Method for manufacturing a locally reinforced rotationally symmetrical part from composite material and resulting rotationally symmetrical part

Abstract

The invention relates to a method for manufacturing a rotationally symmetrical part from composite material, the method comprising: - depositing a plurality of unidirectional fibrous layers on a mandrel (200) in order to obtain a fibrous preform (100) of a structural shroud; - producing, by three-dimensional weaving, a fibrous texture (90) in the form of a strip; - winding the fibrous texture (90) one or more turns around the outer surface (100b) of the fibrous preform (100) in order to obtain a fibrous preform of a reinforcing belt, wherein the fibrous texture (90) has a width (l90) less than the width (l100) of the fibrous preform (100) of the structural shroud, in the axial direction; - densifying the fibrous preform of the structural shroud and the fibrous preform of the belt with a matrix so as to obtain a rotationally symmetrical part made from composite material comprising a structural shroud consisting of a fibrous reinforcement corresponding to the fibrous preform (100) of the structural shroud densified by the matrix and a reinforcing belt made from composite material present on an outer surface of the structural shroud.

Description

[0001] Description

[0002] Title of the invention: Method for manufacturing a part of revolution made of locally reinforced composite material and the resulting part of revolution

[0003] Technical Field

[0004] 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 aircraft engines.

[0005] Previous technique

[0006] A gas turbine aircraft 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 path within the engine and incorporate a debris trap. The debris trap retains fragments of damaged blades, propelled by centrifugal force, to prevent them from passing through the casing and reaching other parts of the aircraft.

[0007] 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 if not superior mechanical resistance.

[0008] The fabrication of a blower housing from an organic matrix composite material is described in US patent 8,322,971. In the housing disclosed in US patent 8,322,971, the retention shield is formed by an increased thickness obtained within 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 increased thickness suitable for forming a retention shield. The resulting housing exhibits good mechanical properties at the retention shield, both in terms of puncture resistance (retention) and dynamic behavior.

[0009] However, the solution of forming an extra thickness in the fibrous reinforcement of the casing is not always suitable because, even if it locally reinforces the impact resistance of the casing, it also modifies its structural behavior, such as the sensitivity of the casing to vibrational stresses.

[0010] There is, therefore, 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 over the entire part.

[0011] Description of the invention

[0012] 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:

[0013] - the deposition of a plurality of unidirectional fibrous layers onto a mold in order to obtain a fibrous preform of a structural shell or a fibrous preform of a sector of a structural shell extending in width along an axial direction and in thickness along a radial direction between an inner face and an outer face,

[0014] - the creation, by three-dimensional weaving between a plurality of warp yarns or strands and a plurality of weft yarns or strands, of at least one fibrous texture in the form of a strip,

[0015] - the formation of a fibrous preform of a reinforcing belt on at least one face of the fibrous preform of the structural ferrule or of the fibrous preform of the structural ferrule sector from the fibrous texture, said at least one fibrous texture having a width less than the width of the fibrous preform of the structural ferrule or of the fibrous preform of the structural ferrule sector along the axial direction,

[0016] - 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

[0017] - 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,

[0018] - the densification of the fibrous preform of the structural ferrule or of the fibrous 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 the fibrous preform of the structural ferrule sector densified by the matrix,

[0019] - the creation, by three-dimensional weaving between a plurality of warp yarns or strands and a plurality of weft yarns or strands, of at least one fibrous texture in the form of a strip,

[0020] - the impregnation of at least one fibrous texture by a matrix precursor,

[0021] - the formation of a fibrous preform of a reinforcing belt on at least one face of the structural shell or structural shell sector made of composite material from a fibrous texture, said at least one fibrous texture having a width less than the width of the structural shell or structural shell sector along the axial direction,

[0022] - the densification of the fibrous belt preform 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 face a reinforcement belt in composite material comprising a fibrous reinforcement corresponding to the densified fibrous belt preform.

[0023] The process according to the invention makes it possible to locally enhance the retention capacity of the part of revolution without altering its overall structural properties. Indeed, since the structural ferrule, or a sector thereof, is manufactured independently of the reinforcing belt, the ferrule or its sector can be produced according to the desired structural properties of the part, with considerable flexibility because the reinforcement of the structural ferrule or the ferrule sector is made from unidirectional layers. The reinforcement of the reinforcing belt is produced from a fibrous texture obtained by three-dimensional weaving.

