METHOD FOR MANUFACTURED A PART FROM COMPOSITE MATERIAL AND PART OBTAINED BY SUCH A METHOD

Abstract

The invention relates to a method for manufacturing a part (40) made of fiber-reinforced composite material densified by a matrix for a turbomachine, particularly for aircraft, the method being characterized in that the matrix is ​​of the thermoplastic type and in that it comprises the following steps: - supplying several plies (50) made of a first thermoplastic composite material; - heating the plies (50) so as to form a preform (52); - placing the preform (52) in a mold, the preform having an initial shape; - stamping the preform (52) so as to modify the initial shape of the preform in order to obtain a substantially final shape of the part; - overmolding the preform (52) by injecting a second thermoplastic composite material to form an overmolded portion (54) onto the preform so as to form the part. Figure for the abstract: Figure 6

Description

Title of the invention: METHOD FOR MANUFACTURED A PART FROM COMPOSITE MATERIAL AND A PIECE OBTAINED BY SUCH A PROCESS technical field

[0001] The present invention relates to the aeronautical field. It relates in particular to a method for manufacturing a part made of composite material with fiber reinforcement densified by a matrix.

[0002] The invention also relates to a turbomachine equipped with at least one such part. Previous technique

[0003] A composite material is an assembly made up of several components whose combination gives the whole particular properties. Composite materials are commonly used in the aeronautical field for their lightness, making it possible to build aircraft with reduced weight and which consequently have lower fuel consumption.

[0004] A composite material part is made from a densified fibrous reinforcement in a matrix. The matrix forms the basis of the composite material and is generally in the form of a resin, and the reinforcement represents the structure of the new material, which is dispersed in the composite material in the form of particles or fibers.

[0005] Among aircraft turbomachinery, there are unducted single-fan turbomachinery. This type of turbomachine offers high propulsive efficiency compared to ducted single-fan turbomachinery.

[0006] This type of turbomachine typically extends around and along a longitudinal axis and comprises, from upstream to downstream in the direction of the gas flow along this longitudinal axis, an unshod blower, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine.

[0007] In contrast to enclosed fan turbomachines, the unenclosed fan turbomachine does not include a fan casing surrounding the fan.

[0008] As is known, an aircraft turbomachine includes various cowlings. For example, a turbomachine includes at least one cowling that is centered on the longitudinal axis of the turbomachine and mounted downstream of a fan or propeller. This cowling is also mounted radially around an annular ferrule. Such a cowling is generally made from a fiber-reinforced composite material densified in a thermosetting matrix obtained by thermocompression.

[0009] However, the use of such a thermosetting matrix or resin requires a significant curing time to polymerize it. The curing time under pressure is generally around 20 minutes.

[0010] The present invention proposes a solution to at least some of the aforementioned drawbacks. Summary of the invention

[0011] The objective of the present invention is to provide a simple and economical solution for manufacturing hoods for fixed or rotating turbomachines out of composite material.

[0012] For this purpose, the invention relates to a method of manufacturing a part in composite material with fiber reinforcement densified by a matrix for a turbomachine, in particular for aircraft. According to the invention, the matrix is ​​of the thermoplastic type and the process comprises the following steps: - supply of several plies made from a first thermoplastic composite material; - heating the folds to form a preform; - placement of the preform in a mold, the preform having an initial shape; - stamping of the preform in such a way as to modify the initial shape of the preform in order to obtain a substantially final shape of the part; - overmolding of the preform by injection of a second thermoplastic composite material to form an overmolded portion on the preform in order to form the part.

[0013] The invention thus proposes a method for manufacturing hoods for fixed or rotating turbomachines in thermoplastic composite material allowing a mass saving.

[0014] The process according to the invention also allows for automation of the process as well as a shorter cycle time than for thermosetting composite materials, in particular less than 5 min per part.

[0015] Such a process has the advantage of reducing manufacturing costs since the hourly rate of the press and the technician is spread over a larger number of parts compared to a thermosetting matrix composite material.

