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Definitions

• the present invention aims to improve the resistance to oxidation of thermostructural composite materials having a carbon fiber reinforcement or coated with carbon.
• Thermostructural composite materials are materials comprising a fibrous reinforcement, or fibrous preform, the fibers of which are made of refractory material, such as carbon or ceramic, and a matrix at least partially filling the initial porosity of the fibrous reinforcement. These materials are remarkable for their mechanical properties, which allow them to be used for structural elements, and for their ability to maintain these properties at high temperatures, in particular when the matrix is ceramic. Generally, the ceramic matrix of such composite materials is subject to cracking. The presence of cracks is already noted at the stage of the preparation of the material, in particular when the matrix is subjected to thermal stresses due to its obtaining by chemical vapor infiltration or by impregnation by means of a liquid precursor and transformation. of the ceramic precursor by heat treatment. These initial cracks then multiply under the effect of the thermomechanical stresses encountered during the use of the material. However, thanks to the presence of the fibrous reinforcement, the damaging nature of the material by cracking of the matrix does not immediately affect its integrity, thus giving thermo ⁇ structural characteristics to the material.
• Thermostructural composite materials find applications in different fields where their capacity to withstand high mechanical stresses under high temperatures is exploited, in particular in the aeronautics, space and braking fields. In their use, these materials are most often exposed to an oxidizing external environment, in particular ambient air.
• the reinforcing fibers are made of an oxidizable material, such as carbon
• the combination of a network of cracks within the matrix, an oxidizing environment and a high temperature leads inexorably to the destruction of the fibers and, consequently, to the collapse of the mechanical properties of the material.
• the carbon is present in the material not at the level of the fibers of the reinforcement, but at the level of an interphase between ceramic fibers and a ceramic matrix.
• the realization of such a pyrolytic carbon interphase and its utility for improving the mechanical behavior of the material are well known in the state of the art. Reference may in particular be made to document EP-A-0 172082 by the applicant.
• the protective coating comprises at least one self-healing layer, generally a vitreous layer which, by the passage of the glass in a pasty state, allows the filling of cracks at temperatures exceeding the melting point of the glass.
• the healing effect can only be obtained satisfactorily in a limited range of temperatures. At lower temperatures, the viscosity of the glass is too high, while at higher temperatures the viscosity becomes too low and the self-healing composition may be damaged by friction, shearing, or even by blowing, that is to say say by exposure to a strong gas stream.
• Another known solution consists in producing a sequenced matrix, by forming the matrix by layers of materials having alternatively relatively high rigidity, in particular a ceramic material, and a relatively low shear rigidity, in particular of pyrolytic carbon of rough laminar type or of boron nitride.
• a solution is described in particular in document EP-A-0 385 869 by the applicant.
• the sequencing of the matrix has the effect of complicating the mode of propagation of the cracks and, consequently, of slowing down the diffusion of oxygen inside the material.
• the oxidation of a reinforcement in carbon fibers or in fibers coated with carbon is only slowed down. We do not can necessarily avoid an initial cracking within the rigid layers, which propagates sooner or later towards the fibers according to the thermomechanical stresses to which the material is exposed.
• the object of the present invention is to remedy the drawbacks of the methods of the prior art.
• the object of the invention is more particularly to improve the resistance to oxidation of a thermostructural composite material with ceramic matrix and reinforcement in carbon fibers or coated with carbon by carrying out a sequencing of the matrix such that the cracking of the matrix can be delayed as much as possible.
• a matrix is formed by chemical vapor infiltration within a fibrous reinforcement at least partially in a sequenced manner by alternating the formation of a layer of a relatively flexible material capable of deflecting any cracks which reach it and a layer of relatively rigid ceramic material, process in which:
• each elementary sequence of matrix comprising a relatively flexible layer and a relatively rigid ceramic layer is formed with a thickness which varies increasingly from the fibers of the reinforcement, as the matrix is produced, the thickness total of at least the elementary matrix sequence deposited first on the fibers being chosen to be sufficiently small to sheath the fibers essentially individually, and
• the relatively flexible layers are made of one or more anisotropic materials having a sufficient capacity for elastic deformation in shear and transverse, and the thickness of the elementary relatively flexible layers is chosen to be sufficiently large, while retaining a mainly ceramic character in the matrix, to be able to absorb the differential expansions of the constituents of the composite material at the stage of its preparation without inducing the existence of an initial cracking network.
