaisons brasées entre deux pièces en composite, plus précisément en composite SiC/SiC (matrice en SiC et fibres en SiC) percées chacune d'un trou de 5 mm, en mettant en œuvre le procédé de brasage selon l'invention, c'est-à- dire en utilisant des organes de serrage lors du brasage. Les pièces à braser sont deux plaques 60, 61 en matériau composite SiC/SiC chacune respectivement percées d'un trou 600 et 610 (figure 8). Un tel matériau composite est disponible auprès de la société Snecma Propulsion Solide sous la dénomination Cerasep A40C®. Ces plaques ont respectivement les dimensions suivantes : This example describes the preparation and the production of bonds brazed between two composite parts, more precisely composite SiC / SiC (SiC matrix and SiC fibers) each pierced with a hole of 5 mm, by implementing the method of brazing according to the invention, that is to say using clamping members during brazing. The parts to be soldered are two plates 60, 61 of SiC / SiC composite material each respectively drilled with a hole 600 and 610 (Figure 8). Such a composite material is available from Snecma Propulsion Solid under the name Cerasep A40C®. These plates respectively have the following dimensions:
- 25x20 mm2, épaisseur 1,5 mm, percée d'un trou de 5 mm- 25x20 mm 2 , thickness 1.5 mm, pierced with a hole of 5 mm
- 20x20 mm2, épaisseur 1,5 mm, percée d'un trou de 5 mm Le brasage a été réalisé par diffusion capillaire sur la zone de brasage en utilisant une composition de brasure constituée de 58% atomique de silicium (Si), de 32% atomique de nickel (Ni), et de 10% atomique d'aluminium (Al). La quantité de composition de brasure placée au bord de la zone de brasage est de 929,2 mg. - 20x20 mm 2 , thickness 1.5 mm, pierced with a hole of 5 mm Brazing was performed by capillary diffusion on the soldering zone using a solder composition consisting of 58 atomic% silicon (Si), 32 atomic% nickel (Ni), and 10 atomic% aluminum (Al). The amount of solder composition placed at the edge of the brazing zone is 929.2 mg.
La composition de brasure (58% atomique de Si, 32% atomique de Ni, et 10% atomique de Al) a été préparée à partir de morceaux de Si, de morceaux de Ni, et de morceaux de Al purs. Ces morceaux ont été pesés en respectant les proportions de la composition de brasure et placés dans un creuset en alumine. L'ensemble a été placé dans un four graphite et soumis à un cycle thermique avec un palier à 1300°C sous vide secondaire pendant 30 minutes. On obtient ainsi, après refroidissement, un lingot. Ce lingot est concassé pour obtenir une poudre. Un liant organique, par exemple un cément de type NICROBRAZ® , a été ajouté à ce mélange de poudre afin de former une composition de brasure visqueuse. Les pièces sont nettoyées à l'acétone puis à l'éthanol et enfin séchées.  The solder composition (58 atomic% Si, 32 atomic% Ni, and 10 atomic% Al) was prepared from pieces of Si, pieces of Ni, and pieces of pure Al. These pieces were weighed respecting the proportions of the solder composition and placed in an alumina crucible. The assembly was placed in a graphite furnace and subjected to a thermal cycle with a plateau at 1300 ° C. under secondary vacuum for 30 minutes. Thus, after cooling, an ingot. This ingot is crushed to obtain a powder. An organic binder, for example a NICROBRAZ® type cement, has been added to this powder mixture to form a viscous solder composition. The parts are cleaned with acetone then with ethanol and finally dried.