[0016] The method according to the invention may comprise one or more of the following features, taken individually or in combination with each other in all technically possible combinations: - the ply supply stage includes: a pre-consolidation stage of the ply made in the first thermoplastic composite material, and a ply trimming stage according to the dimensions of the part to be manufactured; - the step of heating the plies to form a preform is carried out at a first temperature, the first temperature being between 320°C and 400°C; - the second thermoplastic composite material comprises short fibers; - the stamping and overmolding stages are simultaneous; - the stamping and overmolding steps are consecutive, the process including a preheating step of the second material before its injection during the overmolding step; - the process includes a punching step to form holes through the preform and the overmolded portion; - the fibrous reinforcement includes fibers selected from the group including Kevlar fibers, glass fibers or carbon fibers; - the preform fibers are pre-impregnated; - the first thermoplastic composite material is a polyether ketone (PEKK), a polyetheretherketone (PEEK), a polyaryletherketone (PAEK), a polyphenylene sulfone (PPS), a polyether-imide (PEI), a polyphenylene sulfone (PPSU), a polyether sulfone (PESU), a polysulfone (PSU) or a polyamide (PA), preferably of the low melt polyaryletherketone (LM PAEK) type; - the second thermoplastic composite material is a polyether ketone (PEKK), a polyarylether ketone (PAEK), a polyether-imide (PEI), a polyether sulfone (PESU), a polyphenylene sulfone (PPSU), a polyphenylene sulfone (PPS), a polysulfone (PSU) or a polyamide (PA), preferably of the PEEK CF30 type; - the part to be manufactured is an engine cover for a turbomachine, in particular an aircraft turbomachine.

[0017] The invention also relates to a turbomachine, in particular for aircraft, comprising at least one part manufactured according to the process of the invention and as described above, and in particular an engine cowling.

[0018] Advantageously, the engine hood is a fixed hood, in particular a hood for stator blades (OGV) or a rotating hood, in particular a propeller or blower hood.

[0019] A turbomachine equipped with at least one such hood according to the invention exhibits improved performance compared to previous turbomachines. Brief description of the drawings

[0020] The present invention will be better understood and other details, features and advantages of the present invention will become more apparent upon reading the following non-limiting example descriptions, with reference to the accompanying drawings in which: - Fig. 1 illustrates a schematic view, an axial section of an example of a turbomachine to which the invention applies; - [Fig.2] schematically represents a three-dimensional view of an example of a turbomachine to which the invention applies; - Fig. 3 schematically illustrates the hoods of the turbomachine in Fig. 2 - [Fig.4] schematically represents in axial section an example of assembly between two parts of a turbomachine, one of the parts being a hood made of a composite material according to the invention; - [Fig.5] is a flowchart of a manufacturing process for a part made of fiber-reinforced composite material densified by a matrix according to the invention; - Figure 6 schematically illustrates the steps of the manufacturing process according to the invention; and - Fig. 7 schematically represents an example of a part obtained by a manufacturing process according to the invention.

[0021] Elements having the same functions in the different implementations have the same references in the figures.

[0022] In the figures, the scales and proportions are not strictly respected for the purposes of illustration and clarity.

[0023] Furthermore, in the description and the claims, the terminology axial, radial and circumferential will be adopted without limitation with reference to the trihedron A, R, T indicated in the figures, the axial axis A being parallel to the longitudinal axis of the turbomachine according to the invention.

[0024] Thus, the terms "axial" and "axially" are defined with respect to the axial axis A, which is parallel to the longitudinal axis of the turbomachine. The terms "radial" and "radially" are defined with respect to the axis R, which is perpendicular to the longitudinal axis of the turbomachine. Description of the implementation methods

[0025] Fig. 1 illustrates a schematic axial cross-section of an example of a turbomachine to which the invention applies and Fig. 2 is a three-dimensional view of the turbomachine.

[0026] The invention relates to a turbomachine 1 comprising a single unfaired propeller 2 and an unfaired stator 3. The turbomachine is intended to to be mounted on an aircraft. Such a turbomachine is a turboprop as shown in [Fig. 1]. This turbomachine is known by the English term "Unducted Single Fan" as explained previously.

[0027] The invention also applies to other types of turbomachinery. In particular, the propeller can be shrouded according to another embodiment.

[0028] In the present invention, and more generally, the terms "upstream," "downstream," "axial," and "axially" are defined with respect to the gas flow in the turbomachine and here along the longitudinal axis X (and even from left to right in [Fig. 1]). Similarly, the terms "radial," "internal," and "external" are defined with respect to a radial axis R perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X.

