• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a method for manufacturing a blade of composite material extending in a main elongation direction, the composite material of said blade comprising a fiber reinforcement densified by a matrix, the method comprising the following steps: step of weaving warp yarns and weft yarns to obtain a fibrous blank, the fibrous blank comprising at least one warp yarn adapted to form in the matrix at least a first portion of a channel, said length portion of the warp thread being directed in the main elongation direction of the blade and opening at the foot of the blade, the first channel portion formed in the matrix by said length portion of warp length thereby constituting at least a first portion the internal airflow channel; a step of shaping the fiber blank so as to produce a preform of the blade and densification of the preform; characterized in that the weaving step comprises the introduction of at least a second portion of wire adapted to form in the matrix a second portion of a channel, said second portion of wire being directed transversely to said direction main elongation and opening at the trailing edge of the blade, the second channel portion formed in the matrix by said second wire portion also constituting at least a second portion of the internal air flow channel.
    公开号:FR3032145A1
    申请号:FR1550699
    申请日:2015-01-29
    公开日:2016-08-05
    发明作者:Paul Antoine Foresto；Adrien Jacques Philippe Fabre
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to a method for manufacturing a blade of a turboprop propeller of an aircraft. More specifically, it relates to a fiber weaving process for the manufacture of a composite blade.
    [0002] GENERAL TECHNICAL FIELD AND STATE OF THE ART The current turboprop engines for aircraft, and more particularly the turboprop engines for aircraft, encounter a problem of interference between the propeller and the air intake. Indeed, for integration and mass constraints, these two components of the turboprop are very close to each other, for example of the order of a few centimeters. It will be understood that the operation of the air inlet is strongly impacted by the passage of rotating blades. It is the same for the operation of the propeller which is modified very locally during its passage in front of the nacelle and the air inlet. The role of the propeller is to provide a tractor effort directed towards the front of the aircraft to enable it to compensate for the halftone force and thus move forward. The role of the air intake, on a turboprop, is to supply the engine with air and to protect it from external aggressions. For reasons of compressor performance and operability, the air supply must be as homogeneous as possible in order to limit the distortion (the difference between the average total pressure and the minimum total pressure). The integration of the air intake must also be done taking into account constraints specific to turboprops, such as the presence of a gearbox for the propeller (or PGB for Propeller Gear Box according to the English terminology well known), an engine-nacelle interface, a de-icing system and compliance with ingestion constraints. Compliance with these constraints results in an S-shaped air intake which is very sensitive to distortion and penalizes the efficiency. The passage of the blades in front of the air intake during the rotation of the propeller creates a distortion disturbance in the air upstream of the air inlet, but also a drop in the dynamic pressure, also called total pressure , (wake of the blades). This drop impairs the operation and the efficiency of the air intake by increasing the pressure losses. Decreasing air intake efficiency directly impacts engine performance. The reduction of the distortion makes it possible to increase the operability of the turboprop compressor. Outside the wake of the blades, the propeller slightly compresses the flow, so as to increase the dynamic pressure. This compression has a beneficial effect on the operation of the air intake, but is mitigated by the negative effect of the wake of the blades. In order to compensate for the total pressure drop in the wake of the blades ingested by the air inlet, it is possible to produce blades each comprising an internal air flow channel which comprises an inlet opening at the foot of the blades and an outlet opening in the vicinity of the trailing edge of the blades so that an internal air flow can flow from the foot to the trailing edge of the blades, and that said internal air flow is expelled by the outlet of the internal airflow channel towards the air inlet so as to reduce the wake of the blades at the air inlet. However, such a solution requires making an internal flow channel in each of the blades of the propeller comprising at least one outlet opening at the trailing edge of the blades. In addition, the positioning of the outlet of the internal airflow channel along the blades as well as the direction of the output of said internal airflow channel must be precise so that the airflow which is expelled by the outlet of said internal airflow channel can effectively reduce the wake of the blades at the air inlet. However, for reasons of mass savings, the current aircraft turboprop propeller blades are made of composite material, that is to say composed of a fiber reinforcement densified by a matrix. However, standard manufacturing processes blades composite material does not make it possible to produce an internal air flow channel inside the blades.
