MOLDING DEVICE FOR PRODUCING A DAWN FOOT

Abstract

The invention relates to a molding device (100) for manufacturing a blade (11) root (14) comprising: - a first molding block (101), - a second molding block (102), the sleeve (15) being axially interposed between the first and second blocks (101, 102) and being held axially clamped in a sealed manner between the first and second blocks (101, 102), one of the first and second blocks (101, 102) comprising at least one resin inlet port (120), and the other of the first and second blocks (101, 102) comprising at least one resin outlet port (121), the channel (119) and the cavity (110) being in fluid communication via the internal passage (15f) of the sleeve (15) so that the resin flows from the inlet port (120) to the outlet port (121) through the channel (119), the internal passage (15f) and the cavity (110). Abstract figure: Figure 7

Description

Title of the invention: MOLDING DEVICE FOR PRODUCING A DAWN FOOT Technical field of the invention

[0001] The invention relates to the field of molding devices for the manufacture of blade roots for aircraft turbomachines.

[0002] The invention relates in particular to the field of molding devices for the manufacture of blade roots which comprise a metal sleeve and a spar made of composite material.

[0003] The invention also relates to a method of manufacturing these blade roots by molding. Technical background

[0004] An aircraft turbomachine typically extends around and along a longitudinal axis. It comprises, from upstream to downstream in the direction of gas flow along this longitudinal axis, a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and a gas exhaust nozzle.

[0005] The blower allows the suction of an air flow dividing into a primary air flow and a secondary air flow. The primary air flow passes through a primary vein of the turbomachine while the secondary air flow is directed towards a secondary vein surrounding the primary vein.

[0006] The primary air flow is compressed within the compressors. The compressed air is then mixed with a fuel and burned within the combustion chamber. The gases resulting from the combustion pass through the turbines and then escape through the nozzle, the cross-section of which allows the acceleration of these gases to generate propulsion.

[0007] The fan typically comprises blades regularly distributed around the longitudinal axis and rotatable around this longitudinal axis. The blades extend radially from a disc centered on the longitudinal axis. The blades may have a variable pitch angle. They are then also rotatable around their extension axes which are perpendicular to the longitudinal axis of the turbomachine.

[0008] Each fan blade typically comprises a blade and a root. The blade has an aerodynamic shape and comprises a pressure face and an extrados face which are connected by a leading edge and a trailing edge. The root is connected to the blade and allows the blade to be fixed to the disc and also constitutes the rotation support of the blade around its axis of elongation. The root includes a sleeve connected to the disc and a spar connected to the blade.

[0009] The sleeve has a generally tubular shape and comprises an internal passage opening out at the axial ends of the sleeve. The spar has an aerodynamic shape and extends between two ends, one of which is received in the blade to secure the sleeve to the blade and the other in the internal passage of the sleeve to secure the spar to the sleeve.

[0010] To reduce the weight of the blade, it has been proposed to form the blade and the spar from a composite material. The composite material is typically an organic matrix composite material, also known by the acronym CMO. Such a composite material comprises reinforcing fibers embedded in a polymer matrix. The reinforcing fibers are, for example, organized in the form of a three-dimensionally woven fiber preform.

[0011] Furthermore, in order to ensure its support and anchoring functions, the foot is made of metallic material.

[0012] The blade root is typically manufactured by a resin transfer molding process also known by the English acronym RTM for "Resin Transfer Molding". Such a root manufacturing process typically comprises the following steps:

[0013] - provide the fiber preform of the spar,

[0014] - connect the preform to the sleeve by inserting a part of the preform into the passage internal sleeve,

[0015] - arranging the fiber preform and the sleeve in an internal cavity of a mold injection and

[0016] - inject resin into the cavity.

[0017] Such a manufacturing process presents many challenges. Indeed, since the metal sleeve is arranged in the internal cavity of the mold, closing this mold can cause the sleeve to move randomly, resulting in misalignments between the spar and the sleeve, which can lead to the final blade being rejected.

[0018] Furthermore, sealing defects between the mold and the sleeve were found, so that, during injection, resin could leak out of the cavity and cover the sleeve. Such resin leakage around the sleeve requires an additional step of resin removal, for example by machining the sleeve. This additional step can impact the mechanical properties of the sleeve and increase the manufacturing time of the blade, resulting in a significant additional manufacturing cost.