• thermostructural composite material having a mainly ceramic matrix which, at the stage of the preparation of the composite material, shows no initial cracking.
• the sheathing of the fibers by concentric layers means that the differential expansions are absorbed in the vicinity of the fibers by the capacity for elastic deformation in transverse, that is to say radial, direction of the relatively flexible layer or layers arranged concentrically around each fiber, without inducing cracking of the adjacent relatively rigid ceramic layers.
• the individual sheathing of the fibers results in the formation of sheathed fibers having an apparent diameter greater than that of the initial fibers of the fibrous reinforcement but which, within the composite material, behave mechanically, in the same way. as unsheathed reinforcing fibers. This increase in the diameter of the fibers then makes it possible at the outset to use a fibrous reinforcement consisting of fibers of smaller diameter and / or having a lower volume content of fibers;
• the relatively flexible layers of one or more materials chosen from those having an anisotropic nature and an elastic deformation capacity in shear and in transverse direction relative to the layers.
• materials are for example chosen from pyrolytic carbon, in particular pyrolytic carbon of the rough laminar type, boron nitride, carbon doped with boron, and other materials having equivalent properties capable of being formed by chemical vapor infiltration.
• the material or materials of the relatively flexible layers can be chosen from materials capable of constituting a self-healing compound, such as a glass, under the effect of an oxidation.
• the total thickness of the relatively flexible layers representing for example between approximately 4% and approximately 20% of the thickness total of the layers forming the sequenced matrix.
• the percentage S represented by the thickness of the relatively flexible layer compared to the total thickness of the sequence can decrease between a maximum value Smax in the elementary sequence formed first on the fibers and a minimum value Smin in the last elementary matrix sequence.
• the Smax value is for example between approximately 10% and approximately 35% while the Smin value is for example between approximately 3% and approximately 20%.
• the particular sequencing adopted in particular in the distribution and the relative thicknesses of the relatively flexible layers, can ensure that during the exposure of the composite material to stresses thermomechanical, non-damaging behavior is first observed, which makes it possible to have a material having a deformation of the linear elastic type up to a certain threshold of stresses. Beyond this threshold, we find behavior with progressive cracking of the ceramic layers, therefore outside the elastic linear range, but the capacity for deflection and, possibly, healing of the cracks offered by the relatively flexible layers further delays the risk of 'direct exposure to the oxygen of the carbon making up the fibers or their coating.
• the layers of relatively rigid ceramic material forming part of the matrix can be of the same ceramic material or of several different ceramic materials.
• the ceramic material or materials may be chosen from carbides, borides and silicides, for example from boron carbide B13C2 and silicon carbide SiC.
• each layer of the matrix is formed by chemical vapor infiltration in pulsed mode, that is to say by a succession of cycles leading to elementary deposits.
• chemical infiltration in the vapor phase in pulsed mode allows precise control of the microstructure of the deposits formed.
• - Figure 1 a photograph obtained with an electron scanning microscope showing a wick of carbon fibers densified by a matrix sequenced according to a method according to the invention
• - Figures 2A and 2B tensile curves at room temperature showing the relationship until rupture between the measured deformation and the applied tensile stress, respectively for composite materials with monolithic matrix of the prior art and composite materials with matrix sequenced according to the invention
• a fibrous reinforcement consisting of wicks of carbon fibers of the "T300" type sold by the Japanese company Toray Industries, each wick comprising approximately 3,000 elementary fibers.
• the fibrous reinforcements are densified by a matrix which is produced by repeating the two successive sequences BC / B13C2 and BC / SiC, that is to say a first sequence comprising:
• each layer of each sequence is formed by chemical vapor infiltration in pulsed mode.
• the fibrous reinforcement is placed in an enclosure where predetermined temperature and pressure conditions are established.
• a volume of the reaction gas phase giving the desired deposit is admitted into the enclosure and remains there for a determined period, before evacuation of the gaseous species from the enclosure and introduction again of a new volume of gas phase.
• the cycle including the introduction of the gas phase into the enclosure, the stay of the gas phase inside the enclosure and the evacuation of gaseous species out of the enclosure is repeated the number of times necessary to reach the desired deposit thickness.
• a reactive gas phase is used comprising a mixture of boron trichloride BCI 3 , propane C3H8 and hydrogen gas FK
• the infiltration conditions in pulsed mode are:
• T is the temperature in the infiltration chamber
• P is the total pressure in the infiltration chamber
• ⁇ (BCI3) is the ratio between flow of H2 and flow of BCI 3
• ⁇ (C 3 H8) is the ratio between flow of Hi and flow of C3H8 Dp is time of stay for each cycle
• K ⁇ J is the thickness of the elementary deposit formed during each cycle.