[0029] In [Fig. 1], the turbomachine 1 comprises a gas generator 4 which typically includes, from upstream to downstream, a low-pressure compressor 5, a high-pressure compressor 6, a combustion chamber 7, a high-pressure turbine 8, and a low-pressure turbine 9. The low-pressure compressor 5 and the low-pressure turbine 9 are mechanically connected by a low-pressure shaft 10 to form a low-pressure housing. The high-pressure compressor 6 and the high-pressure turbine 8 are mechanically connected by a high-pressure shaft 11 to form a high-pressure housing. The low-pressure shaft 10 extends at least partially inside the high-pressure shaft 11 and is coaxial with the longitudinal axis X.

[0030] The unshod propeller 2 is formed of a ring of movable blades 2a extending from a rotating housing 12 that is centered and rotatable about the longitudinal axis X. The rotating housing 12 is movable relative to an inner housing 13 extending downstream of the rotating housing 12. In the example shown in [Fig. 1], the propeller 2 is mounted upstream of the gas generator 4 (tractor or "pull" configuration). Alternatively, the propeller 2 is mounted downstream of the gas generator 4 (pusher or "tow" configuration). The blades 2a of the propeller 2 can have variable pitch by means of a pitch-changing system 14.

[0031] An airflow F passing through the turbomachine 1 splits into a primary airflow Fl and a secondary airflow F2 at a separation nozzle 15. The latter is carried by an inlet housing 16 centered on the longitudinal axis. The rotating housing 12 is also mounted to move relative to the inlet housing 16. The latter is extended downstream by an external housing or inter-flow housing 17. In particular, the inlet housing 16 comprises a radially internal ferrule and a radially external ferrule which are centered on the X axis and which partially form, respectively, the radially internal and external walls of the primary flow 20 in which the primary airflow FL circulates. A plurality of structural arms 21 extend radially between the radially internal ferrule 18 and the radially external ferrule 19.

[0032] The inlet casing is also connected to a pylon 30 linking the turbomachine to the aircraft, and which ensures the transfer of axial thrust force.

[0033] The power shaft or the low-pressure shaft 10 (respectively of the free power turbine and the low-pressure turbine) drives the propeller 2, which compresses the airflow outside the outer casing 17 and provides most of the thrust. Optionally, a reduction gear 22 is interposed between the propeller 2 and the power shaft, as shown in [Fig. 1]. The reduction gear 22 may be of the planetary or epicyclic type.

[0034] With reference to Figures 1 and 2, the stator 3 is arranged downstream of the propeller 2. The stator 3 comprises a plurality of stator vanes 23 (or fixed vanes) known by the English acronym OGV for "Outlet Guide Vane". The stator vanes 23 are evenly distributed around the longitudinal axis X and extend radially into the secondary airflow F2. The stator vanes 23 of the stator 3 are arranged downstream of the blades 2a of the propeller 2 so as to straighten the airflow generated by them. The stator vanes 23 advantageously have variable pitch so as to optimize the performance of the turbomachine.

[0035] The various elements described above are assembled and / or manufactured in a modular manner so as to make them easier to manufacture and to facilitate their maintenance.

[0036] Each turbomachine housing has a hood which is advantageously annular and centered on the longitudinal axis X of the turbomachine 1, which is here the axis of rotation of the turbomachine rotors.

[0037] Figure 3 schematically illustrates the turbomachine hoods of the [Fig.2] and more specifically, the hood 12C of the rotating housing 12 and the hood 16C of the inlet housing 16.

[0038] Figure 4 schematically represents, in axial section, an example assembly between two parts of a turbomachine, one of the parts being a hood, of general reference 40, made of a composite material according to the invention.

[0039] As shown in [Fig. 4], the hood 40 is mounted radially around a ferrule 42. The hood 40 is fixed to the ferrule 42, which is advantageously annular and centered on the longitudinal axis X. The fixing is advantageously achieved by means of fixing members 44.

[0040] The fasteners 44 can be threaded elements such as screws and bolts or rivets.

[0041] The hood 40 can also be advantageously equipped with a sealing gasket.

[0042] These hoods are made of a fiber-reinforced composite material densified in a thermoplastic matrix by a manufacturing process according to the invention which will be detailed.

[0043] In the following description, the manufacturing process applies to the manufacture of such hoods.

[0044] However, the manufacturing process according to the invention is intended to manufacture any part made of composite material, in particular intended to be mounted in an aircraft turbomachine. The aircraft comprises, for example, a fuselage and two wings extending on either side of the fuselage with respect to the fuselage axis. Each wing can carry at least one turbomachine.

