WO2007066052A2 - Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c. - Google Patents
Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c. Download PDFInfo
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- WO2007066052A2 WO2007066052A2 PCT/FR2006/051318 FR2006051318W WO2007066052A2 WO 2007066052 A2 WO2007066052 A2 WO 2007066052A2 FR 2006051318 W FR2006051318 W FR 2006051318W WO 2007066052 A2 WO2007066052 A2 WO 2007066052A2
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- piece
- assembly according
- intermediate piece
- ceramic
- ceramic material
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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
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
- C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
- C04B37/025—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used consisting of glass or ceramic material
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- 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
- B23K35/00—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting
- B23K35/02—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape
- B23K35/0222—Rods, electrodes, materials, or media, for use in soldering, welding, or cutting characterised by mechanical features, e.g. shape for use in soldering, brazing
- B23K35/0244—Powders, particles or spheres; Preforms made therefrom
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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
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
- C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
- C04B37/026—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used consisting of metals or metal salts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infra-red radiation suppressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/08—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof
- F02K3/10—Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluid; Control thereof by after-burners
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2311/00—Metals, their alloys or their compounds
- B32B2311/22—Nickel or cobalt
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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
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5244—Silicon carbide
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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
- C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
- C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
- C04B2235/50—Constituents or additives of the starting mixture chosen for their shape or used because of their shape or their physical appearance
- C04B2235/52—Constituents or additives characterised by their shapes
- C04B2235/5208—Fibers
- C04B2235/5216—Inorganic
- C04B2235/524—Non-oxidic, e.g. borides, carbides, silicides or nitrides
- C04B2235/5248—Carbon, e.g. graphite
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/08—Non-oxidic interlayers
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/12—Metallic interlayers
- C04B2237/123—Metallic interlayers based on iron group metals, e.g. steel
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/12—Metallic interlayers
- C04B2237/125—Metallic interlayers based on noble metals, e.g. silver
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/16—Silicon interlayers
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/34—Oxidic
- C04B2237/341—Silica or silicates
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/36—Non-oxidic
- C04B2237/365—Silicon carbide
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
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- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/32—Ceramic
- C04B2237/38—Fiber or whisker reinforced
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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
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/30—Composition of layers of ceramic laminates or of ceramic or metallic articles to be joined by heating, e.g. Si substrates
- C04B2237/40—Metallic
- C04B2237/405—Iron metal group, e.g. Co or Ni
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- 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
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/237—Brazing
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- 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
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
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- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/226—Carbides
- F05D2300/2261—Carbides of silicon
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M2900/00—Special features of, or arrangements for combustion chambers
- F23M2900/05004—Special materials for walls or lining
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12326—All metal or with adjacent metals with provision for limited relative movement between components
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/125—Deflectable by temperature change [e.g., thermostat element]
- Y10T428/12507—More than two components
Definitions
- the invention relates to an assembly between a metal part and a part made of ceramic material based on silicon carbide (SiC) and / or carbon (C).
- This invention finds a preferred application in the field of aeronautics, for the assembly of a part of refractory metal alloy, such as an alloy based on nickel (Ni) or cobalt (Co), and a part in ceramic matrix composite material, or CMC part.
- the CMC parts concerned comprise a matrix based on SiC, C or a so-called "mixed" matrix of C and SiC, reinforced by fibers of SiC and / or C.
- Said matrix can be single-phase (for example entirely in SiC) or multiphase (it may contain, for example, at least one other phase with self-healing property as described in document FR 2 732 338).
- CMC parts are used in aircraft turbojet engines to replace the most thermo-mechanically exposed mechanical parts, because they retain good mechanical properties at high temperatures, require less cooling, and are generally lighter.
- the object of the invention is to overcome these drawbacks, or at least to mitigate them, by proposing an assembly which makes it possible, on the one hand, to compensate for the difference in expansion between a metal part and a part made of ceramic material based SiC and / or C and, on the other hand, to avoid or limit the formation of undesirable chemical compounds.
- said part made of ceramic material based on SiC and / or C, this assembly being such that:
- the second intermediate piece is made of another ceramic material (ie a ceramic material different from that of said piece of ceramic material), this other ceramic material being chemically less reactive towards metals than SiC or C, and having a coefficient of expansion lower than that of the material constituting said metal part; and -
- the first intermediate piece is metallic and able to deform to compensate for the difference in expansion between said metallic piece and the second intermediate piece.