• a reactive gas phase comprising boron trichloride BCI 3 , hydrogen gas Fb, and methane CH 4 as reaction species.
• the infiltration conditions in pulsed mode are:
• a characterization of the deposit by forming a relatively thick layer on a sample of fibers does indeed show a composition close to the rhombohedral carbide B13C2, while the X-ray diffraction spectrum reveals an amorphous deposit.
• a gas phase comprising methyltrichlorosilane (MTS) and hydrogen gas Eb as reactive species.
• MTS methyltrichlorosilane
• Eb hydrogen gas
• 150 mm long fibrous reinforcing strands are densified by a matrix constituted by the repetition of the double sequence
• the volume ratio of the fibers in the initial wick is 24% (percentage of the apparent volume of the wick actually occupied by the fibers).
• Two first double sequences are produced in which the thickness of the layers BC is 0.1 ⁇ m, the thickness of the layer B13C2 is 0.4 ⁇ m and the thickness of the layer SiC is 0.4 ⁇ m, giving a total thickness of 1 ⁇ m.
• a third double sequence is carried out in which the thickness of the deflecting layers BC is 0.2 ⁇ m, the thickness of the layer B13C2 is 2 ⁇ m and the thickness of the SiC layer is 2 ⁇ m, giving a total thickness of 4.4 ⁇ m.
• a fourth double sequence is carried out in which the thickness of the deflecting layers BC is 0.2 ⁇ m, the thickness of the layer B13C2 is 3 ⁇ m and the thickness of the layer SiC is 3 ⁇ m, giving a total thickness of 6.4 ⁇ m.
• the total thickness of the relatively flexible layers BC is therefore equal to 1.2 ⁇ m.
• FIG. 1 is a snapshot under the scanning electron microscope of a section of the material densified by the sequenced matrix.
• the carbon fibers are coated individually with the layers formed during the first two sequences, with the exception of the contact zones between the fibers, these layers being arranged concentrically around the fibers.
• the layers formed during the third infiltration sequence envelop groups of fibers, while the layers formed during the fourth infiltration sequence practically surround the wick of fibers. Observations under the microscope reveal that, remarkably, no initial cracking is present in the matrix.
• a first tensile test at room temperature is carried out on a wick densified by the sequenced matrix.
• Curve B in FIG. 2A shows the relative elongation measured (in%) as a function of the tensile force exerted, until breaking which occurs at around 460 MPa.
• a second traction test was performed at 700 ° C in air after applying an outer coating consisting of P2O5 type of glass, in order to achieve an anti-oxidation protection for the duration of the test.
• Curves B in FIG. 3A show the relationships between elongation and stress during several stretch-relaxation cycles.
• a third tensile test is carried out after aging at
• Wicks of carbon fibers are densified by a sequenced matrix in the same way as in Example 1, except for the thickness of the relatively flexible layers BC which is halved, giving a total thickness of 0.6 ⁇ m.
• the microscopic observation of the composite material thus produced does not reveal any initial cracking network within the matrix.
• Curve A in FIG. 2A shows the relationship between the relative elongation and the force exerted during a tensile test carried out at ambient temperature until a strand thus densified by a sequenced matrix breaks.
• Wicks of carbon fibers are densified by a sequenced matrix in the same way as in Example 1, except for the thickness of the relatively flexible layers BC which is multiplied by two, giving a total thickness of 2.4 ⁇ m.
• the microscopic observation of the composite material thus produced does not reveal any initial cracking network within the matrix.
• Curve C in FIG. 2A shows the relationship between the relative elongation and the force exerted during a tensile test carried out at ambient temperature until a strand thus densified by a sequenced matrix breaks.
• Comparative Example 1 By way of comparison, strands of fibers such as those used in Example 1 are densified by a monolithic matrix of silicon carbide, after formation on the fibers of a rough laminar type pyrolytic carbon interphase coating.
• the pyrolytic carbon interphase is formed by chemical vapor infiltration in pulsed mode, from methane C3H8 as a gaseous precursor.
• the infiltration conditions are:
• the number of cycles is chosen so as to reach a thickness of 2.4 ⁇ m for the interphase coating.