Comme illustrées sur la figure 9, les pièces 60 et 61 sont mises en contact de manière à définir une zone de brasage 62 délimitée par les portions des plaques 60 et 61 en regard l'une de l'autre. La plaque 60 comporte une partie 60a qui dépasse de 5 mm à l'extérieur de la zone de brasage 62 et sur laquelle on a déposé une composition de brasure 63 correspondant à la composition de brasure visqueuse décrite ci-avant (cette configuration est appelée configuration capillaire). La composition de brasure 63 est déposée avec une spatule sur la partie 60a sous la forme d'un cordon de brasure (figure 9) ayant une masse de 929,2 mg. As illustrated in Figure 9, the parts 60 and 61 are brought into contact so as to define a brazing zone 62 defined by the portions of the plates 60 and 61 facing one another. The plate 60 has a part 60a which protrudes 5 mm outside the brazing zone 62 and on which a solder composition 63 has been deposited. corresponding to the viscous solder composition described above (this configuration is called the capillary configuration). Solder composition 63 is deposited with a spatula on portion 60a in the form of a solder bead (FIG. 9) having a mass of 929.2 mg.
Conformément à l'invention, un organe de serrage 70 constitué d'une vis 71 et d'un écrou 72, revêtus d'un agent anti-mouillant comme du BN, a été utilisé pour appliquer un effort de serrage entre les deux plaques. A cet effet, la vis 71 a été introduite dans les trous 600 et 610 en vis-à-vis, le serrage de l'écrou 72 assurant l'application de l'effort de serrage entre les deux plaques (figure 9).  According to the invention, a clamping member 70 consisting of a screw 71 and a nut 72, coated with an anti-wetting agent such as BN, was used to apply a clamping force between the two plates. For this purpose, the screw 71 was introduced into the holes 600 and 610 vis-a-vis, the tightening of the nut 72 ensuring the application of the clamping force between the two plates (Figure 9).
L'ensemble a été ensuite placé dans un four de brasage (four graphite) sous vide secondaire et soumis à un cycle thermique de brasage sous vide qui comprend, un premier palier de 180 minutes à 980°C suivi d'un second palier de 60 minutes à 1100°C, qui est le palier de brasage (figure 10).  The assembly was then placed in a secondary vacuum brazing furnace (graphite furnace) and subjected to a vacuum brazing heat cycle which includes a first 180-minute plateau at 980 ° C followed by a second plateau of 60 ° C. minutes at 1100 ° C, which is the soldering bearing (Figure 10).
Après refroidissement, on obtient, tel qu'illustré sur la figure 11, un assemblage 70 formé des deux plaques 60 et 61 qui liées entre elles par un joint de brasure 64.  After cooling, there is obtained, as illustrated in FIG. 11, an assembly 70 formed of two plates 60 and 61 which are interconnected by a solder joint 64.
Après brasage, la vis est retirée sans difficulté malgré la présence du joint de brasure jusqu'au bord des trous 600 et 610. La liaison brasée obtenue est de bonne qualité avec un taux de remplissage de la zone de brasure de 95 % (contrôlé par tomographie).  After brazing, the screw is removed without difficulty despite the presence of the solder joint to the edge of the holes 600 and 610. The brazed connection obtained is of good quality with a filling ratio of the solder zone of 95% (controlled by tomography).
Exemple 2 : Example 2
Cet exemple diffère de l'exemple 1 décrit ci-dessus en ce qu'on interpose entre les deux plaques avant leur brasage des particules de SiC afin de réaliser un joint de brasure plus épais que dans l'exemple 1. Les plaques utilisées ici sont de même nature et de mêmes dimensions que les plaques 60 et 61 décrites ci-dessus. La composition de brasure utilisée est également identique en constitution (poudre de 58% atomique de Si, 32% atomique de Ni, et 10% atomique de Al liée dans par cément de type NICROBRAZ®) à celle utilisée dans l'exemple 1. This example differs from Example 1 described above in that SiC particles are interposed between the two plates prior to soldering in order to produce a thicker solder joint than in Example 1. The plates used here are of the same nature and dimensions as the plates 60 and 61 described above. The solder composition used is also identical in constitution (58 atomic% Si powder, 32 atomic% Ni, and 10 atomic% Al bound in NICROBRAZ® type cement) to that used in Example 1.