[0019] Consequently, there is a need to provide a solution allowing the manufacture of a blade root comprising a spar made of composite material and a sleeve made of metallic material, the risk of resin leakage around the sleeve of which is reduced in order to limit the manufacturing time of the blade and reduce the risk of mechanical defect, and the risk of misalignment between the spar and the sleeve of which is limited. Summary of the invention

[0020] To this end, the invention proposes a molding device for manufacturing a blade root for an aircraft turbomachine, the root comprising a metal tubular sleeve comprising an internal passage opening out at the axial ends of the sleeve, and a spar comprising a fiber preform embedded in a matrix and which axially passes through the internal passage of the sleeve, the device comprising:

[0021] - a first molding block comprising a cavity for receiving resin and at least one less a portion of the fiber preform.

[0022] The molding device according to the invention is remarkable in that it further comprises:

[0023] - a second molding block comprising a resin passage channel,

[0024] the sleeve being axially interposed between the first and second blocks and being held axially tight in a sealed manner between the first and second blocks, one of the first and second blocks comprising at least one resin inlet port, and the other of the first and second blocks comprising at least one resin outlet port, the channel and the cavity being in fluid communication via the internal passage of the sleeve so that the resin circulates from the inlet port to the outlet port via the channel, the internal passage and the cavity.

[0025] Thus, according to the invention, the sleeve is positioned axially between the first and second blocks and is therefore located outside the cavity for receiving the resin and the fiber preform. According to the invention, the sleeve is therefore an integral part of the molding device.

[0026] Thanks to such a position of the sleeve, and to its axial holding in a tight and sealed manner between the first and second blocks, the risks of resin leaking outside the internal passage of the sleeve are limited. It is therefore no longer necessary to implement an additional resin removal step to remove the resin deposits around the sleeve, which makes it possible to preserve the mechanical properties of the sleeve and to reduce the manufacturing time of the blade root.

[0027] Furthermore, the sleeve being located outside the first and second blocks and therefore outside the cavity for receiving the resin and the fiber preform, the risks of movement of the sleeve are limited during the handling of the first and second blocks and during resin injection, reducing the risk of misalignment between the sleeve and the fiber preform.

[0028] The invention may comprise one or more of the following features, taken in isolation from one another or in combination with one another:

[0029] - clamping members connect the first and second blocks.

[0030] - the clamping members comprise threaded rods.

[0031] - the threaded rods pass through holes formed in the first and second blocks.

[0032] - each of the first and second blocks comprises a hollow annular interface on in which one of the axial ends of the sleeve is in axial support.

[0033] - each interface is respectively provided in one face of the first and second blocks.

[0034] - a first sealing member is arranged between the sleeve and the first block, and a second sealing member is arranged between the sleeve and the second block.

[0035] - the first and second sealing members each comprise an annular seal.

[0036] - the first block and / or the second block comprises first and second parts connected together by connecting members.

[0037] The invention also relates to a method for manufacturing a blade root for an aircraft turbomachine, the root comprising a metal tubular sleeve comprising an internal passage opening at the axial ends of the sleeve, and a spar comprising a fibrous preform embedded in a matrix and which axially passes through the internal passage of the sleeve, characterized in that the method uses a molding device according to any one of the preceding characteristics, the method comprising the following steps:

[0038] (a) inserting the fiber preform into the internal passage of the sleeve,

[0039] (b) arranging the fiber preform in the first cavity of the first block,

[0040] (c) arranging the sleeve axially between the first and second blocks and connecting sealingly the sleeve to each of the first and second blocks,

[0041] (d) injecting the resin through the inlet port, and

[0042] (e) discharging the resin through the outlet port. Brief description of the figures

[0043] Other characteristics and advantages will emerge from the following description of non-limiting embodiments of the invention with reference to the appended drawings in which:

[0044] [Fig.l] is a schematic view in longitudinal section of a half aircraft turbomachine,

[0045] [Fig.2] is a schematic perspective view of a blade equipping the turbomachine of [Fig.l],