- said ceramic part can be a solid SiC part or a CMC part of the type described above.
- the invention therefore proposes to interpose between the ceramic and metallic parts two intermediate parts having distinct functions.
- the first intermediate part makes it possible to compensate, by deforming, the expansion differences between the ceramic and metallic parts.
- the latter is composed of a layer of ductile metallic material.
- the part generally has a massive structure and forms a cushion of material capable of being deformed by shearing.
- ductile materials which can be used, there may be mentioned nickel, palladium, gold, or alloys comprising these different metals.
- nickel-based alloys are chosen, these exhibiting good resistance to high temperature and a limited cost.
- said deformation is obtained by choosing a deformable structure for this part.
- This structure can, for example, be spiral spring or bellows.
- the part is then not necessarily made of ductile material.
- this part can be made of an alloy based on Ni or Co.
- the second intermediate piece aims to chemically protect said piece of ceramic material by preventing it from attacking by the liquid solder used, which generally comprises metals reactive with respect to SiC or C.
- the liquid solder used which generally comprises metals reactive with respect to SiC or C.
- the second intermediate part made of another ceramic material, less reactive with respect to metals (more particularly transition metals), such as an oxide or a nitride.
- the second intermediate part has a higher rigidity and / or resistance to rupture than that of the part made of ceramic material.
- the rigidity of the second intermediate piece makes it possible to form a rigid support for the first intermediate piece, which ensures the deformation of the latter, and makes it possible to attenuate the mechanical stresses exerted on the part made of ceramic material. Its resistance to rupture ensures the good mechanical strength of the assembly.
- the second intermediate part thus makes it possible to mechanically protect the part made of ceramic material which, by nature, is generally fragile.
- the second intermediate part has a coefficient of expansion sufficiently close to that of the part made of ceramic material, in order to limit the differences in expansion between these parts.
- the latter is produced in mullite (an oxide) or in aluminum nitride AIN (a nitride).
- Mullite is an alumina silicate, defined compound of formula (3AI2O3, 2Si ⁇ 2) obtainable by heating silica in the presence of alumina.
- alumina AI 2 O 3
- alumina can be used for aeronautical applications which require refractory assemblies.
- the first brazing composition used to assemble the first intermediate part to the metal part and / or to the second intermediate part is based on Ni and comprises an atomic proportion of Ti less than or of the order of 10%.
- this first composition also comprises the following elements: Fe, Cr and Si.
- the brazing compositions comprising the elements Ni, Fe, Cr, Si and Ti will be denoted hereinafter NiFeCrSiTi.
- Ni-based brazing compositions known as reactive (because they give rise to new intermetallic chemical compounds), are already known but in the present case, the proportion of Ti must be limited because this element has a high reactivity vis vis-à-vis the second intermediate piece, which would lead to the birth of fragile intermetallic phases.
- said first brazing composition preferably comprises, in atomic percentages: between 3 and 6% (preferably between 3.5 and 5.5%) of Ti when the second intermediate piece is made of AIN, and between 6 and 10% of Ti when the second intermediate piece is made of mullite.
- the second brazing composition used to assemble the second intermediate piece of AIN or mullite to the piece of ceramic material based on SiC and / or C is an alloy based on Si.
- this second brazing composition essentially comprises, in atomic percentages: 60% to 97% of silicon Si and 40 to 3% of zirconium Zr and, preferably, it is a eutectic mixture of silicide of Zirconium ZrSi 2 and Si.
- the liquidus temperature of a eutectic mixture ZrSi 2 -Si is around 1370 ° C., a temperature generally higher than the temperature at the start of melting of aeronautical metal alloys used for the metal part and / or the first intermediate part (for example, the temperature at which melting of the “Hastelloy X” alloy begins, described below, is 1310 ° C.).
- a first cycle typically carried out up to 1400 ° C. to carry out the assembly of the part made of ceramic material to the second intermediate piece
- a second cycle typically carried out up to 1250 ° C., temperature higher than the liquidus temperature of the first brazing composition, but at which said aeronautical metal alloys do not degrade.
- This second cycle makes it possible to carry out the final assembly by assembling the metal parts together, that is to say the basic metal part and the first metal intermediate part, and with the parts made of ceramic materials, that is to say - say the second intermediate piece and the piece made of ceramic material based on SiC and / or C.
