Patent Application
20200325076
The invention relates to a method for manufacturing a composite material part provided with a sensor, in particular for aeronautical applications.
It is well known that composite material parts are instrumented with measuring sensors to determine the physical or chemical stresses to which these parts are subjected. Sensors are usually attached to one or more surfaces of the part by means of holding members. The measurements returned by the sensors then provide access to the real stresses seen by the part in operation, such as temperature, pressure or deformation of the part.
In practice, the holding members of the sensors are fixed to a surface of the part by means of a ceramic glue. The measuring sensors are then inserted into housings defined by the holding members. Such instrumentation must then be held on the part for several hundred hours.
However, when the part is subjected to high loads, e.g. severe vibratory stress, it is possible that some holding members may become detached from the underlying part to which they are attached. The detachment of these holding members can then lead to the loss of the measurements of the sensors that were previously housed in these devices. It would therefore be advisable to reinforce the holding members on the composite part in order to limit the potential risk of detachment of these devices.
The purpose of the present invention is to improve the holding of measuring sensors on the surface of a composite material part.
For this purpose, the invention provides a method for manufacturing a composite material part provided with a sensor, the method comprising at least the following steps:
A preform is said to be in the consolidated state when it has undergone a consolidation stage during which its initial porosity has been partially filled by a deposition of a consolidation phase, this preform in the consolidated state retaining a residual porosity which may be wholly or partially filled during the subsequent co-densification stage. Various examples of consolidation methods are detailed below. A preform is said to be in the unconsolidated state when it does not have such a consolidation phase.
The assembly of the first and second preforms is intended to form, after co-densification, the fibrous reinforcement of a one-piece composite material structure, which includes the holding member. Advantageously, the co-densification of the preform of the part and the preform of the holding member allows a better adhesion of the holding member to the underlying part. This strengthens the hold of the measuring sensors on the part.
In an example embodiment of this method, the holding member comprises two parts forming legs connected to the part and located on either side of the housing, and a joining part closing the housing on the side opposite the part and connecting the legs.
In an example embodiment of this method, the holding member comprises two spaced holding elements located on either side of the housing, with the spacing between the two holding elements decreasing with distance from the part.
In example embodiment of this method, co-densification is achieved by chemical vapor infiltration.
In another example embodiment of this method, co-densification is carried out by a liquid process.
In an example embodiment of this method, a silicon carbide matrix is deposited in the porosity of the first and second preforms during co-densification.
In an example embodiment of this method, the sensor is a temperature sensor.
In example embodiment of this method, the part is a nozzle diverter.
Other features and advantages of the invention will be apparent from the following description of particular embodiments of the invention, given by way of non-limiting examples, with reference to the appended drawings, wherein:
The first preform 1 and the second preform 2 are fibrous preforms, each made by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns.
The multilayer weave produced can be in particular an interlock weave, i.e. a weave in which each layer of weft threads binds several layers of warp yarns with all the yarns of the same weft column having the same movement in the plane of the weave. Alternatively, each layer of warp yarns binds several layers of weft yarns with all the yarns of the same warp column having the same movement in the plane of the weave, the roles between the warp and weft yarns being interchangeable.
Other types of multilayer weaving may be used. Different types of multilayer weaving that can be used are notably described in WO 2006/136755.
In an example embodiment, the first and second fibrous preforms 1, 2 can be formed from carbon yarns. Alternatively, the first and second fibrous preforms 1, 2 can be formed from ceramic yarns such as silicon carbide yarns.
Thus, in an example embodiment, the yarns used may be silicon carbide (SiC) yarns supplied under the name “Nicalon”, “Hi-Nicalon” or “Hi-Nicalon-S” by the Japanese company Nippon Carbon or “Tyranno SA3” by the company UBE and having for example a titer (number of filaments) of 0.5K (500 filaments).
In the example shown in
After weaving, the first fibrous preform 1 can optionally, but not necessarily, be consolidated by depositing a consolidation phase in the porosity of the first preform 1, which consolidation phase can be deposited in a gas or liquid process in a manner known per se.
The liquid process consists of impregnating the preform with a liquid composition containing a precursor of the material of the consolidation phase. The precursor is usually in the form of a polymer, such as a resin, optionally diluted in a solvent. The preform is placed in a sealable mold. Then the mold is closed and the liquid precursor of the consolidation phase (for example a resin) is injected into the mold to impregnate the preform.
The transformation of the precursor in the consolidation phase is carried out by heat treatment, generally by heating the mold, after removal of any solvent and cross-linking of the polymer.
In the case of the formation of a consolidation phase in ceramic material, the heat treatment includes a step of pyrolysis of the precursor to form the consolidation phase in ceramic material. For example, liquid ceramic precursors, especially SiC, can be polycarbosilane (PCS) or polytitanocarbosilane (PTCS) or polysilazane (PSZ) resins. Several consecutive cycles, from impregnation to heat treatment, can be carried out to achieve the desired consolidation.
In the gas process (chemical vapor infiltration (CVI) of the consolidation phase), the fibrous preform is placed in a furnace in which a reactive gas phase is admitted. The pressure and temperature prevailing in the furnace and the composition of the gas phase are chosen so as to allow the diffusion of the gas phase within the porosity of the preform in order to form the consolidation phase there by depositing, at the core of the material in contact with the fibers, a solid material resulting from the decomposition of a constituent of the gas phase or from a reaction between several constituents.