[0046] [Fig.3] is a perspective view of the sleeve equipping the blade of [Fig.2],

[0047] [Fig.4] is a perspective view of the spar equipping the blade of [Fig.2],

[0048] [Fig.5] is a perspective view of the device for molding the foot of the blade of the [Fig.2],

[0049] [Fig.6] is a perspective view of the first molding block of the device of [Fig.5],

[0050] [Fig.7] is a perspective view of the molding device in which the second part of the first molding block has been removed,

[0051] [Fig.8] is a perspective view of a first part of the first molding block in which the fiber preform of the foot is arranged,

[0052] [Fig.9] is a perspective view of the second part of the first molding block,

[0053] [Fig. 10] is a perspective view of the second molding block,

[0054] [Fig.l 1] is another perspective view of the second molding block,

[0055] [Fig. 12] is a perspective view of the first part of the second block of molding,

[0056] [Fig. 13] is a block diagram of the manufacturing process of the invention. Detailed description of the invention

[0057] An example of an aircraft turbomachine 1 according to the invention is shown in [Fig.l]. The turbomachine 1 extends around and along a longitudinal axis A.

[0058] In the present application, the terms "axial", "axially", "radial" and "radially" are defined with respect to the longitudinal axis A.

[0059] The terms “upstream” and “downstream” are defined in relation to the direction of circulation of the gases in the turbomachine 1 along the longitudinal axis A.

[0060] The terms “internal”, “interior”, “internally”, “external”, “exterior”, “externally” are defined in relation to the distance from the longitudinal axis A along an axis perpendicular to the longitudinal axis A.

[0061] The turbomachine 1 comprises from upstream to downstream in the direction of flow of the gases F along the longitudinal axis A, a fan 2, at least one compressor such as a low pressure compressor 3 and a high pressure compressor 4, a combustion chamber 5, at least one turbine 6 such as a high pressure turbine and a low pressure turbine, and a nozzle (not shown).

[0062] The rotor of the low pressure turbine is connected to the fan 2 and to the rotor of the low pressure compressor 3 by a low pressure shaft (not shown). The rotor of the high pressure turbine is connected to the rotor of the high pressure compressor 4 by a high pressure shaft (not shown).

[0063] The turbomachine 1 may further comprise a rectifier 10. The rectifier 10 makes it possible to straighten the flow at the outlet of a rotor located upstream in order to provide maximum thrust at the outlet of the turbomachine 1. In the particular example of [Fig.l], the rectifier 10 is located downstream of the fan 2 and makes it possible to straighten the secondary air flow F2.

[0064] The blower 2 allows the suction of an air flow dividing into a primary air flow F1 and a secondary air flow F2. The primary air flow F1 passes through a primary vein of the turbomachine 1 while the secondary air flow F2 is directed towards a secondary vein surrounding the primary vein.

[0065] The primary air flow F1 is compressed within the low-pressure compressor 3 and then the high-pressure compressor 4. The compressed air is then mixed with a fuel and burned within the combustion chamber 5. The gases formed by the combustion pass through the high-pressure turbine and the low-pressure turbine. The gases finally escape through the nozzle, the cross-section of which allows the acceleration of these gases to generate propulsion. The secondary air flow F2 passes through the rectifier 10, which accelerates the circulation speed of the secondary air flow F2 to generate propulsion.

[0066] The fan 2 and the rectifier 10 comprise vanes 11. The vanes 11 equipping the rectifier 10 are known by the English term “Outlet Guide Vane” (OGV). The vanes 11 are movable or fixed in rotation about the longitudinal axis A. Typically, the vanes 11 of the fan 11 are movable in rotation. They are mounted around a disc centered on the longitudinal axis A. The vanes 11 of the rectifier 10 are fixed.

[0067] The blades 11 extend radially relative to the longitudinal axis A. They are advantageously at a variable pitch angle. Such blades 11 are rotatable about their axes of elongation X.

[0068] With reference to [Fig.2], each blade 11 comprises a blade 12 and a root 14 secured to the blade 12.