- the second brazing composition consists essentially of a mixture of praseodymium silicide (PrSi 2 ) and Si, in which the silicon (Si) is in the majority and the praseodymium (Pr) is in the minority, in atomic proportions.
- a brazing composition is new and can be used more generally for the assembly by brazing of two parts, one of the parts being made of SiC-based ceramic. and / or C and the other part being ceramic based on SiC, C, AIN or mullite.
- said mixture of PrSi 2 and Si comprises, in atomic percentages 78% to 97% of Si and 22 to 3% of Pr and, preferably, consists of an eutectic mixture of PrSi 2 and Si.
- the melting temperature of the PrSÎ 2 -Si brazing composition is relatively low and the assembly can be carried out by brazing all the parts of the assembly in a single step.
- liquidus temperature of a eutectic mixture of PrSi 2 and Si is approximately 1212 0 C, and therefore approximately 158 ° C lower than the liquidus temperature of a eutectic mixture of ZrSi 2 and Yes.
- the atomic proportion of the mixture of PrSi 2 and Si is less close to the eutectic, in particular between 78 and 81% of Si and 22 to 19% of Pr, or between 85 and 97% of Si and 15 to 3% of Pr, it will then be necessary to proceed in two stages, as detailed above, to avoid the fusion of the metallic parts.
- solder composition PrSi 2 -Si it is therefore possible to braze all the parts of the assembly together, in a single step, at a temperature higher than the liquidus temperatures of said first and second solder compositions, but which remains low enough not to degrade the alloys present.
- the subject of the invention is also a method of assembly by brazing using such a composition.
- FIG. 1 schematically shows an assembly according to a first embodiment of the invention
- FIG. 2 schematically shows an assembly according to a second embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 shows an assembly according to a third embodiment of the invention.
- FIG. 1 shows an assembly according to a third embodiment of the invention.
- FIG. 1 shows an assembly according to a third embodiment of the invention.
- FIG. 1 shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 schematically shows an assembly according to a third embodiment of the invention.
- FIG. 1 shows an assembly according to a third embodiment of the invention.
- An alloy of the "Inconel 625" type typically comprises, in percentages by weight: at most 0.4% of AI; at most 0.1% of C; 20 to 23% Cr; at most 1% Co; at most 5% Fe; at most 0.5% of Mn; 8-10% Mo; 3.15 to 4.15% Niobium Nb; at most 0.015% P; at most 0.5% Si; at most 0.015% S; at most 0.4% Ti; and a balance in Ni.
- CMC ceramic matrix composite part 7
- the first brazing composition 2 used for brazing the metal part 1 to the first intermediate part 3 and for brazing the first intermediate part 3 to the second intermediate part 5 is of the NiFeCrSiTi type and essentially comprises (ie, apart from impurities), in mass percentages : 2.8% Fe; 7% Cr; 6.2% Si; 4.5% of Ti and a balance in Ni.
- the second brazing composition 6 used to braze the second intermediate piece 5 to the piece of ceramic material 7 is a eutectic mixture of Zr 2 Si and Si.
- the method of assembling the metallic 1 and ceramic 7 parts comprises two thermal cycles of temperature rise and fall, and essentially comprises the following steps:
- the second brazing composition 6 is arranged on the surfaces to be assembled of the part made of ceramic material 7 and of the second intermediate part 5; - The assembly thus formed (parts 5 and 7 and composition 6) is raised in temperature beyond the liquidus temperature of the second brazing composition 6, then cooled;
- the first brazing composition 2 is arranged on the surfaces to be assembled of the first and second intermediate parts 3 and 5 and of the metal part 1;
- the surfaces of the parts of parts 5 and 7 to be assembled, respectively in AIN and CMC, are degreased in an organic solvent for example of the acetone, ester, ether, alcohol or a mixture of these.
- the surfaces of the parts of parts 7 and 5 are coated with the suspension of the second brazing composition 6, formed from a eutectic mixture of ZrSi 2 and Si.
- the parts in the vicinity of the CMC / AIN joint are covered with a suspension said anti-wetting agent which cannot be wetted by said composition. This suspension prevents the brazing composition from flowing out of the CMC / AIN joint.