    [0003] Document FR 2 955 609, however, discloses a method for manufacturing blades made of composite material by resin transfer molding with three-dimensional weaving (or 3D RTM for "three-dimensional resin transfer molding" according to the English name). Saxon well known) which comprise an air flow channel directed in the direction of main elongation of the blades, so that the internal air flow channel comprises an inlet opening at the foot of the blades, and an outlet opening at the top of the blades. However, the teaching of document FR 2 955 609 does not make it possible to make blades of composite material each comprising an internal air flow channel which has an outlet opening in the vicinity of the trailing edge of the blades. GENERAL PRESENTATION OF THE INVENTION A general object of the invention is to provide a method for the manufacture of a blade of composite material which comprises an internal air flow channel comprising an inlet opening at the foot of the blade as well as an outlet opening in the vicinity of the trailing edge of said blade. In addition, the invention also makes it possible to produce such blades with a manufacturing method that does not require a major modification of the production tooling for the manufacture of blades made of composite material. More particularly, according to a first aspect, the invention relates to a method of manufacturing a blade made of 3D RTM composite material extending in a main elongation direction, said blade comprising a foot, a trailing edge and at least one internal air flow channel, said blade being obtained from a fiber reinforcement densified by a matrix, the method comprising the following steps: a step of weaving a plurality of warp yarns and a plurality of weft yarns so as to obtain a fibrous blank, the fibrous blank comprising at least one warp thread adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, said portion of length of the warp yarn being directed in the main elongation direction of the blade and opening at the foot of the blade, the first channel portion formed in the matrix by said length portion of yarn chain thus constituting at least a first portion of the internal air flow channel; a step of shaping the fibrous blank so as to produce a preform of the blade; a step of densifying the preform by impregnating said preform with a constituent material of the matrix; characterized in that the weaving step also comprises the establishment of at least a second portion of wire adapted to form in the matrix a second portion of a channel, said second portion of wire being directed transversely relative to said main elongation direction of the blade and opening at or near the trailing edge of the blade, the second channel portion formed in the die by said second wire portion also constituting at least a second portion of the blade; internal airflow channel.
    [0004] According to a further feature, the warp thread adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, and the second portion of wire adapted to form in the matrix a second portion of a channel, are hollow fibers.
    [0005] According to an additional characteristic, the warp thread adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, and the second portion of wire adapted to form in the matrix a second portion of a channel, are fugitive fibers, said method comprising a step of elimination by thermal or chemical treatment. According to another characteristic, the second portion of wire adapted to form a second portion of a channel in the matrix is a weft yarn extending from a leading edge of the blade to the trailing edge, said yarn of weft intersecting with contact the length portion of the warp thread adapted to form a first channel portion, so that the first and second portions of the internal air flow channel open into one another and allow a flow of air between one another. According to a particular characteristic, the manufacturing method 5 comprises a shut-off step in the vicinity of the leading edge of the second portion of the internal air flow channel. According to another characteristic, the shut-off step is carried out by laying an anti-erosion polyurethane film, or placing a defrost heating mat at the leading edge, or by injection of a resin, or by injection of a resin followed by the laying of a defrost heating mat at the leading edge. According to an additional characteristic, the warp thread adapted over at least a portion of its length to form in the matrix at least a first portion of a channel comprises a nonwoven free end with the weft threads which is folded and folded towards the trailing edge transversely to the main elongation direction of the blade, said free end being intended to form the second portion of the internal air flow channel directed transversely to said main elongation direction. According to an additional characteristic, the free end is woven with the warp yarns. According to one particular characteristic, the free end is deposited on the surface of the fibrous reinforcement without being woven. According to another characteristic, a warp yarn intended to form a channel directed in the main elongation direction and which extends from the foot to the level of a salmon of the blade, so as to form a first portion the internal air flow channel that opens at said blade salmon. According to a second aspect, the invention relates to a blade manufactured according to a manufacturing method according to one of the preceding characteristics.