[0069] The blade 12 extends along its elongation axis X. The elongation axis X of the blade 12 extends radially (or substantially radially, for example, with an angle of approximately 5° with the radial axis) relative to the longitudinal axis A of the turbomachine 1 after mounting the blade 11 on the turbomachine 1. The blade 12 has an aerodynamic profile. The blade 12 thus comprises an extrados face 12e and an intrados face connected by a leading edge 12a and a trailing edge 12b.

[0070] The blade 12 also extends longitudinally along the elongation axis X between an external end 13a and an internal end 13b opposite the external end 13a.

[0071] The blade 12 comprises a composite material. The composite material comprises a polymer matrix and a fibrous reinforcement embedded in the matrix. The composite material is for example an organic matrix composite (OMC). The matrix is ​​for example a thermoplastic or thermosetting polymer matrix. The thermosetting material is for example an epoxy polymer. The fibrous reinforcement comprises fibers which are for example carbon fibers or glass fibers. The fibers are organized for example in the form of a fiber preform. The fiber preform is for example 3D woven. The 3D weaving is for example of the interlock type.

[0072] The foot 14 comprises a sleeve 15 and a spar 16 secured to the sleeve 15 and the blade 12.

[0073] As best seen in [Fig. 3], the sleeve 15 has a generally tubular shape centered on the axis of elongation X of the blade 12. The sleeve 15 comprises a cylindrical body 15a extending between first and second axial ends 15b, 15c. Advantageously, the sleeve 15 comprises two annular end flanges 15d, 15e located at the first and second axial ends 15b, 15c. The end flanges 15d, 15e form, for example, rolling tracks for bearings allowing the blade 11 to rotate about its axis of elongation X. The sleeve 15 further comprises an internal passage 15f opening at the first and second axial ends 15b, 15c. In other words, the sleeve 15 is hollow.

[0074] The sleeve 15 comprises and advantageously consists of a metallic material. The metallic material is for example chosen from aluminum, stainless steels, titanium or even their alloys.

[0075] The sleeve 15 makes it possible to create the interface between the blade 12 and the disk. It thus constitutes a support for fixing the blade 11 to the disk. It also forms a support for rotation of the blade 11 around its elongation axis X.

[0076] With reference to [Fig. 4], the spar 16 extends along the elongation axis X between an outer end 16a and an inner end 16b. The spar 16 is received in the blade 12 and in the sleeve 15 and makes it possible to create the interface between the blade 12 and the sleeve 15. For this purpose, the outer end 16a of the spar 16 is housed in the blade 12 and the inner end 16b of the spar 16 is received in the inner housing 15d of the sleeve 15.

[0077] The spar 16 further has a lower surface face 16i located on the side of the lower surface face 12i of the blade 12 and an upper surface face 16e located on the side of the upper surface face 12e of the blade 12. The lower and upper surfaces 16i, 16e of the spar 16 are connected by first and second edges 16c, 16d extending along the elongation axis X.

[0078] The spar 16 comprises and preferably consists of a composite material. The composite material comprises a polymer matrix and a fibrous reinforcement embedded in the matrix. The composite material is, for example, an organic matrix composite (OMC). The matrix is, for example, a thermoplastic or thermosetting polymer matrix. The thermosetting material is, for example, an epoxy polymer. The fiber reinforcement comprises fibers that are, for example, carbon fibers or glass fibers. The fibers are organized, for example, in the form of a fiber preform. The fiber preform is, for example, 3D woven. The 3D weaving is, for example, of the interlock type. The composite material of the spar 16 is advantageously identical to the composite material of the blade 12.

[0079] The foot 14 is manufactured by a resin transfer molding process, also known by the English acronym RTM for “Resin Transfer Molding”. The resin transfer molding process may in particular be a vacuum-assisted resin transfer molding process, also known by the English acronym VA-RTM for “Vacuum Assisted Resin Transfer Molding”.

[0080] Resin transfer molding is carried out in a molding device 100 illustrated in [Fig. 5]. According to the invention, the device 100 comprises first and second molding blocks 101, 102 between which the sleeve 15 is axially located.

[0081] The first block 101 advantageously has a general polygonal shape, in particular rectangular. The first block 101 advantageously comprises a first face 103 opposite the second block 102 and a second opposite face 104. The first and second faces 103, 104 are located in a plane perpendicular to the elongation axis X of the sleeve 15. The first and second faces 103, 104 are connected together by lateral faces 105. These lateral faces 105 are located in a plane parallel to the elongation axis X of the sleeve 15.