• the silicon carbide matrix is formed by chemical infiltration in pulsed mode, from a gas phase containing methyltrichlorosilane (MTS) and hydrogen rb as reactive species.
• the infiltration conditions are:
• a first tensile test at room temperature is carried out on a wick densified by the SiC matrix.
• Curve D in FIG. 2B shows the relative elongation measured as a function of the tensile force exerted, until breaking which occurs at around 405 MPa.
• a second tensile test is carried out at 700 ° C. in air after application of an external coating consisting of a glass of the P2O5 type in order to provide anti-oxidation protection for the duration of the test.
• Curves D in FIG. 3B show the relationship between elongation and stress during several stretch-relaxation cycles.
• FIG. 2B shows that the composite material with an unsequenced SiC matrix exhibits a non-linear behavior from the start of the mechanical stress, which is associated with the damage mechanisms of the matrix and of the intrphase initiated from the start of the process of material development.
• FIG. 2A shows that composite materials with a sequenced matrix with deviating layers of cracks BC exhibit a linear initial behavior. The stress corresponding to the start of the non-linearity is higher the lower the total thickness of the layers BC, however the rupture is less fragile for a total thickness of 1.2 ⁇ m.
• FIG. 3B shows that when hot, with external anti-oxidation protection, the damage phase extends to a higher stress level than when cold for the composite material with an unsequenced SiC matrix.
• the hot behavior of composite materials with a sequenced matrix is little different from cold behavior: it is linear at the start, then damaged.
• the damage phase is much more extensive. The stress levels and elongation at break achieved are quite high: around 800 MPa and 1%.
• FIG. 4 shows, after aging in air, a tensile behavior of the same type as that observed at ambient temperature or hot for the composite material with a sequenced matrix.
• the breaking strain appears, however, to be greater than during the tensile test at room temperature without aging.
• a remarkable property of the composite material produced in accordance with the invention resides in the absence of an initial cracking network resulting from the manufacturing process.
• the individual or essentially individual sheathing of each fiber of the fibrous reinforcement by at least one matrix sequence comprising a relatively flexible layer and a relatively rigid layer contributes to making it possible to absorb the differential expansions without inducing cracking of the rigid layers.
• the thickness of the first or first sequences deposited must therefore be relatively small and take into account the volume ratio of fibers in the fibrous reinforcement, that is to say the fraction of the apparent volume of the reinforcement actually occupied by the fibers. Generally, this thickness is preferably chosen to be less than 1 micron.
• the thickness of the matrix sequences formed after that (s) sheathing the fibers is increasing continuously or in stages, the sequences successively coating groups of fibers and then strands of fibers. Indeed, this increase in thickness, which can be more marked for the rigid layers than for the flexible layers, does not affect the overall capacity of the matrix to absorb the differential expansions between the constituents of the composite material and prevents multiplication unnecessary number of sequences, multiplication which would result in a significant increase in the time and cost of preparation of the material.
• the gradual increase in thickness achieved more markedly for the layers relatively rigid ceramics also allows the matrix to retain its essentially ceramic character.
• the thickness of the sequences formed successively can increase from a value between approximately 0.2 micron and 1 micron to a value greater than 2 microns, while, in successive sequences, the percentage S represented by l the thickness of the relatively flexible layer relative to the total thickness of the block can decrease from a value of between approximately 10% and approximately 35% to a value comprised between approximately 3% and approximately 20%.
• boron-doped carbon, BC is suitable for producing relatively flexible layers, because of its anisotropic nature and its capacity for elastic deformation in shear and transversely. Boron-doped carbon BC also has the advantage of having better resistance to oxidation.
• other materials, which do not necessarily have the property of self-healing may be suitable, for example pyrolytic carbon, in particular of the rough laminar type, and boron nitride BN.
• the relatively rigid layers consist of a ceramic material capable of being deposited by chemical vapor infiltration, for example a carbide, a boride, a silicide, or any other ceramic capable of allowing healing of cracks when they appear.
• a ceramic material capable of being deposited by chemical vapor infiltration for example a carbide, a boride, a silicide, or any other ceramic capable of allowing healing of cracks when they appear.
• the same material may always be used, as in examples 1 to 3, or different materials may be chosen, alternating or not in the successive sequences.
• the same material may always be used, or different materials may be chosen, as in examples 1 to 3, alternating or not in the successive sequences.

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• 1995
  • 1995-12-14 FR FR9514843A patent/FR2742433B1/fr not_active Expired - Fee Related
• 1996
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