Method for manufacturing a part of revolution from composite material with locally optimized properties and the resulting part of revolution
The method enhances debris retention and structural integrity of composite material gas turbine housings by using unidirectional fibrous layers and high elongation fibers, addressing vibrational stress issues and preventing crankcase failure.
Patent Information
- Authority / Receiving Office
- FR · FR
- Patent Type
- Applications
- Current Assignee / Owner
- SAFRAN SA
- Filing Date
- 2024-12-13
- Publication Date
- 2026-06-19
AI Technical Summary
Composite material gas turbine housings face issues with vibrational stresses and frequency crossover due to thin structural zones outside the retention zone, leading to potential crankcase failure from resonation with blade wake excitation frequencies.
A method involving the deposition of unidirectional fibrous layers and a reinforcing belt with high elongation fibers on a mold to form a structural ferrule, followed by matrix densification, enhancing retention capacity without compromising structural properties.
The method improves debris retention capacity and maintains overall structural integrity by locally reinforcing the part with unidirectional fibers, preventing crankcase failure and ensuring stable operation.
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Abstract
Description
Title of the invention: Method for manufacturing a part of revolution made of composite material with locally optimized properties and the resulting part of revolution technical field
[0001] The present invention relates to the general field of manufacturing parts of revolution exposed to impacts and more particularly, but not exclusively, gas turbine housings for aeronautical engines. Previous technique
[0002] An aircraft gas turbine engine comprises one or more turbine casings surrounding a rotating blade wheel. These casings perform several functions. In particular, they define an air intake or flow channel in the engine and incorporate a retention shield. The retention shield acts as a debris trap, retaining fragments of damaged blades, ejected by centrifugal force, to prevent them from passing through the casing and reaching other parts of the aircraft.
[0003] Previously made of metallic material, housings, such as blower housings, are now made of composite material, that is to say from a fibrous preform densified by an organic matrix, which makes it possible to produce parts with a lower overall mass than the same parts when made of metallic material while having at least equivalent or even greater mechanical resistance.
[0004] The manufacture of a blower housing from an organic matrix composite material is described in particular in US patent 8,322,971. In the housing disclosed in US patent 8,322,971, the retention shield is formed by an excess thickness obtained in the housing's fibrous reinforcement, which has a progressively increasing thickness. The fibrous reinforcement is obtained by winding a 3D woven fibrous texture, which has an excess thickness suitable for forming a retention shield. The housing thus obtained exhibits good mechanical properties at the retention shield, both in terms of puncture resistance (retention) and dynamic behavior.
[0005] However, since the structural zones outside the retention zone are significantly thinner than the retention zone, they may be sensitive to vibrational stresses, which can be problematic for the dynamic behavior of the casing. Indeed, their thinness leads to a decrease in the natural frequencies of the turbine casing and increases the risk of Frequency crossover occurs between one of its natural modes and the excitation frequencies from the blade wake opposite the crankcase within the engine's operating range. The crankcase then resonates when one of its natural frequencies intersects an excitation harmonic produced by the blade wake, which can lead to crankcase failure.