[0024] Furthermore, the impact failure mode of composite structures such as the structural shell or a section thereof consumes energy primarily under tension, rather than compression or shear. By forming a reinforcing belt from a fibrous texture obtained by three-dimensional weaving on at least one face of the structural shell or the structural shell section, the stiffness of the shell or section is locally increased in an area likely to be subjected to impact. The resulting part of revolution exhibits excellent debris retention capacity.

[0025] According to a particular feature of the process of the invention, the width of said at least one fibrous texture along the axial direction is between 10% and 80% of the width of the fibrous preform of the structural ferrule or of the structural ferrule in composite material, or of the fibrous preform of the structural ferrule sector or of the structural ferrule sector in composite material.

[0026] According to another particular feature 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° to the direction of the warp and / or weft yarns or strands of the fibrous texture.

[0027] According to another particular feature of the process of the invention, the structural ferrule fibrous preform or the structural ferrule sector fibrous preform and the fibrous texture comprise fibers selected from: carbon, glass, aramid fibers.

[0028] 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.

[0029] 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).

[0030] Brief description of the drawings

[0031] [Fig. 1] Figure 1 is a perspective and partial cross-sectional view of an aircraft engine equipped with a fan casing made of composite material according to one embodiment of the invention,

[0032] [Fig. 2] Figure 2 is a cross-sectional view along plane ll-ll of the housing of Figure 1,

[0033] [Fig. 3] Figure 3 schematically shows an example of the layered structure of a fibrous preform of a structural ferrule,

[0034] [Fig. 4] Figure 4 is a perspective view showing the shaping of a fibrous preform of a structural ferrule,

[0035] [Fig. 5] Figure 5 is a schematic perspective view of a loom showing the weaving of a fibrous texture used for forming the fibrous reinforcement of a casing reinforcement belt in Figures 1 and 2. [Fig. 6] Figure 6 shows an interlock weave.

[0036] [Fig. 7] Figure 7 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,

[0037] [Fig. 8] Figure 8 is a cross-sectional view showing the profile of a fibrous preform of the housing in Figures 1 and 2, as well as a tooling for densifying the fibrous preform with a matrix.

[0038] Description of the implementation methods

[0039] The invention applies generally to any part of revolution or sector of a part of revolution made of composite material of a gas turbine comprising a portion of excess thickness forming a retention zone or shield.

[0040] 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.

[0041] Such an engine, as shown very schematically by figure 1, comprises, from upstream to downstream in the direction of the gas flow E, a blower 1 arranged at the inlet of the engine, a compressor 2, a combustion chamber 3, a high-pressure turbine 4 and a low-pressure turbine 5.

[0042] The motor is housed inside a casing comprising several parts corresponding to different motor components. Thus, the blower 1 is surrounded by a blower casing 10 having a shape of revolution.

[0043] Figure 2 shows the axial cross-section of the blower housing 10, which is made of an organic matrix composite material, i.e., a fiber reinforcement (for example, carbon, glass, or aramid) densified by a polymer matrix (e.g., epoxy, bismaleimide, or polyimide). The manufacture of such a housing is described in US patent 8,322,971.

[0044] The housing 10 extends laterally along an axial direction DA between its upstream and downstream ends (from left to right in Figure 2), which are here fitted with external flanges 14, 15 to allow its mounting and connection with other elements. The housing 10 extends lengthwise along a circumferential direction De.

[0045] According to the invention, the casing 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 defines a retention zone of the casing 10 capable of retaining debris from damage to the fan blades, projected radially by the fan's rotation, to prevent it from passing through the casing and damaging other parts of the aircraft. The inner surface 11a of the structural shell 11 defines the engine's air intake duct.

[0046] 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.

[0047] A manufacturing process for the blower housing 10 is now described according to an embodiment of the invention. In the process 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.