[0045] We will now describe in detail the S100 process for manufacturing such a part from composite material. This process is shown in [Fig. 5], which is a flowchart of the manufacturing process for a part made of fiber-reinforced composite material densified by a matrix according to the invention. [Fig. 6] schematically illustrates steps of the manufacturing process according to the invention, and [Fig. 7] schematically represents an example of a part obtained by a manufacturing process according to the invention.

[0046] The part manufactured by the process according to the invention is made of a fiber-reinforced composite material densified by a thermoplastic-type matrix, thereby reducing and optimizing the mass of this housing. Composite material is understood to mean a material comprising woven fibers embedded in a resin, in particular a thermoplastic resin according to the invention.

[0047] Advantageously, the fibrous reinforcement comprises inorganic fibers. For example, the fibers comprise mineral fibers, metallic fibers, thermoplastic polymers, thermosetting polymers, or a mixture of these fibers.

[0048] The fibers of the fibrous reinforcement are advantageously chosen, for example, from the group including Kevlar fibers, glass fibers, and carbon fibers. Depending on their size, the fibers can be described as short (between 0.1 and 1 mm), long (between 1 and 50 mm), or continuous (greater than 50 mm).

[0049] Preferably, the fibers of the fibrous reinforcement are made of carbon or glass.

[0050] Preferably, the fibers of the fibrous reinforcement are continuous.

[0051] The fibers of the fibrous reinforcement can be woven or grouped into strands containing, for example, 3,000 to 12,000 fibers with a diameter of approximately 7 pm.

[0052] The matrix or resin allows the fibrous reinforcement to be densified in order to obtain the final rigid composite part. The terms "matrices" and "resins" are used interchangeably in this description.

[0053] Thermoplastic composite materials comprise a matrix belonging to the large family of organic matrices also called polymer matrices.

[0054] The matrix is ​​advantageously chosen from thermoplastic polymers. An example of a thermoplastic resin is a polyamide, a polyetheretherketone (PEEC), A polyetherketoneketone, poly(phenylene sulfide) or a polyaryletherketone (PAEK). Such a choice of resin makes it possible to meet the specifications of the aeronautical industry in terms of temperature resistance and / or resistance to aggressive chemical agents such as cleaning or de-icing products.

[0055] Polyaryletherketones (PAEK) are a family of polymers with high thermomechanical properties, even at high temperature.

[0056] The manufacturing process according to the invention includes a step of supplying SI 10 with several plies 50 made from a first thermoplastic composite material.

[0057] The first thermoplastic composite material TP (more simply referred to as "TP material" in the rest of the description), is in particular, but not limited to, a polyetheretherketone (PEEK) or a polyaryletherketone (PAEK).

[0058] Preferably, the first thermoplastic composite material TP is of the LM PAEK type, according to the Anglo-Saxon acronym "Low Melt PAEK". This material belongs to the PAEK family and has the advantage of having a lower melting temperature than other materials in this family, therefore being less demanding to process while maintaining properties equivalent to other materials in this PAEK family.

[0059] Alternatively, the first thermoplastic composite material TP can be a polyether ketone (PEKK), a polyphenylene sulfone (PPS), a polyether-imide (PEI), a polyphenylene sulfone (PPSU), a polyether sulfone (PESU), a polysulfone (PSU) or a polyamide (PA).

[0060] Each ply is formed for example by a 2D or 3D weave of fibers, preferably a two-dimensional (2D) weave which is more suitable for parts to be manufactured with a thin thickness, such as a hood for example.

[0061] Preferably, the folds are advantageously pre-impregnated with the polymeric matrix.

[0062] By ply, we mean a strip of fibers, preferably pre-impregnated with a resin. The plies 50 of the plurality of plies 50 are arranged parallel to each other and in several layers. In other words, the plies 50 are stacked one on top of the other.

[0063] Preferably, the prepreg materials used are resin composite materials with continuous or discontinuous fibers, for example with discontinuous long fibers called "Discontinuons Long-Fiber" (DLF) in Anglo-Saxon terminology.

[0064] Preferably, the SI 10 supply step of the 50 folds comprises: - a pre-consolidation step of the 50 plies made in the first thermoplastic composite material, and - a step of trimming the folds 50 according to the dimensions of the part 40 to be manufactured.