    [0006] DESCRIPTION OF THE FIGURES Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows, and with reference to the appended drawings, given by way of non-limiting examples and in which: FIG. 1 represents a blade of a propeller of a turboprop which has been manufactured according to a manufacturing method according to the invention; FIG. 2 represents an explanatory diagram of the weaving of the threads constituting the fibrous reinforcement of a blade manufactured according to a first implementation of the invention; - Figure 3 shows a sectional view along the axis AA of the explanatory diagram of Figure 2 of a blade manufactured according to a first variant of the first implementation of the invention; - Figure 4 shows a sectional view along the axis AA of the explanatory diagram of Figure 2 of a blade manufactured according to a second variant of the first implementation of the invention; FIG. 5 represents an explanatory diagram of the position of the internal air flow channel in the blade manufactured according to the first implementation of the invention; FIG. 6 is an explanatory diagram of the weaving of the threads constituting the fibrous reinforcement of a blade made according to a second embodiment of the invention; FIG. 7 represents an explanatory diagram of the position of the internal air flow channel in the blade manufactured according to the second implementation of the invention; FIG. 8 represents an explanatory diagram of the weaving of the threads constituting the fibrous reinforcement of a blade made according to a third embodiment of the invention; FIG. 9 represents an explanatory diagram of the step of positioning a warp yarn which is intended to form a channel according to the third implementation of the invention; - Figure 10 shows a sectional view along the axis BB of the explanatory diagram of Figure 9 of a blade manufactured according to a first variant of the third implementation of the invention; - Figure 11 shows a sectional view along the axis BB of the explanatory diagram of Figure 9 of a blade manufactured according to a second variant of the third implementation of the invention; FIG. 12 represents an explanatory diagram of the position of the internal air flow channel in the blade manufactured according to the third implementation of the invention; FIG. 13 represents an explanatory diagram of a three-dimensional weave weave of the interlock type; FIG. 14 represents a first explanatory diagram of the control of the direction of the entry of the internal channel of air flow; - Figure 15 shows a second explanatory diagram of the control of the direction of the inlet of the internal channel of the air flow. DESCRIPTION OF ONE OR MORE EXEMPLARY EMBODIMENTS FIG. 1 shows a blade 1 of a propeller of a turboprop. The blade 1 extends in a direction of main elongation a and comprises a leading edge 11, a trailing edge 12, a foot 13, a vertex, a radius, a salmon 14, a lower surface and an upper surface. Salmon 14 of the blade 1 is the surface of the top of the blade 1 for which the blade 1 has its maximum radius. The blade 1 also comprises a skeleton line S, which is constituted by the points located equidistant from the intrados and the extrados. The blade 1 comprises an internal air flow channel 2 which extends, inside said blade 1, from its foot 13 to the salmon 14 of the blade 1. air 2 comprises at least a first portion 21 which extends from an inlet 23 opening at the bottom of the foot 13, and which is directed in the main direction of elongation a. The internal air flow channel 2 also comprises at least a second portion 22 which is connected to at least a first portion 21, and which connects said first portion 21 to an outlet 24 which opens at the trailing edge 12 or in its immediate vicinity. Said second portion 22 is directed transversely to the main elongation direction a of the blade 1 being for example, but not necessarily, perpendicular to the general direction of the trailing edge 12. Thus, the internal flow channel of 2 air opens the blade 1 by one or more output (s) 24 which is (are) located at the trailing edge 12 and / or is (are) located in its immediate vicinity. In FIG. 1, the internal air flow channel 2 comprises a first portion 21, an inlet 23, four second portions 22 and four outlets 24, said four second portions 22 being each connected to the first portion 21. However, it is only a non-limiting example of the number of first and second portions 21 and 22, input 23 of outputs 24.
    [0007] The outlets 24 are disposed in an area of the trailing edge 12 likely to end up at the right of an air inlet of the turboprop engine during the rotation of the propeller. Thus, the outlets 24 are preferably located between 0% and 25% of the height of the blade 1.