[0048] As shown in Figures 3 and 4, a fibrous preform 100 of a structural shell is formed by successive deposition 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 well-known Automatic Fiber Placement (AFP) technology. 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 shell 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.In the case of manufacturing a sector of a part of revolution, a preform of the structural ferrule sector is formed by successive deposits of unidirectional layers on a mold corresponding to the shape of the structural ferrule sector to be manufactured.

[0049] The mandrel 200 (Figure 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 portions of the fibrous preform corresponding to the flanges 14 and 15 of the housing 10.

[0050] The structural ferrule (or structural ferrule sector) fibrous preform 100 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 that the fibers or wires in the fibrous preform are oriented in different directions. This allows the mechanical properties of the part to be reinforced along predefined stress directions, particularly in the fiber orientation directions of the unidirectional layers composing the structural ferrule (or structural ferrule sector) preform.

[0051] An example of a fibrous preform 100 composed of a stratification of unidirectional layers is illustrated in Figure 3. In this example, it presents a stratification of unidirectional layers 101, 102, 103, 104 and 105 oriented at different angles with respect to a longitudinal direction L, namely 0° (1101), 90° (102), +45° (103), 90° (104), and -45° (105).

[0052] 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 Figure 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°. As illustrated in Figure 5, the process according to the invention also includes producing a fibrous texture 90 by weaving using a Jacquard-type loom 60 on which a bundle of warp yarns or strands 70 is arranged in a plurality of layers, the warp yarns being linked by weft yarns or strands 80. The fibrous texture is produced by three-dimensional weaving.

[0053] The term "three-dimensional weave" or "3D weave" refers to a weaving method in which at least some of the weft threads interlock with warp threads across multiple layers of warp threads, or vice versa. An example of three-dimensional weaving is interlock. Interlock weave is a weave structure in which each layer of warp threads interlocks with multiple layers of weft threads, with all the threads in the same warp column moving in the same direction within the plane of the weave.

[0054] Figure 6 shows an example of an interlock weave for creating the fibrous texture 90. In Figure 6, the weft yarns 80 are shown in cross-section. A three-dimensional weave with an interlock weave is a weave in which each warp yarn 70 connects several layers of weft yarns 80, with the warp yarns 70 following identical paths. Other three-dimensional weaving methods are possible, such as multilayer weaves with multi-satin or multi-plain weaves. Weaves of this type are described in document W02006136755.

[0055] The creation of the 90 fibrous texture by 3D weaving allows a bond to be obtained between the layers, thus providing good mechanical strength of the fibrous texture and the resulting composite material reinforcement belt, in a single textile operation.

[0056] As illustrated in Figures 5 and 7, the fibrous texture 90 has a band shape which extends lengthwise in an X direction (Figure 5) corresponding to the direction of the warp yarns or strands 70 and widthwise or transversely in a Y direction (Figure 5) corresponding to the direction of the weft yarns or strands 80.

[0057] As illustrated in Figure 7, the fibrous texture 90 is wound in one or more turns on the external surface 100b of the structural ferrule fibrous preform 100 at a specific location on the latter along the axial direction DA, corresponding to a debris retention zone of the final housing. Therefore, in the fibrous reinforcement of the final reinforcing belt, the warp yarns or strands extend along the circumferential direction De (Figure 2), while the weft yarns or strands extend along the axial direction DA (Figure 2). In the case of manufacturing a sector of revolution, one or more layers of the fibrous texture are draped over the structural ferrule sector fibrous preform.

[0058] The fibrous texture 90 can be pre-impregnated with a matrix precursor or be "dry," meaning without pre-impregnation, with the fibrous texture being impregnated with a matrix precursor subsequently. The precursor can 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.

[0059] The fibrous texture 90 has a width Igo that is less than the width Iwo of the structural shell (or structural shell sector) fibrous preform 100 along the axial direction DA (Figure 7). The width Igo of the fibrous texture determines the axial area or extent over which the structural shell (or structural shell sector) of the housing is to be locally reinforced. Generally, the width Igo of the fibrous texture 90 is between 10% and 80% of the width Iwo of the fibrous preform 100.

[0060] Once wound on a predetermined number of turns on the external surface 100b of the fibrous preform 100, the fibrous texture 90 forms a fibrous reinforcing belt preform.