Avant leur mise en contact, les faces des plaques destinées à être brasées sont recouvertes de particules de SiC ayant une granulométrie de 50 μΓη environ. Ces particules ont été traitées thermiquement à 1460°C sous vide secondaire pendant deux heures.Before being brought into contact, the faces of the plates intended to be brazed are covered with SiC particles having a particle size of about 50 μΓη. These particles were heat-treated at 1460 ° C under a secondary vacuum for two hours.
Après ce traitement thermique, les particules de SiC sont stockées sous argon jusqu'à leur utilisation. After this heat treatment, the SiC particles are stored under argon until they are used.
Pour le dépôt sur les plaques en matériau composite SiC/SiC, les particules de SiC sont liées entre elles par un liant organique tel qu'un cément de type NICROBRAZ®, ce qui permet d'obtenir une pâte facile à déposer sur les plaques en SiC/SiC. La quantité de particules déposée avec une spatule est de 229 mg, cette quantité étant répartie entre les deux plaques en dépassant de la zone de brasage au niveau de la portion de plaque qui dépasse de la zone de brasage et sur laquelle la composition de brasure est déposée.  For the deposition on SiC / SiC composite material plates, the SiC particles are bonded to each other by an organic binder such as a NICROBRAZ® type cement, which makes it possible to obtain a paste that is easy to deposit on the plates. SiC / SiC. The amount of particles deposited with a spatula is 229 mg, this amount being distributed between the two plates by exceeding the brazing zone at the portion of the plate that protrudes from the brazing zone and on which the solder composition is filed.
Dans cet exemple, la quantité de composition de brasure, déposée sous forme de cordon avec une spatule, est de 826 mg.  In this example, the amount of solder composition, deposited in bead form with a spatula, is 826 mg.
Un organe de serrage identique à celui déjà décrit dans l'exemple 1 est utilisé pour appliquer un effort de serrage entre les deux plaques.  A clamping member identical to that already described in Example 1 is used to apply a clamping force between the two plates.
L'ensemble est ensuite placé dans un four de brasage (four graphite) sous vide secondaire et soumis à un cycle thermique de brasage identique à celui décrit dans l'exemple 1.  The assembly is then placed in a brazing furnace (graphite furnace) under secondary vacuum and subjected to a thermal brazing cycle identical to that described in Example 1.
Après refroidissement, on obtient un assemblage formé de deux plaques qui sont liées entre elles par un joint de brasure.  After cooling, there is obtained an assembly formed of two plates which are interconnected by a solder joint.
Après brasage, la vis est retirée sans difficulté malgré la présence du joint de brasure jusqu'au bord des trous percés dans les plaques. La liaison brasée obtenue est de bonne qualité avec un taux de remplissage de la zone de brasure de 83 % (contrôlé par tomographie).  After brazing, the screw is removed without difficulty despite the presence of the solder joint to the edge of the holes drilled in the plates. The brazed bond obtained is of good quality with a filling rate of the solder zone of 83% (controlled by tomography).