- the assembly thus formed, ready to be brazed, is placed in a vacuum oven or in a neutral gas atmosphere.
- a first thermal cycle with a temperature plateau is typically carried out at 140 ° C. for 5 to 10 minutes. This temperature is higher than the liquidus temperature of the composition of the solder (at least 25 ° C above).
- the assembly is then cooled to ambient temperature at a rate for example of 5 ° C. per minute.
- the CMC / AIN assembly is removed from the oven.
- a continuous brazing bead is observed between the CMC and I 1 AIN.
- the assembly is cleaned with acetone and then ethanol before the second brazing with the first intermediate piece 3 and the metallic part 1.
- the first intermediate piece 3 is made of Ni base alloy of the "Inconel 625" type.
- metal part 1 is made of Ni base alloy of the "Hastelloy X" type.
- the CMC piece 7, the bead of the second brazing composition 6 and the edges of the piece 5 in AIN are covered with a so-called anti-wetting suspension, which cannot be wetted by the first brazing composition of the NiFeCrSiTi type.
- the latter is applied in the form of a ribbon on the AIN.
- the first intermediate piece 3 is deposited.
- This part 3 is then covered with a brazing tape of NiFeCrSiTi type and then with the part metallic 1.
- the edges of parts 1 and 3 can be coated with an anti-wetting agent which cannot be wetted with the NiFeCrSiTi brazing composition.
- this anti-wetting coating depends on the shape of this piece.
- the assembly CMC / brazing ZrSi 2 -Si / AIN / brazing NiFeCrSiTi / base alloy Ni / brazing NiFeCrSiTi / base alloy Ni, ready to be brazed, is placed in an oven under vacuum or in a neutral gas atmosphere.
- a second thermal cycle is carried out with a temperature plateau at 110O 0 C for 30 minutes and then a second plateau at 1250 0 C for 15 minutes. This temperature of 1250 ° C. is higher than the temperature of the liquidus of the NiFeCrSiTi brazing composition (at least 25 ° C. above).
- the assembly is then cooled to room temperature at the rate, for example, of 5 ° C per minute.
- the second brazing composition 6 used in the first example given above is replaced by an eutectic mixture of PrSi 2 and Si.
- the assembly process metallic 1 and ceramic 7 parts comprises a single thermal cycle of temperature rise and fall, which essentially comprises the following stages:
- the second brazing composition 6 is arranged on the surfaces to be assembled of the part made of ceramic material 7 and of the second intermediate part 5; and the first brazing composition 2 is arranged on the surfaces to be joined of the first and second intermediate pieces 3 and 5 and of the metallic piece 1; and
- the carbon can be applied: 1) in the form of graphite powder mixed or not with an organic binder, 2) by deposition techniques of the chemical vapor deposition or CVD (for chemical vapor deposition) type or physical deposition in vapor phase or PVD (for "physical vapor deposition "), 3) simply by rubbing the surfaces with a graphite lead (for example a pencil lead).
- the recommended carbon thickness is around 1 micrometer.
- the parts in the vicinity of the joint are covered with a so-called suspension anti-wetting agent not wettable by the said composition
- This suspension prevents the solder from flowing out of the CMC / AIN joint.
- the AIN is covered with a solder tape of NiFeCrSiTi type. Over this solder tape, the first intermediate piece 3 in Ni base alloy is put in place This piece 3 is then covered with a solder tape of NiFeCrSiTi type and then with the metal piece in massive "Hastelloy X".
- the edges of the pieces in metal alloy 1 and 3 can be r coated with anti-wetting agent, not wettable with the NiFeCrSiTi composition.
- this anti-wetting coating depends on the shape of this piece.
- the assembly CMC / brazing PrSi 2 -Si / AIN / brazing NiFeCrSiTi / base alloy Ni / brazing NiFeCrSiTi / base alloy Ni, ready to be brazed, is placed in an oven under vacuum (or in an atmosphere of neutral gas).
- a single thermal cycle is carried out with a temperature plateau at HOO 0 C for 30 min. then a second level at 1250 0 C for 15 min. This temperature of 1250 ° C. is higher than the liquidus temperature of the NiFeCrSiTi type solder and that of the second PrSi 2 -Si solder composition (at least 25 ° C. above).
- the assembly is then cooled to room temperature at the rate, for example, of 5 ° C per minute.