    [0008] They are distributed there being regularly spaced relative to each other. The blade 1 is composed of a composite material, comprising a fibrous reinforcement and a matrix, and all the implementations of the invention comprise the following steps which are the basic steps for the manufacture of a composite material blade. a step of weaving a plurality of warp yarns 3 and weft yarns 4 so as to produce a fibrous blank which constitutes the fibrous reinforcement; a step of forming in a mold the fibrous blank obtained in the preceding step so as to produce a preform whose shape is close to the blade to be manufactured; a step of densifying the preform obtained in the preceding step by impregnating the preform with a material constituting the matrix. The warp yarns 3 are yarns which are directed in the main elongation direction a of the blade 1, and the weft yarns 4 are yarns which are orthogonally oriented with respect to the warp yarns 3 and which connect the yarn edge. Attack 11 at the trailing edge 12. The warp yarns 3 and the weft yarns 4 are generally made of carbon, but other materials can also be used. The weaving of the warp yarns 3 and the weft yarns 4 is preferably a three-dimensional weave with "interlock" weave, as represented in FIG. 13. Here, the term "interlock" weave is understood to mean a weave in which each layer of yarn is woven. chain 3 binds several layers of weft threads 43 with all the threads of the same weft column having the same movement in the plane of the armor. However, other armor can be used. Even more preferably, the fibrous reinforcement is obtained by weaving with 3D armor of the "interlock" type at the heart, and a 2D or 3D armor of satin skin type. Reference can be made to WO2006 / 136755, which teaches the weaving of a fibrous reinforcement according to such a technique. For an example of manufacturing blades made of composite material with this type of technique, reference may also be made to document FR2955609, which proposes, in particular, various possible variants concerning the weaving of the yarns or the choice of materials.
    [0009] In addition, in the manufacturing process of the blade 1, the fibrous blank comprises at least one chain wire 31 adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, said length portion of the warp yarn 31 being directed in the main elongation direction a of the blade 1 and opening at the foot 13 of said blade 1. The first channel portion formed in the matrix by said length portion of yarn chain 31 thus constitutes at least a first portion 21 of the internal air flow channel 2. Finally, the weaving step also comprises the introduction of at least a second portion of wire adapted to form in the matrix a second portion of a channel, said second portion of wire being directed transversely to said main elongation direction a and opening at the trailing edge 12 of the blade 1 or in the vicinity thereof. The second channel portion formed in the matrix by said second portion of wire also constitutes at least a second portion 22 of the internal air flow channel 2. As illustrated in FIG. 2, according to a first possible implementation. , the manufacturing method comprises a step of positioning at least one warp thread 31 adapted along its length to form in the die at least a first portion of a channel and at least one weft thread 41 adapted to its length for forming in the matrix a second portion of a channel, so as to make the internal air flow channel 2 inside the blade 1.
    [0010] In this implementation, the second portion of wire adapted to form in the matrix a second portion of a channel is constituted by the weft thread 41 which is adapted along its length to form in the matrix a second portion of a channel . This warp yarn 31 and weft yarn 41 are fugitive fibers which can be removed by appropriate treatment during an elimination step, for example a chemical treatment or a heat treatment. The fugitive fibers may be for example polyvinyl acetate or polyethylene, so that they can be removed by a heat treatment. The fibers may also be polyvinyl alcohol (PVA) so that it can be removed by chemical treatment. This warp yarn 31 and this weft yarn 41 can also be hollow fibers, so that the manufacturing method does not require a step of eliminating the warp yarn 31 and the weft yarn 41.
    [0011] In one possible implementation, the method comprises a step in which at least one weft yarn 4 formed in the base material (for example carbon) is replaced by a weft yarn 41 adapted to form a channel in the matrix. This weft yarn 41 adapted to form a channel in the matrix extends from the leading edge 11 to the trailing edge 12, and is positioned at a desired height, preferably between 0% and 25% of the height of the blade. 1. This weft thread 41 adapted to form a channel is intended to form a second portion 22 of the internal air flow channel 2.