[0006] Consequently, there is a need for a solution that locally enhances the retention capacity of a part of revolution made of composite material while preserving good structural properties throughout the part. Description of the invention
[0007] To this end, the invention proposes a method for manufacturing a part of revolution or a sector of a part of revolution made of composite material for a gas turbine, comprising: - the deposition of a plurality of unidirectional fibrous layers onto a mold in order to obtain a fibrous preform of a structural ferrule or a fibrous preform of a structural ferrule sector extending in width along an axial direction and in thickness along a radial direction between an inner face and an outer face, - the formation of a fibrous preform of a reinforcing belt on at least one surface of the fibrous preform of a structural ferrule or of the fibrous preform of a structural ferrule sector, the textile band being formed with fibers having an elongation at break greater than or equal to 1.6%, said textile band having a width less than the width of the fibrous preform of a structural ferrule along the axial direction, - the co-densification of the fibrous preform of the structural ferrule or of the fibrous preform of the structural ferrule sector and of the fibrous preform of the belt by a matrix so as to obtain a part of revolution or a sector of a part of revolution made of composite material comprising a structural ferrule or a sector of structural ferrule consisting of a fibrous reinforcement corresponding to the fibrous preform of the structural ferrule or the fibrous preform of the structural ferrule sector densified by the matrix and a reinforcing belt made of composite material present on at least one face of the structural ferrule or the sector of structural ferrule, the reinforcing belt made of composite material comprising a fibrous reinforcement corresponding to the densified fibrous preform of the belt, or - the deposition of a plurality of unidirectional fibrous layers onto a mold in order to obtain a fibrous preform of a structural ferrule part or a fibrous preform of a structural ferrule sector extending in width along an axial direction and in thickness along a radial direction between an inner face and an outer face, - the densification of the fibrous preform of the structural ferrule or of the preform of the structural ferrule sector by a matrix so as to obtain a structural ferrule or a structural ferrule sector made of composite material comprising a fibrous reinforcement corresponding to the fibrous preform of the structural ferrule or to the preform of the structural ferrule sector densified by the matrix, - the production of a textile strip with fibers having an elongation at break greater than or equal to 1.6%, - impregnation of the textile strip with a matrix precursor, - the formation of a fibrous preform of a reinforcing belt on at least one surface of the structural ferrule or structural ferrule sector in composite material from the textile strip in order to form a fibrous preform of a reinforcing belt, the fibrous texture having a width less than the width of the structural ferrule along the axial direction, - the densification of the fibrous preform of the reinforcing belt by a matrix so as to obtain a part of revolution or a sector of a part of revolution in composite material comprising the structural ferrule or the sector of structural ferrule having on at least one surface a reinforcing belt in composite material comprising a fibrous reinforcement corresponding to the densified fibrous preform of the belt.
[0008] The method according to the invention makes it possible to locally enhance the retention capacity of the rotating part without altering its overall structural properties. Indeed, since the structural ferrule is manufactured independently of the reinforcing belt, it can be produced taking into account the desired structural properties of the rotating part, and with considerable flexibility because the reinforcement of the structural ferrule is made from unidirectional layers.
[0009] The reinforcement of the strengthening belt is made from a textile strip comprising fibers with high elongation at break. By forming a strengthening belt from a textile strip with high elongation at break on the external surface of the structural ferrule, the structural ferrule's deformation capacity without breaking is locally increased in an area likely to be subjected to impact. The resulting part of revolution exhibits very good debris retention capacity.
[0010] According to a particular feature of the process of the invention, the textile strip consists of one or more unidirectional layers or plies, one or more two-dimensional layers or plies, multiaxial sheets or flat braids.
[0011] According to another particular feature of the process of the invention, the width of the fibrous texture along the axial direction is between 10% and 90% of the width of the fibrous preform of the structural ferrule or of the fibrous preform of structural ferrule sector or structural ferrule made of composite material or structural ferrule sector made of composite material.
[0012] According to another particular feature of the process of the invention, the layers of the plurality of unidirectional fibrous layers deposited on the mold have fibers oriented in different directions from one layer to another. This makes it possible to reinforce the mechanical properties of the part along predefined stress directions, particularly in the fiber orientation directions of the unidirectional layers composing the preform of the structural shell or structural shell sector. The layers of the plurality of unidirectional fibrous layers deposited on the mold may, in particular, have fibers oriented at an angle of ± 45° with respect to the direction of the warp and / or weft yarns or strands of the fibrous texture.
[0013] According to another particular feature of the process of the invention, the fibrous preform of the structural ferrule or structural ferrule sector and the fibrous texture comprise fibers selected from: carbon, glass, aramid or ceramic fibers.
[0014] The invention also relates to a part of revolution or a sector of a part of revolution made of a composite material manufactured according to the manufacturing process of a part of revolution or a sector of a part of revolution made of a composite material of the invention. The part of revolution may, in particular, correspond to a gas turbine blower housing or a low-pressure gas turbine compressor. The sector of the part of revolution may, in particular, correspond to a blower housing sector or a low-pressure gas turbine compressor housing sector.