Claims

REVENDICATIONS
1. Procédé d'assemblage par brasage entre une première pièce (10) et une deuxième pièce (20) en matériau à base de carbure de silicium, les première et deuxième pièces (10, 20) comportant chacune une portion d'assemblage (11 ; 21) destinée à être brasée avec la portion d'assemblage (21 ; 11) de l'autre pièce, le procédé comprenant les étapes suivantes : 1. A method of soldering between a first part (10) and a second part (20) made of silicon carbide material, the first and second parts (10, 20) each comprising an assembly portion (11). 21) intended to be brazed with the connecting portion (21; 11) of the other part, the method comprising the following steps:
accostage des portions d'assemblage (11, 21) des première et deuxième pièces (10, 20), une composition de brasure (41) étant disposée entre les portions d'assemblage ou à proximité desdites portions d'assemblage,  docking the assembly portions (11, 21) of the first and second pieces (10, 20), a solder composition (41) being disposed between or near the assembly portions,
brasage des portions d'assemblage,  brazing of the assembly portions,
caractérisé en ce que le procédé comprend en outre une étape de formation d'une pluralité d'orifices (110, 210) dans les portions d'assemblage (11, 21) des première et deuxième pièces, les orifices étant formés à des positions déterminées de manière à aligner les orifices (110) de la portion d'assemblage (11) de la première pièce (10) avec les orifices (210) de la portion d'assemblage (21) de la deuxième pièce (20) lors de l'étape d'accostage et en ce qu'un élément (31) d'un organe de serrage (30) est introduit dans chaque paire d'orifices (110, 210) en vis-à-vis, chaque organe de serrage (30) appliquant un effort de serrage entre les portions d'assemblage (11, 21), et en ce que les éléments des organes de serrage (30) sont en un matériau anti-mouillant vis-à-vis de la composition de brasure ou revêtus d'un matériau anti-mouillant vis-à-vis de la composition de brasure.  characterized in that the method further comprises a step of forming a plurality of orifices (110, 210) in the assembly portions (11, 21) of the first and second pieces, the orifices being formed at predetermined positions in order to align the orifices (110) of the assembly portion (11) of the first piece (10) with the orifices (210) of the assembly portion (21) of the second piece (20) when the step of docking and in that an element (31) of a clamping member (30) is introduced into each pair of orifices (110, 210) facing each other, each clamping member (30) ) applying a clamping force between the assembly portions (11, 21), and in that the elements of the clamping members (30) are of a wicking material with respect to the solder composition or coated anti-wetting material with respect to the solder composition.
2. Procédé selon la revendication 1, caractérisé en ce qu'il comprend, après l'étape de brasage, une étape de retrait des organes de serrage (30). 2. Method according to claim 1, characterized in that it comprises, after the soldering step, a step of removing the clamping members (30).
3. Procédé selon la revendication 1 ou 2, caractérisé en ce qu'il comprend, après l'étape de retrait des organes de serrage (30), une étape de mise en place d'organes de fixation (50) dans chaque paire d'orifices en vis-à-vis. 3. Method according to claim 1 or 2, characterized in that it comprises, after the step of removing the clamping members (30), a step of placing fasteners (50) in each pair of 'orifices vis-à-vis.
4. Procédé selon l'une quelconque des revendications 1 à 3, caractérisé en ce que l'étape de brasage comprend un traitement thermique réalisé à une température de brasage apte à liquéfier la composition de brasure (41) et en ce que les éléments des organes de serrage présentent une température de fluage supérieure à la température de brasage (30). 4. Method according to any one of claims 1 to 3, characterized in that the soldering step comprises a heat treatment performed at a soldering temperature capable of liquefying the solder composition (41) and in that the elements of the clamping members have a creep temperature higher than the brazing temperature (30).
5. Procédé selon l'une quelconque des revendications 1 à 4, caractérisé en ce que des entretoises (33) ayant une hauteur (H) déterminée sont interposées entre les portions d'assemblage (11, 21), chaque entretoise étant traversée par un élément (31) d'un organe de serrage (30). 5. Method according to any one of claims 1 to 4, characterized in that spacers (33) having a height (H) determined are interposed between the assembly portions (11, 21), each spacer being traversed by a element (31) of a clamping member (30).
6. Procédé selon l'une quelconque des revendications 1 à 5, caractérisé en ce qu'il comprend une étape d'interposition d'éléments capillaires entre les portions d'assemblage (11, 21) des première et deuxième pièces (10, 20) et une étape de placement d'une composition de brasure en contact avec une partie des éléments capillaires. 6. Method according to any one of claims 1 to 5, characterized in that it comprises a step of interposing capillary elements between the assembly portions (11, 21) of the first and second parts (10, 20). ) and a step of placing a solder composition in contact with a portion of the capillary elements.