    [0012] The method also comprises a step in which at least one warp thread 3 is replaced by a warp thread 31 fitted along its length to form a channel. This warp thread 31 is braided with the weft threads 4 from the portion of the fibrous reinforcement intended to form the foot 13 of the blade 1 to a desired height which is at least equal to the height at which a weft thread 41 adapted along its length to form a channel is positioned, so that said one warp thread 31 and said weft thread 41 are in contact. The warp yarn 31 and the weft yarn 41 can be woven with the weft yarns 4 and warp yarns 3 in a different or identical weave to the weave used to weave the warp yarns 3 and weft yarns. shown in Figure 2, the fiber reinforcement comprises two warp son 31 adapted along their length to form channels and two weft son 41 adapted to form channels. The warp threads 31 are woven on different lengths. The warp threads 31 are in contact with a single weft thread 41. However, according to one variant, said warp threads 31 may be in contact with several weft threads 41.
    [0013] Figures 3 and 4 schematically illustrate two variants of this implementation. According to the variant illustrated in FIG. 3, the warp thread 31 is located in the center of the fibrous reinforcement (and therefore in the center of the blade 1). This variant makes it possible to guarantee a better mechanical strength of the blade 1, with respect to the variant illustrated in FIG. 4, wherein said warp thread 31 is located in a less central part of the blade 1 and therefore closer to the outer surface of the blade. In general, in all implementations, it is preferable to position the warp yarns 31 and the weft yarns 41 in the center of the fibrous reinforcement so that the channel portions thus formed are located in the center of the pile. the blade 1. As illustrated in FIG. 5, following the densification step of the preform, and at the potential step of eliminating the warp yarns 31 and the weft yarns 41, the blade 1 is formed and comprises a channel internal air flow 2 which opens at the foot 13, the trailing edge 12 of the blade 1 or in the vicinity thereof, and the leading edge 11 or in the vicinity thereof. The fact that the internal air flow channel 2 opens to the leading edge 11, or in its vicinity, can cause a degradation of the performance of the blade 1, as well as possible risks of obstruction by foreign bodies. during operation of the turboprop. Thus, the method comprises a shutter step at the leading edge 11 of the internal air flow channel 2. This shutter step can be performed, for example, by applying an anti-erosion polyurethane film. by placing a defrost heating mat at the leading edge 11, or by injection of a resin. It is also possible to inject a resin and put a heating mat at the leading edge 11.
    [0014] According to a second possible embodiment, and as illustrated in FIGS. 6 and 7, the manufacturing method may comprise a step of positioning a warp thread intended to form a channel 32 which is woven from the reinforcement portion fibrous to form the foot 13 of the blade 1, to the portion of the fibrous reinforcement for forming the salmon 14 of the blade 1. Such a step forms a first portion 21 of the internal air flow channel 2 which opens at the level of the salmon 14 of the blade 1. The fact that the internal air flow channel 2 opens at the level of the salmon 14 allows a flow of air to be ejected by said salmon 14, which allows to improve the aerodynamic performance of the turboprop.