[0015] The invention further relates to an aeronautical gas turbine engine having a part of revolution or one or more sectors of a part of revolution of the invention (blower casing, low pressure compressor according to the invention, blower casing sector(s), or low pressure compression casing sector(s). Brief description of the drawings
[0016] [Fig-1] [Fig. 1] is a perspective and partial cross-sectional view of an aircraft engine equipped with a fan casing made of composite material according to an embodiment of the invention,
[0017] [Fig.2] The [Fig.2] is a cross-sectional view along plane II-II of the housing of the [Fig.1],
[0018] [Fig.3] Fig.3 schematically shows an example of a stratified structure of a fibrous preform of a structural ferrule,
[0019] [Fig.4] Fig.4 is a perspective view showing the shaping of a fibrous preform of structural ferrule,
[0020] [Fig.5] Fig.5 is a perspective view showing the shaping of a fibrous texture intended to form the fibrous reinforcement of a reinforcement belt for the blower housing of Figures 1 and 2,
[0021] [Fig.6] Fig.6 is a cross-sectional view showing the profile of a fibrous preform of the housing of Figures 1 and 2 as well as a tooling allowing densification with a matrix of the fibrous preform. Description of the implementation methods
[0022] The invention applies generally to any part of revolution or sector of part of revolution made of composite material of gas turbine comprising a portion of excess thickness forming a retention zone or shield.
[0023] A manufacturing process for a part of revolution of the invention is described below, applied, according to a first example, to a blower housing for an aeronautical gas turbine engine.
[0024] Such an engine, as shown very schematically by [Fig.1], comprises, from upstream to downstream in the direction of the gas flow E, a blower 1 disposed at the inlet of the engine, a compressor 2, a combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5.
[0025] The motor is housed inside a casing comprising several parts corresponding to different elements of the motor. Thus, the blower 1 is surrounded by a blower casing 10 having a shape of revolution.
[0026] Figure 2 shows the axial cross-sectional profile of the blower housing 10, which is made of an organic matrix composite material, i.e., a fiber reinforcement of, for example, carbon, glass, aramid, or ceramic, densified by a polymer matrix, for example, epoxy, bismaleimide, or polyimide. The manufacture of such a housing is described in particular in US patent 8,322,971.
[0027] The housing 10 extends laterally along an axial direction DA between its upstream and downstream ends (from left to right in [Fig. 2]), which are here provided with external flanges 14, 15 to allow its mounting and connection with other elements. The housing 10 extends lengthwise along a circumferential direction Dc.
[0028] According to the invention, the housing 10 comprises a structural shell 11 made of composite material having a reinforcing band on its inner and / or outer surface. In the example described here, a reinforcing band 12 made of composite material is present on the outer surface 11b of the structural shell. The reinforcing band 12 delimits a retention zone of the housing 10 capable of retaining debris from damage to the fan blades, and projected radially by the rotation of the fan, to prevent them from passing through the housing and causing damage. other parts of the aircraft. The internal surface 1 of the structural ferrule 11 defines here the air intake duct of the engine.
[0029] As explained below in detail, the fibrous reinforcement of the structural ferrule 11 is formed by a plurality of unidirectional layers superimposed on one another, while the fibrous reinforcement of the reinforcing belt 12 is formed by a fibrous texture made in the form of a strip by three-dimensional weaving.
[0030] A method for manufacturing the blower housing 10 according to an embodiment of the invention is now described. In the method described below, the part is manufactured directly with its final geometry of revolution. However, the invention also applies to the unitary manufacturing of sectors of the part of revolution, the latter being obtained by assembling several of these sectors of revolution, for example by tightening flanges located at the ends of each sector.