[0082] With reference to [Fig. 6], advantageously, the first block 101 comprises a first part 106 and a second part 107 which are connected together. Each first and second part 106, 107 comprises an internal face 108 facing one another. The internal faces 108 together advantageously define an imprint of the spar 16. Advantageously, the internal faces 108 extend in a plane parallel to the elongation axis X of the sleeve 15.

[0083] The first and second parts 106, 107 are advantageously connected together by connecting members 109. The connecting members 109 are advantageously threaded rods which connect the first and second parts 106, 107 to each other. Preferably, four threaded rods connect the first and second parts 106, 107 to each other at their tops. Preferably, the threaded rods each have an axis perpendicular to the elongation axis X of the sleeve 15.

[0084] The first and second parts 106, 107 further comprise orifices 109a for receiving the connecting members 109.

[0085] With reference to Figures 7 and 8, the first block 101 further comprises an internal cavity 110. The fiber preform 16 is arranged in the internal cavity 110. The internal cavity 110 is for example defined between the first and second parts 106, 107 of the first block 101. It is for example delimited by the internal faces 108 of these first and second parts 106, 107.

[0086] Furthermore, the first block 101 comprises an annular interface 111. The interface 111 is centered on the elongation axis X of the sleeve 15. The interface 111 is provided on the first face 103 of the first block 101. The interface 111 is centered on the first face 103. It is hollow and advantageously opens into the internal cavity 110.

[0087] Advantageously, each first and second part 106, 107 has a semi-circular interface portion 111a, 111b centered on the elongation axis X and which cooperate together to form the annular interface 111.

[0088] With reference to [Fig. 10], the second block 102 advantageously has a generally polygonal shape, in particular parallelepipedal. The second block 102 advantageously comprises a first face 112 opposite the first block 101 and a second opposite face 113. The first and second faces 112, 113 are located in a plane perpendicular to the elongation axis X of the sleeve 15. They are parallel to the first and second faces 103, 104 of the first block 101. The first and second faces 112, 113 are connected together by lateral faces 114. These lateral faces 114 are located in a plane parallel to the elongation axis X of the sleeve 15.

[0089] Advantageously, the second block 102 comprises a first part 115 and a second part 116 which are connected together. The first and second parts 115, 116 are advantageously connected together by connecting members 117. The connecting members 117 are advantageously threaded rods which connect the first and second parts 115, 116 to each other. Preferably, between four and eight threaded rods connect the first and second parts 115, 116 to each other at their apexes. Preferably, the threaded rods each have an axis parallel to the elongation axis X of the sleeve 15.

[0090] The first and second parts 115, 116 further comprise orifices 117a for receiving the connecting members 117.

[0091] Furthermore, the second block 102 comprises an annular interface 118. The interface 118 is centered on the elongation axis X of the sleeve 15. The interface 118 is provided on the first face 112 of the second block 102. The interface 118 is centered on the first face 112. It is hollow. Advantageously, the interface 118 passes through the first part 116 and opens into the first part 116.

[0092] According to the invention, the second block 102 further comprises a channel 119 for the passage of resin. The channel 119 is for example formed in the first part 115 of the second block 102. It opens into the interface 118.

[0093] According to the invention, the device 100 further comprises a resin inlet port 120 and an outlet port 121. The inlet port 120 is provided in one of the first or second blocks 101, 102 and the outlet port 121 is provided in the other of the first or second blocks 101, 102.

[0094] Advantageously, the input port 120 is provided in the second block 102 and the output port 121 is provided in the first block 101.

[0095] The inlet port 120 is fluidically connected to the channel 119 of the second block 102. The inlet port 120 is for example arranged on one of the lateral faces 114 of the second block 102. It is for example arranged on the second part 116 of this second block 102. The inlet port 120 allows the injection of the resin.

