Method of manufacturing a composite sandwich panel for an aircraft propulsion unit
US-10239227-B2 · Mar 26, 2019 · US
US11255203B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11255203-B2 |
| Application number | US-201816649372-A |
| Country | US |
| Kind code | B2 |
| Filing date | Sep 19, 2018 |
| Priority date | Sep 21, 2017 |
| Publication date | Feb 22, 2022 |
| Grant date | Feb 22, 2022 |
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A method for manufacturing a part made of composite material includes injecting into a fibrous texture a slurry including at least one powder of refractory ceramic particles suspended in a liquid phase, filtering the liquid phase of the slurry and retaining the powder of refractory ceramic particles inside the texture so as to obtain a fibrous preform loaded with refractory ceramic particles, densifying the fibrous texture by treatment of the refractory ceramic particles present in the fibrous texture in order to form a refractory matrix in the texture. The method further includes, before injecting the slurry under pressure, pre-saturating the fibrous texture with a carrier fluid consisting in injecting into said texture a carrier fluid.
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The invention claimed is: 1. A method for manufacturing a part made of composite material comprising the following steps: forming a fibrous texture from refractory ceramic fibers, placing the fibrous texture in a mold cavity of an injection tooling, injecting under pressure and into the fibrous texture, placed in the mold cavity, a slurry including at least one powder of refractory ceramic particles or particles of a refractory ceramic precursor suspended in a liquid phase, filtering the liquid phase of the slurry using a filter of porous material provided with the mold cavity and retaining the powder of refractory ceramic particles or particles of a refractory ceramic precursor inside said fibrous texture so as to obtain a fibrous preform loaded with refractory ceramic particles or particles of a refractory ceramic precursor, densifying the fibrous texture by treatment of the refractory ceramic particles present in the fibrous texture in order to form a refractory matrix in said texture, wherein, after the step of placing the fibrous texture in the mold cavity of the injection tooling and before the step of injecting the slurry under pressure, the method comprises a step of pre-saturating the fibrous texture with a carrier fluid consisting of a liquid, the pre-saturating step consisting of injecting said carrier fluid into said fibrous texture while placed inside the mold cavity, said carrier fluid being filtered with said liquid phase of the slurry during the filtering, and wherein the injection tool comprises means for regulating a flow rate such that the step of pre-saturating the fibrous texture inside the mold cavity comprises regulating the flow rate of the injection of the carrier fluid. 2. The method according to claim 1 , wherein the carrier fluid corresponds to the liquid phase of the slurry. 3. The method according to claim 1 , wherein the carrier fluid pre-saturation step and the slurry injection step are performed continuously. 4. The method according to claim 1 , wherein the pre-saturation step is stopped when pressure in the mold cavity reaches a predetermined pressure value. 5. The method according to claim 1 , wherein, during the pre-saturation step, the carrier fluid is injected at a first determined flow rate and wherein, during the slurry injection step, said slurry is injected at a second determined flow rate similar to or different from the first flow rate. 6. The method according to claim 1 , wherein, during the fibrous texture formation step, yarns are woven in a three-dimensional or multilayer weaving. 7. The method according to claim 1 , wherein yarns of the fibrous texture are formed of fibers made of one or several of the following materials: alumina, mullite, silica, an aluminosilicate, a borosilicate, silicon carbide and carbon. 8. The method according to claim 1 , wherein the refractory ceramic particles are made of a material chosen from: alumina, mullite, silica, an aluminosilicate, an aluminophosphate, zirconia, a carbide, a boride and a nitride. 9. The method according to claim 1 , wherein the part made of composite material obtained constitutes a turbomachine vane, an after-body part, a combustion chamber, a flap, a post-combustion arm, a turbine ring, a mixer or a distributor.
Jet pipe walls, e.g. liners · CPC title
Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title
forming ring or sector · CPC title
Selection of ceramic materials · CPC title
Fibres, filaments, whiskers, platelets, or the like · CPC title
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