[0031] As shown in Figures 3 and 4, a fibrous preform 100 of a structural ferrule is formed by successive deposits of unidirectional layers onto a mold, in this case a mandrel 200. The deposition of the unidirectional layers onto the mandrel is preferably carried out using the known technology of automatic fiber placement, or AFP (Automatic Fiber Placement). The unidirectional layers deposited on the mandrel may be pre-impregnated with a matrix precursor or be "dry," i.e., without pre-impregnation, the fibrous preform of the structural ferrule being impregnated with a matrix precursor subsequently. The precursor may be, in particular, an epoxy resin, such as, for example, a commercially available high-performance epoxy resin, or liquid precursors of carbon or ceramic matrices.
[0032] The mandrel 200 ([Fig.4]) (or sector mold) has an external surface 201 whose profile corresponds to the internal surface of the structural shell to be produced. By being deposited on the mandrel 200, the unidirectional layers conform to its profile. The mandrel 200 also includes two flanges 220 and 230 to form parts of the fibrous preform corresponding to the flanges 14 and 15 of the housing 10.
[0033] The fibrous preform 100 of the structural ferrule (or structural ferrule sector) comprises a plurality of unidirectional layers, i.e., layers each having fibers or wires extending in the same direction. The unidirectional layers are preferably deposited one on top of the other with different orientations so as to have fibers or wires in the fibrous preform oriented in different directions, which makes it possible to strengthen the mechanical properties of the part along predefined stress directions, particularly in the orientation directions of the fibers of the unidirectional layers composing the structural ferrule preform (or structural ferrule sector).
[0034] An example of a fibrous preform 100 composed of a stratification of unidirectional layers is illustrated in [Fig.3]. In this example, it has a stratification of unidirectional layers 101, 102, 103, 104 and 105 oriented at different angles with respect to a longitudinal direction L, namely 0° (101), 90° (102), +45° (103), 90° (104), and -45° (105).
[0035] It should be noted that the fibrous preform of the structural ferrule (or structural ferrule sector) may have different layers in their orientation and / or number than those illustrated in [Fig. 3]. For example, when it is desired to reinforce the shear mechanical properties of the structural ferrule, the fibrous preform may comprise at least one first unidirectional layer oriented at +45° and at least one second unidirectional layer oriented at -45°.
[0036] The method according to the invention also includes the production of a textile strip 90 which is intended to be wound on the external surface 100b of the fibrous preform 100 of the structural ferrule (or structural ferrule sector) ([Fig.5]).
[0037] According to the invention, the textile band 90 is formed with fibers having an elongation at break greater than or equal to 1.6% and greater than the elongation at break of the fibers of the fibrous preform 100. By way of non-limiting examples, the textile band 90 can be formed with para-aramid fibers (such as Twaron®, Kevlar® or Technora® fibers), PBO Zylon® fibers, glass fibers, or high-density polyethylene (PE) or high-molecular-weight PE-UHMW type Dyneema® fibers.
[0038] The textile band can in particular but not exclusively be formed by one or more unidirectional (UD) layers or plies, by one or more two-dimensional (2D) layers or plies with fibers oriented at 0° / 90° or +45° / -45°, by one or more multiaxial plies (“Non Crimp Fabric” in English or NCF) which is a textile fabric which generally has several layers of non-woven unidirectional fibers oriented in different directions linked by a fine knitting yarn, or by flat braids.
[0039] As illustrated in [Fig. 5], the textile strip 90 is wound one or more times around the external surface 100b of the structural ferrule fibrous preform 100 at a predetermined location on the latter along the axial direction DA corresponding to a debris retention zone of the final housing. In the case of manufacturing a sector of a part of revolution, one or more layers of the fibrous texture are draped over the structural ferrule sector fibrous preform.
[0040] The textile strip 90 may be pre-impregnated with a matrix precursor or be "dry", i.e., without being pre-impregnated, the textile strip being impregnated with a matrix precursor subsequently. The precursor may, in particular, be a resin epoxy, such as, for example, a commercially available high-performance epoxy resin, or liquid precursors of carbon or ceramic matrices.