- the second intermediate piece in AIN brazed either with ZrSi 2 -Si (in the first example) or with PrSi 2 -Si (in the second example), is replaced by a piece 5 in mullite.
- the second intermediate piece in AIN from the previous examples is replaced by a piece 5 of mullite and a metallization is carried out on the face of this part 5 facing towards part 3.
- This metallization is produced with a brazing composition known under the brand "TiCuSiI" comprising in mass percentages around 68.8% of Ag, 26.7% of Cu and 4.5% of Ti.
- brazing composition based on palladium Pd and on Ni, preferably comprising, in atomic proportions, between 35 and 55% of Pd and a balance of Ni (that is to say between 50 and 69% of Pd and between 50 and 31% of Ni in percentages by mass), can then be used to assemble the first and second intermediate pieces 3 and 5 together and to also assemble the metallic piece with the first intermediate piece.
- the method of assembling the metallic 1 and ceramic 7 pieces includes two thermal cycles and an additional metallization step between the first brazing of the piece of ceramic material 7 with the second intermediate piece 5 and the complete brazing of the assembly.
- the metal part made of Ni-based alloy used in the first example given above is replaced by a metal part 1 made of Co-based alloy, for example the alloy known under the brand "Haynes 188" and typically comprising in percentages by weight: 20 to 24% of Ni, 20 to 24% of Cr, 13 to 15% of W, at most 3% of Fe, 0.2 to 0.5% of Si, at most 1.25% of Mn, 0.5 to 0.15% of C, at least 0.015% of B, 0.02 to 0.12% of La, and a balance in Co
- the method of assembling the metallic 1 and ceramic 7 parts comprises two thermal cycles with a first temperature rise and fall cycle with a plateau at 1400 ° C. for 5 to 10 min. and a second cycle with a plateau at 1250 ° C. for 15 min.
- the first intermediate piece 3 may have a massive structure, as shown in FIG. 1. This piece 3 is then made of material that is sufficiently ductile to deform and compensate for the difference in expansion between the metallic and ceramic pieces. Of course, the dimensions of this first intermediate piece 3 and, in particular, its thickness, must be sufficient for this piece to be able to play its role. For example, for a piece of ceramic material 7 and a metal piece 1 both cylindrical of revolution, 10 mm in diameter and 5mm thick, the first intermediate piece 3 is chosen with a cylindrical shape of revolution of 10 mm in diameter and 2 mm thick and, the first intermediate piece also of cylindrical shape of revolution 10 mm in diameter and 1 mm thick.
- this piece 3 is not necessarily made of ductile alloy.
- this piece 3 can be produced from an alloy of the "Inconel 601" type (registered trademark) typically comprising, in percentages by weight, 1 to 1.7% of AI, at most 0.1% of C , 21 to 25% of Cr, at most 1% of Cu, at most 1% of Mn, 58 to 63% of Ni, at most 0.5% of Si, at most 0.015% of S, and a balance in Fe .
- FIG. 2 An example of a first intermediate piece 3 with a deformable structure is shown in FIG. 2.
- This piece is formed of a deformable sheet 3 having flat areas 11, 15 brazed and inclined areas 10 which succeed one another to form concentric undulations.
- the ply 3 comprises an inner flat area 11, substantially circular around an axis A, an outer flat area 15 substantially annular, coaxial with the inner area 11, and with an inner diameter greater than the diameter of said inner area, and at at least one intermediate, annular flat area 13 located between zones 11 and 15 and coaxial with them.
- These zones 11, 13, 15 are connected to each other by inclined zones 10 having a symmetry of revolution with respect to the axis A.
- the internal flat zone 11 is brazed to the metal part 1 while the external flat zone 15 is brazed to the second intermediate piece 5 or vice versa.
- the intermediate ripples (formed by zones 10 and 13) remain free.
- the intermediate piece 3 is formed by several ribbons folded in accordion and arranged radially around a fixed point, preferably central. These ribbons are arranged in several radial directions around said fixed point, which constitutes an arrangement of concentric undulations.
- the deformable structure consists of several parts including a spiral spring 3 arranged in a circle whose main plane is substantially parallel to the surfaces of parts 1 and 5 to be assembled, so that these surfaces rest on the side faces of the spring.