[0096] The outlet port 121 is fluidically connected to the internal cavity 110. It is for example arranged on the second face 104 of the first block 101. It is in particular arranged on the first part 106 of the first block 101. The outlet port 121 allows the resin to flow out of the device 100. Advantageously, the outlet port 121 is a resin and air outlet port. It also allows a vacuum to be created in the first block 101. According to this embodiment, the device 100 comprises a pump connected to the outlet port 121 allowing a vacuum to be created in the first block 101.

[0097] The sleeve 15 is axially interposed between the first and second blocks 101, 102. The sleeve 15 is connected to the first block 101 by its first end 15b and to the second block 102 by its second end 15c.

[0098] In particular, the first end 15b of the sleeve 15 bears axially on the interface 111 of the first block 101 and the second end 15c of the sleeve 15 bears axially on the interface 118 of the second block 102. Advantageously, centering elements may be located on each of the interfaces 111, 118 in order to facilitate the positioning of the sleeve 15. These centering elements comprise, for example, centering lugs.

[0099] Furthermore, according to the invention, the internal passage 15f of the sleeve 15 is fluidically connected to the channel 119 of the second block 102 and to the cavity 110 of the first block 101, thus ensuring the circulation of the resin from the inlet port 120 to the outlet port 121, passing successively through the channel 119, the internal passage and the cavity 110.

[0100] In order to improve the sealing between the sleeve 15 and the first and second blocks 101, 102, a first sealing member (not shown) is arranged between the sleeve 15 and the first block 101, and a second sealing member (not shown) is arranged between the sleeve 15 and the second block 102. The first and second sealing members are preferably annular seals. Each annular seal is for example mounted respectively around the first and second end flanges 15d, 15e of the sleeve 15.

[0101] In order to further improve the sealing of the device 100, the device 100 further comprises clamping members 122 (visible in [Fig. 6]) which connect the first and second blocks 101, 102. The device 100 comprises for example between two and ten clamping members 122, and advantageously between four and eight clamping members 122. The clamping members 122 preferably comprise threaded rods which connect the first and second blocks 101, 102. The threaded rods are for example received in orifices 122a (shown in FIGS. 9 and 12) formed in each first and second block 101, 102. The threaded rods each have an axis parallel to the elongation axis X of the sleeve 15.

[0102] The clamping members 122 allow compression of the first and second blocks 101, 102 and of the sleeve 15, thus improving the sealing of the device 100. Furthermore, these clamping members 122 make it possible to ensure sealing of the device 100 even when the injection of resin is carried out at high pressures, for example between 1 bar and 30 bars, in particular between 15 bars and 20 bars.

[0103] The device 100 may comprise a heating system for increasing the temperature of the resin in order to achieve its polymerization. The heating system comprises, for example, a heating member arranged on the first block 101 and / or the second block 102 and / or the sleeve 15. According to another example, the heating system comprises an oven (not shown) in which the first and second blocks 101, 102 and the sleeve 15 are arranged.

[0104] To facilitate the demolding of the foot 14 and with reference to [Fig. 5], the device 100 may comprise extraction points 123 of the foot 14. The extraction points 123 comprise for example notches provided on the first and second blocks 101, 102. The notches are for example located on the lateral faces 105, 115 of the first and second blocks 101, 102. Each first and second block 101, 102 advantageously has between two and ten extraction points 123.

[0105] According to the invention, the sleeve 15 is an integral part of the molding device 100. Indeed, the sleeve 15 is positioned axially between the first and second blocks 101, 102 and is therefore located outside the cavity 110 for receiving the resin and the fiber preform 16. Thanks to such a position of the sleeve 15, and to its axial holding in a tight and sealed manner between these two blocks 101, 102, the risks of resin leaking outside the internal passage 15f of the sleeve 15 are limited. It is therefore no longer necessary to implement an additional step of removing resin from the sleeve 15, which makes it possible to preserve the mechanical properties of the sleeve 15 and to reduce the manufacturing time of the root 14 of the blade 11.

[0106] This sealing is further reinforced by the sealing members which further limit the risk of resin leakage. This sealing is also reinforced by the clamping members 122 which reinforce the axial compression of the sleeve 15 between the first and second blocks 101, 102.

[0107] Furthermore, the sleeve 15 being located outside the first and second blocks 101, 102 and therefore outside the cavity 110 for receiving the resin and the fiber preform 16, the risks of displacement of the sleeve 15 are limited, reducing the risks of misalignments between the sleeve 15 and the fiber preform 16.