[0061] The structural ferrule (or structural ferrule sector) fibrous preform 100 and the fibrous texture 90 can include fibers of, for example, carbon, glass, or aramid. The structural ferrule (or structural ferrule sector) fibrous preform 100 and the fibrous texture 90 can be made with fibers of the same or different types.

[0062] Figure 8 shows a cross-sectional view of a fibrous preform 300 of a part of revolution, here 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 in Figure 8). The number of turns or spirals of the fibrous texture 90 depends on the desired thickness of the reinforcing band and the desired local reinforcement properties.

[0063] The next step is to densify the fibrous preform 300 using a matrix.

[0064] The densification of the fibrous preform consists of filling the porosity of the preform, in all or part of its volume, with the material constituting the matrix.

[0065] In the case of a 300 fibrous preform consisting of unidirectional layers and a dry belt fibrous texture, the matrix can be obtained in a manner known per se by the liquid process.

[0066] The liquid process involves 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 sealed tightly, with a cavity shaped like the final molded part. As illustrated in Figure 8, the fibrous preform 300 is positioned between a plurality of sectors 240 forming a counter-mold and the mandrel 200 forming a support, these elements having, respectively, the external and internal shapes of the housing to be produced. The liquid matrix precursor, for example, a resin, is then injected into the entire cavity to impregnate the entire fibrous portion of the preform.

[0067] The transformation of the precursor into an organic matrix, namely its polymerization, is carried out by heat treatment, generally by heating the mold, after the removal of any solvent and crosslinking of the polymer. The preform remains in the mold, which has a shape corresponding to that of the part to be produced. The organic matrix can be obtained from epoxy resins, such as, for example, a commercially available high-performance epoxy resin, or from liquid precursors of carbon or ceramic matrices.

[0068] In the case of carbon or ceramic matrix formation, heat treatment involves 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 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.

[0069] 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. In accordance with 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.

[0070] 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 will be subjected. Once the resin has been injected throughout the reinforcement, it is cured by heat treatment according to the RTM process.

[0071] In the case of manufacturing a sector of a part of revolution, only the shapes of the mold and counter-mold are modified to adapt to the geometry of the sector to be manufactured. 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.

[0072] 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 preform of the belt.

[0073] In the case of a 300 fibrous preform consisting of unidirectional layers and a fibrous reinforcement 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 by heating the mold in which the preform is held, the mold having a shape corresponding to that of the part to be produced.

[0074] 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:

[0075] - formation of a fibrous preform for a structural ferrule (such as fibrous preform 100) (or a fibrous preform for a structural ferrule sector) by depositing a plurality of pre-impregnated or dry unidirectional fibrous layers onto a mandrel (or sector mold) as already described above,

[0076] - 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,

[0077] - creation by three-dimensional weaving of a fibrous texture in the form of a strip (like fibrous texture 90),

[0078] - impregnation of the fibrous texture by a matrix precursor,

[0079] - formation of a fibrous preform of a reinforcing belt on at least one surface of the structural shell made of composite material from the fibrous texture (or draping of one or more layers of 3D fibrous texture on an external surface of the structural shell sector made of composite material), the fibrous texture having a width less than the width of the structural shell (or of the structural shell sector) along the axial direction,

[0080] - densification of the fibrous preform of the belt by a matrix.

[0081] This gives us a part of revolution (or sector of part of revolution) in 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 11 b a reinforcement belt in composite material 12 comprising a fibrous reinforcement corresponding to the densified fibrous preform of the belt.

[0082] The invention is particularly applicable to the manufacture of fan housings or housing sections and / or low-pressure compressor housings for various 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 composite material as described above, but in which the reinforcing band is present on the inner surface of the structural shell or structural shell sector.

[0083] According to another embodiment, the reinforcing belt can be made from one or more layers of titanium, in the form of a thin film with a thickness ranging from 0.1 mm to 3.0 mm. The titanium layer(s) can be:

[0084] - bonded to the structural ferrule or the structural ferrule sector made of composite material manufactured as described above,

[0085] - deposited with adhesive films between raw, pre-impregnated fibrous layers, the whole being cooked, or

[0086] - nested in a draping sequence alternating a layer of titanium with a fibrous layer such as a unidirectional fold for example.