[0041] The textile strip 90 has a width l90 that is less than the width l100 of the fibrous preform 100 of the structural ferrule (or structural ferrule sector) along the axial direction Da ([Fig. 5]). The width l90 of the fibrous texture determines the axial area or extent over which the structural ferrule (or structural ferrule sector) of the housing is to be locally reinforced. Generally, the width l90 of the textile strip 90 is between 10% and 90% of the width hoo of the fibrous preform 100.
[0042] Once wound on a determined number of turns on the external surface 100b of the fibrous preform 100, the textile strip 90 forms a fibrous preform of a reinforcing belt.
[0043] The fibrous preform 100 of the structural ferrule (or structural ferrule sector) may include fibers, for example, of carbon, aramid or ceramic, while the textile band 90 includes fibers having an elongation at break greater than or equal to 1.6% and greater than the elongation at break of the fibers of the fibrous preform 100.
[0044] Figure 6 shows a cross-sectional view of a fibrous preform 300 of a part of revolution, here of the housing 10 to be produced, consisting, from the center outwards, of the unidirectional layers 101 to 105 of the fibrous preform 100 of the structural ferrule and the fibrous texture 90 (wound in a single turn on Figure 6). The number of turns or spirals of the textile strip 90 depends on the desired thickness of the reinforcing belt and the desired local reinforcing properties.
[0045] The fibrous preform 300 is then densified by a matrix.
[0046] The densification of the fibrous preform consists of filling the porosity of the preforms, in all or part of its volume, by the material constituting the matrix.
[0047] In the case of a fibrous preform 300 made up of unidirectional layers and a dry textile belt strip, the matrix can be obtained in a manner known per se following the liquid process.
[0048] The liquid process consists of impregnating the preform with a liquid composition containing an organic precursor of the matrix material. The organic precursor is usually in the form of a polymer, such as a resin, possibly diluted in a solvent. The fibrous preform is placed in a mold that can be hermetically sealed with a cavity having the shape of the final molded part. As illustrated in [Fig. 6], the fibrous preform 300 is placed here between a plurality of sectors 240 forming a counter-mold and the mandrel 200 forming a support, these elements having respectively the outer shape and the inner shape interior of the housing to be made. Then, the liquid matrix precursor, for example a resin, is injected into the entire housing to impregnate all the fibrous part of the preform.
[0049] The transformation of the precursor into an organic matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after removal of any solvent and crosslinking of the polymer, the preform always being held in the mold, which has a shape corresponding to that of the part to be produced. The organic matrix can be obtained, in particular, from epoxy resins, such as, for example, a commercially available high-performance epoxy resin, or from liquid precursors of carbon or ceramic matrices.
[0050] In the case of forming a carbon or ceramic matrix, the heat treatment consists of pyrolyzing the organic precursor to transform the organic matrix into a carbon or ceramic matrix, depending on the precursor used and the pyrolysis conditions. For example, liquid carbon precursors can be resins with a relatively high coke content, such as phenolic resins, while liquid ceramic precursors, particularly SiC, can be polycarbosilane (PCS), polytitanocarbosilane (PTCS), or polysilazane (PSZ) type resins. Several consecutive cycles, from impregnation to heat treatment, can be carried out to achieve the desired degree of densification.
[0051] According to one aspect of the invention, the densification of the fibrous preform can be achieved by the well-known resin transfer molding (RTM) process. According to the RTM process, the fibrous preform is placed in a mold having the shape of the housing to be produced. A thermosetting resin is injected into the internal space defined between the mandrel 200 and the counter-molds 240, which includes the fibrous preform. A pressure gradient is generally established in this internal space between the point where the resin is injected and the resin discharge ports in order to control and optimize the impregnation of the preform by the resin.
[0052] The resin used can be, for example, an epoxy resin. Resins suitable for RTM processes are well known. They preferably have a low viscosity to facilitate their injection into the fibers. The choice of temperature class and / or the chemical nature of the resin is determined according to the thermomechanical stresses to which the part must be subjected. Once the resin has been injected throughout the reinforcement, it is polymerized by heat treatment in accordance with the RTM process.