[0108] A method of manufacturing the root 15 of the blade 11 will now be described with reference to [Fig. 13]. The manufacturing method comprises the following steps:

[0109] (a) inserting the fiber preform 16 into the internal passage 15f of the sleeve 15,

[0110] (b) arranging the fiber preform 16 in the first cavity 110 of the first block 101,

[0111] (c) axially connecting in a sealed manner the sleeve 15 to each of the first and second blocks 101, 102,

[0112] (d) injecting the resin through the inlet port 120, and

[0113] (e) discharging the resin through the outlet port 121.

[0114] Step (d) is advantageously carried out at a pressure of between 1 bar and 30 bars, preferably between 15 bars and 20 bars.

[0115] Before step (d), the method may comprise a following step (d'):

[0116] (d') evacuate the cavity 110.

[0117] After step (d), the method may comprise a following step (f):

[0118] (f) polymerizing the resin.

Claims

Claims

1. Molding device (100) for manufacturing a blade (11) root (14) for an aircraft turbomachine (1), the root (14) comprising a metal tubular sleeve (15) comprising an internal passage (15f) opening at the axial ends (15b, 15c) of the sleeve (15), and a spar (16) comprising a fiber preform embedded in a matrix and which axially passes through the internal passage (15f) of the sleeve (15), the device (100) comprising: - a first molding block (101) comprising a cavity (110) for receiving resin and at least a portion of the fiber preform, characterized in that the device (100) further comprises: - a second molding block (102) comprising a resin passage channel (119), the sleeve (15) being axially interposed between the first and second blocks (101, 102) and being held axially clamped in a sealed manner between the first and second blocks (101, 102), one of the first and second blocks (101,102) comprising at least one resin inlet port (120), and the other of the first and second blocks (101, 102) comprising at least one resin outlet port (121), the channel (119) and the cavity (110) being in fluid communication via the internal passage (15f) of the sleeve (15) so that the resin flows from the inlet port (120) to the outlet port (121) via the channel (119), the internal passage (15f) and the cavity (110).,

2. Molding device according to the preceding claim, characterized in that clamping members (122) connect the first and second blocks (101, 102).

3. Molding device according to the preceding claim, characterized in that the clamping members (122) comprise threaded rods.

4. Molding device according to the preceding claim, characterized in that the threaded rods pass through orifices (122a) formed in the first and second blocks (101, 102).

5. Molding device according to any one of the preceding claims, characterized in that each of the first and second blocks (101, 102) comprises a hollow annular interface (111, 118) on which one of the axial ends (15b, 15c) of the sleeve (15) is in axial support.

6. Molding device according to the preceding claim, characterized in that each interface (111, 118) is respectively provided in a face (103, 112) of the first and second blocks (101, 102).

7. A molding device according to any preceding claim, characterized in that a first sealing member is arranged between the sleeve (15) and the first block (101), and a second sealing member is arranged between the sleeve (15) and the second block (102).

8. Molding device according to the preceding claim, characterized in that the first and second sealing members each comprise an annular seal.

9. Molding device according to the preceding claim, characterized in that the first block (101) and / or the second block (102) comprises first and second parts (106, 107, 115, 116) connected together by connecting members (109, 116).

10. A method of manufacturing a blade (11) root (14) for an aircraft turbomachine (1), the root (14) comprising a metal tubular sleeve (15) comprising an internal passage (15f) opening at the axial ends (15b, 15c) of the sleeve (15), and a spar (16) comprising a fiber preform embedded in a matrix and which axially passes through the internal passage (15f) of the sleeve (15), characterized in that the method uses a molding device (100) according to any one of the preceding claims, the method comprising the following steps: (a) inserting the fiber preform into the internal passage (15f) of the sleeve (15), (b) arranging the fiber preform in the first cavity (110) of the first block (101), (c) arranging the sleeve (15) axially between the first and second blocks (101, 102) and connecting sealingly attaching the sleeve (15) to each of the first and second blocks (101, 102), (d) injecting the resin through the inlet port (120),and (e) discharging the resin through the outlet port (121).,

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