    [0015] The warp yarn intended to form a channel 32 may be in contact with one or more weft yarns 41, or it may not be in contact with said weft yarns 41. In addition, according to one variant, a suitable warp yarn 31 may be used. along its length to form in the matrix a first portion of a channel may be woven from the foot 13 to the salmon 14, so that the internal air flow channel 2 opens in the vicinity of the salmon 14. According to a third embodiment still implemented (Figures 8 to 11), the manufacturing method of the blade 1 may not include a positioning step of a weft thread 41 adapted along its length to form in the matrix a second portion of 'a canal. In order to control the thickness of the fibrous reinforcement (and thus of the blade 1), fiber layers are stacked, the length over which the warp yarns 3 and the weft yarns 4 are woven is controlled. Thus, as shown in FIG. 8, the warp yarns 4 comprise a non-woven free end 30 which is intended to be cut. A manufacturing method according to this third embodiment may for example comprise a positioning step of at least one chain wire 31 fitted over at least a portion of its length to form a first portion of a channel in the matrix. replacing a warp yarn 3 formed in the base material by a said warp yarn 31. This warp yarn 31 is positioned in a layer whose warp yarns 3 are not woven integrally, and therefore comprises a free end 33 no woven with the weft threads 4 which is intended to be cut. As shown in FIG. 9, this free end 33 is folded and folded towards the trailing edge 12 transversely with respect to the main elongation direction a of the blade 1, so that said warp thread 31 is folded L-shaped and that the free end 33 is thus adapted to form the second portion 22 of the inner air flow channel 2. As shown in Figures 10 and 11, the free end 33 of the warp thread 31 which is folded can be either woven with the warp threads 3, or deposited on the surface of the fibrous reinforcement. When the free end 33 of the warp thread 31 is woven with the warp threads 3, it can be woven in an interlock weave or in other possible armor. In this implementation, the second portion of wire adapted to form in the matrix a second portion of a channel is constituted by the free end 33 of the warp thread 31 which is adapted along its length to form in the die a second portion of a canal. According to a variant of this implementation, the method may comprise a step of positioning a warp thread intended to form a channel 32 directed along the main elongation direction a which extends from the foot 13 to the level salmon 1 of the blade 1, so as to form a first portion 21 of the internal air flow channel 2 which extends from the foot 13 to the salmon 14, and which opens at the foot 13 and at the salmon 14.
    [0016] In order to control the direction of the outlet 24 of the internal airflow channel 2, it is possible to control an angle i3 created by the axis of said outlet 24 and a skeleton line S of the blade 1 to 12. The skeletal line S is a parameter which is determined by the profile of the blade 1, and which directly influences the wake of the blade 1. The control of this angle i3 is achieved by adapting the weave with which the weft thread 41 or the free end 33 are woven with the warp threads 3.
    [0017] Indeed, as can be seen in FIGS. 14 and 15, it can be seen that the weave used for the weaving has a direct influence on the direction of the free end 33 of the warp thread 31 which will form the outlet 24. The outlet 24 is formed by the free end 33 of a warp thread 31. However, it is also possible to control the angle i3 between the skeleton line S and the axis of the outlet 24 by adapting the armor in the case of weaving. a weft thread 41 adapted to form a channel in the first and second embodiments of the invention. In the case where the second portion of wire adapted to form in the matrix a second portion of a channel (for example a weft thread 41 adapted along its length to form a channel, or a free end 33 of a warp yarn 31 adapted along its length to form a channel) is not woven and is only deposited on the surface of the fibrous reinforcement, the angle i3 is easily determinable because said second portion of wire adapted to form in the matrix a second portion of a channel will be directed along the intrados or extrados of the blade 1, following the face of the fibrous reinforcement on which it is deposited. In order to increase the diameter of the internal air flow channel, it is possible, for any implementation of the invention, to use a plurality of warp threads 31, and / or several threads of frame 41, by juxtaposing them so as to increase the diameter of the channel created by the elimination of said warp and / or warp threads 41. In the case where the warp 31 and / or warp threads 41 are hollow fibers it is possible to increase the diameter of the fibers to increase the diameter of the created channels.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. A method of manufacturing a blade (1) of composite material extending in a main elongation direction (a), said blade comprising a foot (13), a trailing edge (12) and at least one internal channel of air flow (2), the composite material of said blade (1) comprising a fiber reinforcement densified by a matrix, the method comprising the following steps: - a step of weaving a plurality of warp yarns (3) and a plurality of weft yarns (4) so as to obtain a fibrous blank, the fibrous blank comprising at least one warp yarn (31) adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, said length portion of the warp yarn (31) being directed in the main elongation direction (a) of the blade (1) and opening at the foot (13) of the blade ( 1), the first channel portion formed in the matrix by said length portion of warp thread ( 31) thereby constituting at least a first portion (21) of the inner airflow channel (2); a step of shaping the fibrous blank so as to produce a preform of the blade (1); a step of densifying the preform by impregnating said preform with a constituent material of the matrix; Characterized in that the weaving step also comprises placing at least a second portion of wire adapted to form a second portion of a channel in the matrix, said second portion of wire being directed transversely relative to said main elongation direction (a) and opening at or near the trailing edge 30 (12) of the blade (1), the second channel portion formed in the die by said second portion of wire also constituting at least a second portion (22) of the inner airflow channel (2).
