Patent application number | Description | Published |
20080299385 | Method for Making a Part of Composite Material with Ceramic Matrix and Resulting Part - An interphase coating is formed by chemical vapor infiltration (CVI) on the fibers constituting a fiber preform, the interphase coating comprising at least an inner layer in contact with the fibers for embrittlement relief to the composite material, and an outer layer for bonding with the ceramic matrix. The fiber preform is then kept in its shape by the fibers provided with the interphase coating and is consolidated by being impregnated with a liquid composition containing a ceramic precursor, and by transforming the precursor into a ceramic matrix consolidation phase. The consolidated preform is then densified by an additional ceramic matrix phase. No support tooling is needed for forming the interphase coating by CVI or for densification after consolidation using the liquid technique. | 12-04-2008 |
20100005780 | METHOD OF MANUFACTURING A CMC FLOW MIXER LOBED STRUCTURE FOR A GAS TURBINE AEROENGINE - A method of fabricating a lobed structure for a gas turbine flow mixer having an annular upstream portion extended downstream by a portion forming a multilobed skirt, the method comprising:
| 01-14-2010 |
20100009143 | PROCESS FOR MANUFACTURING A PART MADE OF A CERAMIC MATRIX COMPOSITE CONTAINING MATRIX PHASES FOR HEALING AND DEFLECTING CRACKS - The method comprises the steps of: forming a porous fiber-reinforcing structure; introducing into the pores of the fiber structure powders containing elements for constituting the composite material matrix; and forming at least a main fraction of the matrix from said powders by causing a reaction to take place between said powders or between at least a portion of said powders and at least one delivered additional element; the powders introduced into the fiber structure and the delivered additional element(s) comprising elements that form at least one healing discontinuous matrix phase including a boron compound and at least one discontinuous matrix phase including a crack-deflecting compound of lamellar structure. At least a main fraction of the matrix is formed by chemical reaction between the powders introduced into the fiber structure and at least one delivered additional element, or by sintering the powders. | 01-14-2010 |
20100015428 | METHOD OF FABRICATING A THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND A PART OBTAINED THEREBY - The method comprises: | 01-21-2010 |
20100086679 | PROCESS FOR MANUFACTURING A THERMOSTRUCTURAL COMPOSITE PART - The invention relates to a method of fabricating a composite material part comprising fiber reinforcement densified by a matrix, the method comprising the steps of:
| 04-08-2010 |
20110200748 | METHOD FOR PRODUCING PARTS MADE OF A THERMOSTRUCTURAL COMPOSITE MATERIAL - A method of fabricating a thermostructural composite material part includes making a fiber preform formed of yarns or tows and impregnated by a consolidating composition containing a carbon- or ceramic-precursor, transforming the carbon- or ceramic-precursor by pyrolysis, and then densifying the preform by chemical vapor infiltration. A consolidating composition is used that additionally contains refractory solid fillers in the powder form presenting mean grain size less than 200 nanometers and leaving, after pyrolysis, a consolidated solid phase in which the carbon or the ceramic derived from the precursor occupies a volume representing 3% to 10% of the apparent volume of the preform, and the solid fillers occupy a volume representing 0.5% to 5% of the apparent volume of the preform. | 08-18-2011 |
20120020863 | METHOD FOR PROCESSING CERAMIC FIBERS - A method of treating ceramic fibers based on metal carbide, the method including a first reagent gas heat treatment performed with at least one first reagent gas of the halogen type that chemically transforms the surface of the fiber to obtain a surface layer constituted mainly of carbon, and a second reagent gas heat treatment performed with at least one second reagent gas that eliminates the surface layer formed during the chemical transformation. | 01-26-2012 |
20120196107 | METHOD OF FABRICATING A THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND A PART OBTAINED THEREBY - The method comprises:
| 08-02-2012 |
20120301691 | LOW-THICKNESS THERMOSTRUCTURAL COMPOSITE MATERIAL PART, AND MANUFACTURE METHOD - A thermostructural composite material part including carbon or ceramic fiber reinforcement densified by a matrix having at least one thin portion in which: the thickness of the part is less than 2 mm, or indeed less than 1 mm; the fiber reinforcement is made as a single thickness of multilayer fabric made of spread yarns having a weight of not less than 200 tex; the fiber volume ratio lies in the range 25% to 45%; and the ratio between the number of layers of the multilayer fabric and the thickness in millimeters of the part is not less than four. | 11-29-2012 |
20140315458 | METHOD OF TREATING CERAMIC FIBERS BY PHOSPHATING - A method of treating silicon carbide fibers comprises phosphating heat treatment in a reactive gas so as to form a coating around each fiber for protection against oxidation. The coating comprises a surface layer of silicon pyrophosphate crystals and at least one underlying bilayer system comprising a layer of a phosphosilicate glass and a layer of microporous carbon. | 10-23-2014 |
20150082589 | METHOD OF FABRICATING A COMPOSITE MATERIAL PART WITH IMPROVED INTRA-YARN DENSIFICATION - A method of fabricating a composite material part comprises fiber reinforcement densified by a matrix. The method comprises the following steps: making a fiber fabric by weaving yarns having an initial mean fiber percentage; and densifying the fiber fabric with a matrix. The fiber fabric is subjected, prior to densification, to one or more jets of water under pressure so as to reduce the mean fiber percentage in the fabric to a value lying in the range 20% to 45%. | 03-26-2015 |
20150083822 | INTEGRATING AFTER-BODY PARTS OF AN AEROENGINE - The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs. | 03-26-2015 |