- This structure may also include at least one spiral spring of rectilinear shape, placed in the center of the circular spring 3 (not visible in FIG. 3), the axis of which is parallel to said surfaces.
- the assembly of the invention can be implemented in a turbomachine and, more particularly, in a turbojet engine.
- the invention may relate to a turbomachine nozzle comprising at least one assembly as mentioned above, in which the metal part is a casing or a lever of this nozzle and the part made of ceramic material is a component of this nozzle.
- the invention also relates to a turbomachine combustion chamber comprising at least one assembly as mentioned above, in which said metal part is a casing, a seal or, in general, a component part of this chamber, and said part. in ceramic material is another component part of this chamber.
- the invention also relates to post-combustion equipment of a turbomachine comprising at least one assembly as mentioned above, in which the metal part is an after-combustion casing or a platform, and the part made of ceramic material is a flame catching arm.
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN200680046270XA CN101326139B (zh) | 2005-12-08 | 2006-12-08 | 一种位于金属部件和碳化硅基和/或碳基陶瓷材料部件之间的装配件 |
CA2632731A CA2632731C (fr) | 2005-12-08 | 2006-12-08 | Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c |
EP06842129.6A EP1971564B1 (fr) | 2005-12-08 | 2006-12-08 | Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c. |
US12/096,663 US8177497B2 (en) | 2005-12-08 | 2006-12-08 | Joint between a metal part and a ceramic part based SiC and/or C |
JP2008543882A JP2009518270A (ja) | 2005-12-08 | 2006-12-08 | 金属ピースとSiCおよび/またはC系セラミック材料からなるピースとのアセンブリ |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0553790 | 2005-12-08 | ||
FR0553790A FR2894499B1 (fr) | 2005-12-08 | 2005-12-08 | Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c |
Publications (2)
Publication Number | Publication Date |
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WO2007066052A2 true WO2007066052A2 (fr) | 2007-06-14 |
WO2007066052A3 WO2007066052A3 (fr) | 2008-04-24 |
Family
ID=37009856
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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PCT/FR2006/051318 WO2007066052A2 (fr) | 2005-12-08 | 2006-12-08 | Assemblage entre une piece metallique et une piece en materiau ceramique a base de sic et/ou de c. |
Country Status (8)
Country | Link |
---|---|
US (1) | US8177497B2 (fr) |
EP (1) | EP1971564B1 (fr) |
JP (1) | JP2009518270A (fr) |
CN (1) | CN101326139B (fr) |
CA (1) | CA2632731C (fr) |
FR (1) | FR2894499B1 (fr) |
RU (1) | RU2427555C2 (fr) |
WO (1) | WO2007066052A2 (fr) |
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EP2233835A1 (fr) | 2009-03-23 | 2010-09-29 | Siemens Aktiengesellschaft | Chambre de combustion brasée avec des inserts en céramique |
US8141364B2 (en) | 2005-12-08 | 2012-03-27 | Snecma | Brazed joint between a metal part and a ceramic part |
US8161753B2 (en) | 2005-12-08 | 2012-04-24 | Snecma | Brazed joint between a titanium-based metal part and a ceramic part based on silicon carbide (SIC) and/or carbon |
EP2048344A3 (fr) * | 2007-10-10 | 2012-06-06 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Moteur à réaction ou à fusée avec tuyère d'éjection isolée thermiquement |
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DE102007029031A1 (de) * | 2007-06-23 | 2008-12-24 | Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. | Verfahren zum dauerhaften Verbinden zweier Komponenten durch Löten mit Glas- oder Metalllot |
CH700774A1 (de) * | 2009-03-31 | 2010-10-15 | Alstom Technology Ltd | Doppellotelement, Verfahren zu dessen Herstellung und Verwendungen desselben. |