[0053] In the case of manufacturing a sector of a part of revolution, only the shapes of the mold and the counter-mold are modified to adapt to the geometry of the sector to manufacture. All other characteristics of the densification step described above also apply to the densification of a fibrous preform of a sector of a part of revolution.
[0054] After injection and polymerization, the part is demolded. Finally, the part is trimmed to remove excess resin and the chamfers are machined to obtain the housing 10 illustrated in figures 1 and 2, namely comprising the structural ferrule 11 having on an external surface 11b a reinforcing belt of composite material 12 comprising a fibrous reinforcement corresponding to the densified fibrous belt preform.
[0055] In the case of a fibrous preform 300 made up of unidirectional layers and a fibrous reinforcing belt texture already pre-impregnated with a matrix precursor, the densification of the matrix preform consists of transforming the precursor into an organic matrix by heat treatment in an autoclave or by heating the mold in which the preform is held, the mold having a shape corresponding to that of the part to be produced.
[0056] According to another embodiment of the process of the invention, the part of revolution (or the sector of the part of revolution), here the housing 10, can be manufactured in the following way:
[0057] - formation of a fibrous preform of structural collar (like the fibrous preform 100) (or a fibrous preform of a structural ferrule sector) by depositing a plurality of pre-impregnated or dry unidirectional fibrous layers onto a mandrel as already described above, - densification of the fibrous preform of the structural ferrule (or structural ferrule sector) by a matrix so as to obtain a structural ferrule (or structural ferrule sector) in composite material (like the structural ferrule 11) comprising a fibrous reinforcement corresponding to the fibrous preform of the structural ferrule (or structural ferrule sector) densified by the matrix, - production of a textile band with fibers having an elongation at break greater than or equal to 1.6% (like the textile band 90), - impregnation of the textile band with a matrix precursor, - formation of a fibrous preform of a reinforcing belt on at least one surface of the structural ferrule (or structural ferrule sector) in composite material,the textile band having a width less than the width of the structural ferrule (or structural ferrule sector) along the axial direction, - the densification of the fibrous preform of the belt by a matrix.
[0058] This yields a part of revolution (or sector of a part of revolution) made of composite material which can correspond to the housing 10 of Figures 1 and 2, namely comprising the structural ferrule 11 having on an external surface 11b a reinforcement belt in composite material 12 comprising a fibrous reinforcement corresponding to the densified fibrous preform of the belt.
[0059] The invention is particularly applicable to the manufacture of fan housings or housing sections and / or low-pressure compressor housings for different types of gas turbine engines, such as conventional enclosed engines or new-generation unenclosed engines known as "open rotor" engines. According to another embodiment, a part of revolution or a sector of a part of revolution is manufactured from a composite material as described above, but in which the reinforcing band is present on the inner surface of the structural shell or the structural shell sector.