    [0002]
    2. Method according to claim 1, characterized in that the warp thread (31) adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, and the second portion of suitable wire to form in the matrix a second portion of a channel are hollow fibers.
    [0003]
    3. Method according to claim 1, characterized in that the warp yarn (31) adapted over at least a portion of its length to form in the matrix at least a first portion of a channel, and the second portion of yarn adapted to form in the matrix a second portion of a channel are fugitive fibers, said process comprising a step of elimination by thermal or chemical treatment.
    [0004]
    4. Method according to one of claims 1 to 3, characterized in that the second portion of wire is a weft thread (41) extending from a leading edge (11) of the blade (1) until at the trailing edge (12), said weft yarn (41) intersecting with contact the length portion of the warp yarn (31) adapted to form a first channel portion, so that the first and second portions (21) 22) of the internal air flow channel (2) open into each other by virtue of the contact between said wires (41, 31), thus allowing the circulation of an air flow from the foot ( 13) to the trailing edge (12).
    [0005]
    5. Method according to claim 4, characterized in that it comprises a closing step in the vicinity of the leading edge (11) of the second portion (22) of the inner air flow channel (2).
    [0006]
    6. Method according to claim 5, characterized in that the sealing step is performed by the application of an anti-erosion polyurethane film, or the installation of a defrost heating mat at the leading edge (11). , or by injection of a resin, or by injection of a resin followed by the laying of a defrost heating mat at the leading edge (11).
    [0007]
    7. Method according to one of claims 1 to 3, characterized in that the chain wire (31) adapted to at least a portion of its length to form in the matrix at least a first portion of a channel comprises a free end (33) non-woven with the weft yarns (4) which is folded and folded towards the trailing edge (12) transversely to the main elongation direction (a) of the blade (1), said free end ( 33) being intended to form the second portion (22) of the internal air flow channel (2) directed transversely to said main elongation direction (a).
    [0008]
    8. Method according to claim 7, characterized in that the free end (33) is woven with the warp son (3).
    [0009]
    9. The method of claim 7, characterized in that the free end (33) is deposited on the surface of the fibrous reinforcement without being woven.
    [0010]
    Method according to claim 4 or claim 7, characterized in that a warp thread intended to form a channel (32) directed in the main elongation direction (a) extends from the foot (13). to the level of a salmon (14) of the blade (1), so as to form a first portion (21) of the internal air flow channel (2) which opens at said salmon (14) of the blade (1).
    [0011]
    11. Paddle (1) manufactured according to a manufacturing method according to one of claims 1 to 10.
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    EP3927529A1|2021-12-29|Repair or resumption of manufacture of a composite material part with fibrous three-dimensional woven reinforcement
    FR3111660A1|2021-12-24|Blade in two-dimensional woven skin composite material incorporating a metal insert and its manufacturing process
    EP3930991A1|2022-01-05|Repairing or resuming production of a component made of composite material
    同族专利:
    公开号 | 公开日
    US20160221273A1|2016-08-04|
    US10406761B2|2019-09-10|
    FR3032145B1|2017-02-10|
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    法律状态:
    2016-01-11| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-05| PLSC| Publication of the preliminary search report|Effective date: 20160805 |
    2017-01-05| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-10| CD| Change of name or company name|Owner name: SNECMA, FR Effective date: 20170713 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 4 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-12-17| PLFP| Fee payment|Year of fee payment: 7 |
    2021-12-15| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1550699A|FR3032145B1|2015-01-29|2015-01-29|METHOD FOR PRODUCING A PROPELLER BLADE|FR1550699A| FR3032145B1|2015-01-29|2015-01-29|METHOD FOR PRODUCING A PROPELLER BLADE|
    US15/009,458| US10406761B2|2015-01-29|2016-01-28|Method for manufacturing a propeller blade|
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