[0065] After the trimming step, the folds 50 are cleaned and checked, for example visually.

[0066] The pre-consolidation step includes an impregnation step which can be carried out using different methods: by powder coating, by films, or by bonded thermoplastic and carbon fibers. The impregnation is carried out by hot calendering.

[0067] The pre-consolidation step continues with a stacking step of plies according to a predefined definition based on the number of plies and their orientation, then a consolidation step under press or by hot calendering in a double belt press.

[0068] The manufacturing process continues with a step S120 of heating the plies 50 to form a preform 52 which constitutes the fibrous reinforcement. This preform is also called the consolidated blank of the composite material part. Preferably, the step of heating the plies 50 to form the preform 52 is carried out at a first temperature in an oven. The first temperature is preferably between 320°C and 400°C. This S120 step of heating the 50 plies allows the thermoplastic matrix to be fused.

[0069] Next, the preform 52, which has an initial shape, is placed in a mold, for example a stamping mold, in S130.

[0070] More specifically, the preform 52 is transferred and installed rapidly in a first cavity of a mold.

[0071] According to an exemplary embodiment, the mold comprises a first part and a second part. The first part of the mold advantageously comprises the first cavity for receiving the preform. The second part of the mold advantageously comprises a second cavity that opens onto an internal surface of the second part. In this example, the second cavity is oriented towards the preform when the latter is placed in the first cavity. The second cavity has a complementary shape to an external surface of the part to be manufactured. The first and second cavities together form a space for receiving the preform.

[0072] The second part of the mold is movable relative to the first part, for example between an open position and a closed position. The first part moves in a non-limiting manner along a translation.

[0073] The process includes a stamping step S140 of the preform so as to modify the initial shape of the preform 52 in order to obtain a substantially final shape of the part 40.

[0074] During this step S140, the second part of the mold moves so as to apply the second impression to the preform. Advantageously, the movement is carried out in a vertical direction towards the preform 52.

[0075] During this stamping step, a second predetermined temperature and a predetermined pressure are applied in the mold.

[0076] Preferably, the second predetermined temperature is between 180°C and 250°C.

[0077] Preferably, the predetermined pressure is between 20 bars and 2,000 bars, preferably between 800 and 1,200 bars.

[0078] The second part of the mold is advantageously in the closed position allowing the preform 52 to be densified and the initial shape of the preform to be modified to obtain a substantially final shape of the part 40 in composite material to be manufactured.

[0079] The preform 52 with the pre-impregnated fibers is compressed when the mold is closed.

[0080] At the end of the stamping step S140, the mold is opened by moving the second part of the mold advantageously vertically, in the opposite direction to the closing and the preform removed.

[0081] The process also includes an overmolding step S150 of the preform 52 by injecting a second thermoplastic composite material to form an overmolded portion 54 on the preform 52 so as to form the final part 40.

[0082] Preferably, the second thermoplastic composite material comprises short fibers.

[0083] Preferably, the second thermoplastic composite material is a short fiber composite material.

[0084] For example, the second composite material is a polyether ketone (PEKK), a polyarylether ketone (PAEK), a polyether-imide (PEI), a polyether sulfone (PESU), a polyphenylene sulfone (PPSU), a polyphenylene sulfone (PPS), a polysulfone (PSU) or a polyamide (PA).

[0085] Advantageously, the second composite material is of the PEEK CF30 / GL30 type. PEEK CF30 is a PEEK (polyether-ether-ketone) type material filled with 30% carbon, which gives it a high degree of rigidity and resistance to fining.

[0086] According to this embodiment, the stamping steps S140 and overmolding steps S150 are consecutive.

[0087] In this case, the process includes a preheating step of the second material before its injection during the overmolding step S150 at a third predetermined temperature. During this step, the second material is heated in below its melting temperature in order to allow fusion of the interfaces without deconsolidating the first and second materials.

[0088] The third temperature depends on the polymer material used. For example, for PEEK, the third temperature for carrying out the injection is preferably between 360°C and 410°C.

[0089] The S150 overmolding step ensures a sealing and stiffening function.

[0090] Advantageously, the manufacturing process may include a punching step to form holes 56 through the preform and the overmolded portion. The through holes 56 are intended to receive fasteners 44 for assembly.

[0091] This step can advantageously be carried out during the S140 stamping step, for example by means of needles which punch the preform and the overmolded portion using a mechanism integrated into the mold.