[0087] In another embodiment, the reinforcing belt can be made from a fibrous structure comprising high-tensile-at-break fibers such as para-aramid or PBO (Zylon®) fibers. The fibrous structure can be a woven fabric or one or more multiaxial plies (Non-Crimp Fabric or NCF). The fibrous structure can be:

[0088] - injected in a different shape, then attached and glued onto the structural ferrule or structural ferrule sector made of composite material, - positioned on the unpolymerized fibrous preform of the structural ferrule or structural ferrule sector and injected into a heating cycle used to polymerize the preform of the structural ferrule or structural ferrule sector,

[0089] - conditioned as a prepreg with a resin compatible with that of the structural ferrule matrix or structural ferrule sector, then cured,

[0090] - nested in a draping sequence alternating a layer of high-elongation-at-break fibrous structure with a fibrous layer such as a unidirectional fold for example.

Claims

Demands [Claim 1] 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 (101, 102, 103, 104, 105) on a mold (200) in order to obtain a fibrous preform of a structural shell (100) or a fibrous preform of a sector of a structural shell 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 creation by three-dimensional weaving between a plurality of warp yarns or strands and a plurality of weft yarns or strands of at least one fibrous texture (90) in the form of a strip, - the formation of a fibrous preform of a reinforcing belt on at least one face (100b) of the fibrous preform (100) of the structural ferrule or of the fibrous preform of the structural ferrule sector from the fibrous texture, said at least one fibrous texture (90) having a width (ho) less than the width (hoo) 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 reinforcement belt (12) made of composite material present on at least one surface (11b) of the structural ferrule or structural ferrule sector, the reinforcement belt made of material composite 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) on a mold (200) in order to obtain a fibrous preform of a structural ferrule part (100) or a fibrous preform of a structural ferrule sector 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 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 creation by three-dimensional weaving between a plurality of warp yarns or strands and a plurality of weft yarns or strands of at least one fibrous texture (90) in the form of a strip, - the impregnation of at least one fibrous texture by a matrix precursor, - the formation of a fibrous preform of a reinforcing belt on at least one face (11b) of the structural ferrule or structural ferrule sector in composite material from the fibrous texture (90), said at least one fibrous texture having a width (ho) less than the width of the structural ferrule or structural ferrule sector along the axial direction, - the densification of the fibrous belt preform by a matrix so as to obtain a part of revolution (10) or a sector of part of revolution in composite material comprising the structural ferrule (11) or the sector of structural ferrule comprising on at least one face a reinforcing belt (12) in composite material comprising a fibrous reinforcement corresponding to the densified fibrous belt preform. [Claim 2] A method according to claim 1, wherein the width (ho) of said at least one fibrous texture (90) along the axial direction is between 10% and 80% of the width (hoo) of the fibrous preform (100) of the structural ferrule or of the structural ferrule (11) in composite material, or of the fibrous preform of the structural ferrule sector or of the structural ferrule sector in composite material. [Claim 3] A method according to claim 1 or 2, 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. [Claim 4] A method according to claim 3, 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. [Claim 5] A method according to any one of claims 1 to 4, wherein the fibrous preform (100) of structural ferrule or the fibrous preform of structural ferrule sector and the fibrous texture (90) comprise fibers selected from: carbon, glass, aramid fibers. [Claim 6] A method according to any one of claims 1 to 5 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. [Claim 7] A method according to any one of claims 1 to 5 wherein the part of revolution corresponds to a housing or the sector of the part of revolution corresponds to a sector of the housing of a low-pressure gas turbine compressor. [Claim 8] 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 5. [Claim 9] A part of revolution or a sector of a part of revolution according to claim 8, said part of revolution or sector of a part of revolution corresponding to a housing or a sector of a housing of a gas turbine blower (10). [Claim 10] A part of revolution or a sector of a part of revolution according to claim 8, said part of revolution or sector of a part of revolution corresponding to a housing or a sector of a housing of a low-pressure gas turbine compressor. [Claim 11] 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 8 to 10.

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