7. Procédé selon la revendication 6, caractérisé en ce que les éléments capillaires sont choisis parmi au moins un des éléments suivants : particules de SiC, voile de SiC, mat de carbone, particules de carbone et nanotubes de carbone. 7. Method according to claim 6, characterized in that the capillary elements are chosen from at least one of the following elements: SiC particles, SiC web, carbon mat, carbon particles and carbon nanotubes.
8. Procédé selon l'une quelconque des revendications 1 à 7, caractérisé en ce que les pièces (10, 20) en matériau composite à assembler par brasage sont des pièces d'arrière-corps de moteur aéronautique. 8. A method according to any one of claims 1 to 7, characterized in that the parts (10, 20) made of composite material to be brazed together are parts of aft engine body.
9. Procédé selon l'une quelconque des revendications 1 à 7, caractérisé en ce que les pièces en matériau composite à assembler par brasage sont des pièces d'un échangeur de chaleur. 9. Method according to any one of claims 1 to 7, characterized in that the parts of composite material to be soldered are parts of a heat exchanger.
PCT/FR2013/052315 2012-10-09 2013-09-30 Method for brazing parts made from silicon carbide material with holding clamping members having anti-wetting properties WO2014057187A1 (en)

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FR1259593A FR2996478B1 (en) 2012-10-09 2012-10-09 PROCESS FOR BRAZING SILICON CARBIDE MATERIALS WITH HOLDING TIGHTENING
FR1259593 2012-10-09

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US4146165A (en) * 1976-11-12 1979-03-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Process for joining by brazing-diffusion
US4648546A (en) * 1985-04-09 1987-03-10 Gellert Jobst U Composite plate method of manufacturing injection molding manifold
US5447683A (en) * 1993-11-08 1995-09-05 General Atomics Braze for silicon carbide bodies
EP0806402A1 (en) 1996-05-07 1997-11-12 Commissariat A L'energie Atomique Joining silicon carbide containing ceramic materials by brazing
US5975407A (en) 1996-06-12 1999-11-02 Commissariat A L'energie Atomique Method using a thick joint for joining parts in SiC-based materials by refractory brazing and refractory thick joint thus obtained
US20060248718A1 (en) * 2005-05-06 2006-11-09 United Technologies Corporation Superalloy repair methods and inserts
US20080190552A1 (en) 2004-06-24 2008-08-14 Eric Bouillon Method For Soldering Composite Material Parts
US7497918B2 (en) 2003-02-17 2009-03-03 Snecma Propulsion Solide Method of siliciding thermostructural composite materials, and parts obtained by the method

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US6708756B2 (en) * 2001-06-08 2004-03-23 Denso Thermal Systems Spa Method for fixing components to a pipe for circulation of a fluid forming part of a heat exchanger, in particular a condenser of an air-conditioning system

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Publication number Priority date Publication date Assignee Title
US4146165A (en) * 1976-11-12 1979-03-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Process for joining by brazing-diffusion
US4648546A (en) * 1985-04-09 1987-03-10 Gellert Jobst U Composite plate method of manufacturing injection molding manifold
US5447683A (en) * 1993-11-08 1995-09-05 General Atomics Braze for silicon carbide bodies
EP0806402A1 (en) 1996-05-07 1997-11-12 Commissariat A L'energie Atomique Joining silicon carbide containing ceramic materials by brazing
US5975407A (en) 1996-06-12 1999-11-02 Commissariat A L'energie Atomique Method using a thick joint for joining parts in SiC-based materials by refractory brazing and refractory thick joint thus obtained
US7497918B2 (en) 2003-02-17 2009-03-03 Snecma Propulsion Solide Method of siliciding thermostructural composite materials, and parts obtained by the method
US20080190552A1 (en) 2004-06-24 2008-08-14 Eric Bouillon Method For Soldering Composite Material Parts
US20060248718A1 (en) * 2005-05-06 2006-11-09 United Technologies Corporation Superalloy repair methods and inserts

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