[0092] Alternatively, this step can be carried out after the S140 stamping step.

[0093] For example, the fasteners 44 may be countersunk screws having a conical head as shown in [Fig.4].

[0094] In this case, the S150 overmolding step advantageously allows these milled screws to be taken into the clevis in their height.

[0095] According to another alternative embodiment, the stamping steps S140 and overmolding steps S150 are simultaneous. In this case, a single mold is advantageously used for both the stamping steps S140 and the overmolding steps S150. Stamping is performed during the mold closing step, and injection immediately after the mold is closed.

[0096] Advantageously, the manufacturing process may include, after the overmolding step, one or more finishing steps, for example, a preparation step for surface treatment, a surface treatment step for painting, a painting step of the part, a marking step of the part and / or a checking step of the part.

Claims

Demands

1. A manufacturing method (S 100) for a part (40) made of a fiber-reinforced composite material densified by a matrix for a turbomachine, in particular for aircraft, the method being characterized in that the matrix is ​​of the thermoplastic type and in that it comprises the following steps: - supplying (S 10) several plies (50) made of a first thermoplastic composite material; - heating (S 120) the plies (50) so as to form a preform (52); - placing (S 130) the preform (52) in a mold, the preform having an initial shape; - stamping (S 140) the preform (52) so as to modify the initial shape of the preform so as to obtain a substantially final shape of the part; - overmolding (S 150) of the preform (52) by injection of a second thermoplastic composite material to form an overmolded portion (54) on the preform so as to form the part.

2. A manufacturing method according to the preceding claim, wherein the step of supplying (S 110) the plies (50) comprises: - a step of pre-consolidating the plies (50) made in the first thermoplastic composite material, and - a step of trimming the plies (540) according to the dimensions of the part (40) to be manufactured.

3. A manufacturing method according to claim 1 or 2, wherein the heating step (S 120) of the plies so as to form a preform (52) is carried out at a first temperature, the first temperature being between 320°C and 400°C.

4. A manufacturing method according to any one of the preceding claims, wherein the second thermoplastic composite material comprises short fibers.

5. A manufacturing method according to any one of claims 1 to 4, wherein the stamping (S 140) and overmolding (S 150) steps are simultaneous.

6. A manufacturing method according to any one of claims 1 to 4, wherein the stamping (S 140) and overmolding (S 150) steps are consecutive, the method comprising a step of preheating of the second material before its injection during the overmolding step (S150).

7. A manufacturing method according to any one of the preceding claims, comprising a punching step to form holes (56) through the preform (52) and the overmolded portion (54).

8. A manufacturing method according to any one of the preceding claims, wherein the fibrous reinforcement comprises fibers selected from the group including Kevlar fibers, glass fibers, carbon fibers.

9. A manufacturing method according to any one of the preceding claims, wherein the preform fibers (52) are pre-impregnated.

10. A manufacturing method according to any one of the preceding claims, wherein the first thermoplastic composite material is a polyether ketone (PEKK), a polyetheretherketone (PEEK), a polyaryletherketone (PAEK), a polyphenylene sulfone (PPS), a polyetherimide (PEI), a polyphenylene sulfone (PPSU), a polyether sulfone (PESU), a polysulfone (PSU) or a polyamide (PA), preferably of the low melting point polyaryletherketone (LM-PAEK) type.

11. A manufacturing method according to any one of the preceding claims, wherein the second thermoplastic composite material is a polyether ketone (PEKK), a polyarylether ketone (PAEK), a polyether-imide (PEI), a polyether sulfone (PESU), a polyphenylene sulfone (PPSU), a polyphenylene sulfone (PPS), a polysulfone (PSU) or a polyamide (PA), preferably of the PEEK CF30 type.

12. A manufacturing method according to any one of the preceding claims, wherein the part (40) to be manufactured is an engine cowling of a turbomachine, in particular of an aircraft turbomachine.

13. Turbomachine, in particular for aircraft, comprising at least one part (40) manufactured by the manufacturing process according to any one of the preceding claims and in particular an engine cowling.

14. Turbomachine according to claim 13, wherein the engine cowling is a fixed cowling, in particular a cowling for stator blades (OGV).

15. Turbomachine according to claim 13, wherein the engine cowling is a rotating cowling, in particular a propeller or fan cowling.

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