The formation of a SiC consolidation phase can be achieved with methyltrichlorosilane (MTS) yielding SiC by decomposition of MTS.
Furthermore, the second preform 2 may or may not be consolidated before being assembled with the first preform 1.
The preforms 1, 2 are then joined together by superimposition, so that after co-densification they form the fiber reinforcement of a single-piece composite structure. In the example shown in
Once assembled together, the preforms 1, 2 undergo a co-densification step. A structure is obtained after co-densification in which the first and second preforms are densified and the parts forming legs 2-1 and 2-2 are attached to the underlying part by co-densification.
The co-densification of the first and second preforms 1, 2 can be achieved by a liquid process.
In a first example, liquid co-densification is achieved by melt infiltration. There is first introduction, into the porosity of the first and second assembled preforms 1, 2, of fillers, for example reactive fillers, the fillers being for example selected from SiC, Si3N4, C, B, and mixtures thereof. The introduction of the fillers may, for example, be carried out by slurry cast, by suction of sub-micron powders (APS) or by an injection process of the resin transfer molding (RTM) type in which a heat treatment is carried out after injection to evaporate the liquid medium.
Once the fillers have been introduced, the first and second preforms 1, 2 are then infiltrated with a melt infiltration composition comprising for example silicon to form a matrix co-densifying the first and second preforms 1 and 2. As shown in
When reactive fillers are used, substantially all of the reactive fillers may be consumed during the reaction between the infiltration composition and the reactive fillers. Alternatively, only part of the reactive charge is consumed during this reaction.
In an example embodiment, the melt infiltration carried out can enable a matrix to be obtained by reaction between solid fillers, for example type C, SiC or Si3N4 introduced by slurry or prepreg, and a molten silicon-based alloy. The reaction can occur at a temperature of 1420° C. or higher. In view of the high temperatures involved, it may be advantageous for at least part of the first and second preforms to be made of heat-stable fibers, for example Hi-Nicalon or Hi-Nicalon S type.
The matrix formed by co-densification can be made of ceramic material or carbon.
In a second example, liquid co-densification is carried out by injecting and then polymerizing a resin in a similar way to what was mentioned above for consolidation. The polymerization step may possibly, but not necessarily, be followed by a pyrolysis step.
Alternatively, the co-densification of the first and second preforms 1, 2 can be carried out by chemical vapor infiltration in order to obtain the composite part 10 provided with the holding member 11. This type of process is carried out in a similar way to what was mentioned above for consolidation.
The yarns of the first and second preforms may, prior to co-densification, have been coated with an interphase layer, for example of PyC, BN or silicon-doped BN, and optionally with a carbide layer, for example of SIC or Si3N4.
Whichever co-densification process is chosen, the result is a one-piece structure of composite material with a profile corresponding to that of the assembly of the preforms 1, 2. The structure thus obtained consists of the part 10 with at least one holding member 11. In the example shown in
In the example shown in
At least one measuring sensor is then inserted in the housing 32. Thus, in the example shown, two measuring sensors 40 are inserted in the housing 32. Furthermore, in order to secure the holding of the sensors 40 present in the housing 32, the spacing between the holding elements 31-1, 31-2 is made to decrease with distance from the part 30. Thus, in the example shown, each holding element 31-1, 31-2 is made to have a beveled shape, with the bevels moving closer together with distance from the part 30.
In addition, in order to limit the movements of the measuring sensors 40 positioned in the housing 32, an adhesive 50, for example ceramic glue, can optionally, but not necessarily, be deposited in the housing 32 so as to fill the residual space between the two holding elements 31-1, 31-2 and the surface 30-1.
Two plates provided with holding members 11, 31 and made of the same composite material, here carbon fiber reinforced carbon (C/C), were manufactured according to the previously described process for mechanical testing. A first plate, referred to below as “Plate No. 1” was directly subjected to shear forces exerted by mechanical testing means. A second plate, manufactured in a similar manner to plate No. 1 and referred to below as “plate No. 2” was subjected to thermal shock at 1400° C. and then underwent shear forces similar to those of plate No. 1. The shear stresses were applied in order to identify the thresholds leading to the detachment of the holding members 11, 31 of Plates No. 1 and No. 2. The table below gives the values of the rupture thresholds that were measured to obtain the pull-out of the holding members 11, 31 of Plates No. 1 and No. 2.
In general, it can be observed that the application of thermal shock to Plate No. 2 had a small impact on the measured thresholds compared to Plate No. 1, which did not undergo such thermal shock. In addition, the holding members 11 and 31 have a very satisfactory shear strength. Indeed, the shear forces required to pull out the holding members 11, 31 from Plates No. 1 and No. 2 are about ten times higher than thresholds measured in the past for which sensor holding members were fixed to a plate by means of a ceramic glue. Furthermore, it can be observed that the holding members 31 seem to have an even better shear strength than the holding members 11, which already have a very high shear strength. Thus, the results obtained confirm that the manufacture of a composite material part provided with at least one holding member, obtained by co-densification of a preform of the part with at least one preform of a holding member, considerably improves the strength of the holding member or members secured to the composite part.
As shown in
| Number | Date | Country | Kind |
|---|---|---|---|
| 1758254 | Sep 2017 | FR | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/FR2018/052184 | 9/6/2018 | WO | 00 |