FR2957542B1 (fr) | 2010-03-16 | 2012-05-11 | Commissariat Energie Atomique | Procede d'assemblage de pieces en materiaux a base de sic par brasage non-reactif, compositions de brasure, et joint et assemblage obtenus par ce procede. |
CN102009239B (zh) * | 2010-10-15 | 2012-09-05 | 北京航空航天大学 | 一种用于碳基材料及其制品的连接方法 |
EP2627349B1 (fr) | 2010-10-15 | 2016-02-03 | The Trustees of Columbia University in the City of New York | Gènes de l'obésité, leurs protéines et leurs utilisations |
US8876481B2 (en) * | 2011-01-05 | 2014-11-04 | General Electric Company | Turbine airfoil component assembly for use in a gas turbine engine and methods for fabricating same |
FR2984781B1 (fr) * | 2011-12-22 | 2014-01-24 | Commissariat Energie Atomique | Procede d'assemblage par brasage d'un substrat comprenant du pyrocarbone avec des pieces comprenant du pyrocarbone. |
CN103476205A (zh) * | 2012-06-08 | 2013-12-25 | 昆山同寅兴业机电制造有限公司 | 改变复合材料电子产品机壳变形度的结构 |
US9527262B2 (en) * | 2012-09-28 | 2016-12-27 | General Electric Company | Layered arrangement, hot-gas path component, and process of producing a layered arrangement |
JP5772861B2 (ja) | 2013-04-01 | 2015-09-02 | 株式会社デンソー | 接合体の製造方法 |
US9702490B2 (en) | 2013-04-30 | 2017-07-11 | Corning Incorporated | Sealing method for silicon carbide parts used at high temperatures |
US20140366544A1 (en) * | 2013-06-13 | 2014-12-18 | Pratt & Whitney Canada Corp. | Combustor exit duct for gas turbine engines |
WO2015009388A1 (fr) * | 2013-07-19 | 2015-01-22 | United Technologies Corporation | Ensemble élément constitutif céramique de moteur à turbine à gaz et liaisonnage |
JP5862630B2 (ja) | 2013-09-20 | 2016-02-16 | 株式会社デンソー | 接合体の製造方法 |
EP3055530B1 (fr) * | 2013-10-07 | 2020-08-12 | United Technologies Corporation | Paroi de dispositif de combustion assemblée par soudage pour un moteur à turbine |
US11619387B2 (en) * | 2015-07-28 | 2023-04-04 | Rolls-Royce Corporation | Liner for a combustor of a gas turbine engine with metallic corrugated member |
US11149646B2 (en) * | 2015-09-02 | 2021-10-19 | General Electric Company | Piston ring assembly for a turbine engine |
FR3045598B1 (fr) * | 2015-12-21 | 2018-01-12 | Centre National De La Recherche Scientifique | Procede de fabrication d'une ceramique a partir d'une reaction chimique |
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- 2006-12-08 US US12/096,663 patent/US8177497B2/en active Active
- 2006-12-08 CA CA2632731A patent/CA2632731C/fr active Active
- 2006-12-08 EP EP06842129.6A patent/EP1971564B1/fr active Active
- 2006-12-08 JP JP2008543882A patent/JP2009518270A/ja active Pending
- 2006-12-08 RU RU2008127506/03A patent/RU2427555C2/ru active
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Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US8141364B2 (en) | 2005-12-08 | 2012-03-27 | Snecma | Brazed joint between a metal part and a ceramic part |
US8161753B2 (en) | 2005-12-08 | 2012-04-24 | Snecma | Brazed joint between a titanium-based metal part and a ceramic part based on silicon carbide (SIC) and/or carbon |
EP2048344A3 (fr) * | 2007-10-10 | 2012-06-06 | Bayern-Chemie Gesellschaft für flugchemische Antriebe mbH | Moteur à réaction ou à fusée avec tuyère d'éjection isolée thermiquement |
EP2233835A1 (fr) | 2009-03-23 | 2010-09-29 | Siemens Aktiengesellschaft | Chambre de combustion brasée avec des inserts en céramique |
Also Published As
Publication number | Publication date |
---|---|
FR2894499B1 (fr) | 2011-04-01 |
RU2008127506A (ru) | 2010-01-20 |
EP1971564A2 (fr) | 2008-09-24 |
CA2632731A1 (fr) | 2007-06-14 |
CN101326139A (zh) | 2008-12-17 |
FR2894499A1 (fr) | 2007-06-15 |
CA2632731C (fr) | 2016-02-02 |
JP2009518270A (ja) | 2009-05-07 |
RU2427555C2 (ru) | 2011-08-27 |
US8177497B2 (en) | 2012-05-15 |
EP1971564B1 (fr) | 2018-03-14 |
CN101326139B (zh) | 2013-06-05 |
US20080304959A1 (en) | 2008-12-11 |
WO2007066052A3 (fr) | 2008-04-24 |
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