Claims
1. Demands Method for manufacturing a part of revolution or a sector of a part of revolution made of composite material for a gas turbine, comprising: - the deposition of a plurality of unidirectional fibrous layers (101, 102, 103, 104, 105) on a mold (200) in order to obtain a fibrous preform of a structural ferrule (100) or a fibrous preform of a sector of a structural ferrule extending in width along an axial direction (DA) and in thickness along a radial direction (Dr) between an inner face and an outer face, - the formation of a fibrous preform of a reinforcing belt on at least one surface (100b) of the fibrous preform (100) of the structural ferrule or of the fibrous preform of the structural ferrule sector from a textile strip (90), the textile strip being formed with fibers having an elongation at break greater than or equal to 1.6%, said textile strip having a width (l90) less than the width (lioo) of the fibrous preform (100) of the structural ferrule or of the fibrous preform of the structural ferrule sector along the axial direction, - the co-densification of the structural ferrule fibrous preform or the structural ferrule sector fibrous preform and the belt fibrous preform by a matrix so as to obtain a part of revolution (10) or a sector of a part of revolution made of composite material comprising a structural ferrule (11) or a structural ferrule sector made of a fibrous reinforcement corresponding to the structural ferrule fibrous preform (100) or the structural ferrule sector fibrous preform densified by the matrix and a reinforcing belt (12) made of composite material present on at least one surface (11b) of the structural ferrule or the structural ferrule sector, the reinforcing belt made of composite material comprising a fibrous reinforcement corresponding to the densified belt fibrous preform, or - the deposition of a plurality of unidirectional fibrous layers (101, 102, 103, 104, 105) onto a mold (200) in order to obtain a fibrous preform (100) of a structural ferrule part or a fibrous preform of a structural ferrule sector extending in width along an axial direction (DA) and thickness along a radial direction (DR) between an inner face and an outer face, - the densification of the fibrous preform of the structural ferrule (100) or of the fibrous preform of the structural ferrule sector by a matrix so as to obtain a structural ferrule (11) or a structural ferrule sector in composite material comprising a fibrous reinforcement corresponding to the fibrous preform of the structural ferrule or the fibrous preform of the structural ferrule sector densified by the matrix, - the production of a textile strip (90) with fibers having an elongation at break greater than or equal to 1.6%, - the impregnation of the textile strip with a matrix precursor, - the formation of a prepreg reinforcing belt fibrous preform on at least one surface (11b) of the structural ferrule or the structural ferrule sector in composite material from the textile strip (90),the textile band having a width (l90) less than the width of the structural ferrule along the axial direction, - the densification of the fibrous preform of the belt by a matrix so as to obtain a part of revolution (10) or a sector of a part of revolution in composite material comprising the structural ferrule (11) or the sector of the structural ferrule having on at least one surface a reinforcing belt (12) in composite material comprising a fibrous reinforcement corresponding to the densified fibrous preform of the belt.
2. A method according to claim 1, wherein the textile strip (90) is made up of one or more unidirectional layers or plies, one or more two-dimensional layers or plies, multiaxial plies or flat braids.
3. A method according to claim 1 or 2, wherein the width (190) of the fibrous texture (90) along the axial direction is between 10% and 90% of the width (110) of the fibrous preform (100) of the structural ferrule or structural ferrule sector or of the structural ferrule (11) or of the structural ferrule sector in composite material.
4. A method according to any one of claims 1 to 3, wherein the layers (101, 102, 103, 104, 105) of the plurality of unidirectional fibrous layers deposited on the mold (200) have fibers oriented in different directions from one layer to another.
5. A method according to claim 4, wherein the layers (101, 102, 103, 104, 105) of the plurality of unidirectional fibrous layers deposited on the mold (200) have fibers oriented at an angle of ± 45° with respect to the direction of the warp and / or weft yarns or strands of the fibrous texture.
6. A method according to any one of claims 1 to 5, wherein the fibrous preform (100) of the structural ferrule or the fibrous preform of the structural ferrule sector and the fibrous texture (90) comprise fibers selected from: carbon, glass, aramid, or ceramic fibers
7. A method according to any one of claims 1 to 6 wherein the part of revolution corresponds to a blower housing (10) or the sector of the part of revolution corresponds to a sector of a gas turbine blower housing.
8. A method according to any one of claims 1 to 6 wherein the part of revolution corresponds to a low-pressure compressor housing or the sector of the part of revolution corresponds to a sector of a low-pressure compressor housing of a gas turbine.
9. Part of revolution or sector of part of revolution made of composite material manufactured according to the process according to any one of claims 1 to 6.
10. Part of revolution or sector of part of revolution according to claim 9, said part of revolution or said sector of part of revolution corresponding to a blower housing (10) or a blower housing sector of a gas turbine.
11. Part of revolution or sector of part of revolution according to claim 9, said part of revolution corresponding to a low pressure compressor housing or a sector of low pressure compressor housing of gas turbine.
12. Aeronautical gas turbine engine comprising at least one part of revolution or one or more sectors of part of revolution made of composite material according to any one of claims 9 to 11.