• 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 turbomachine blade from a preform (10) made of composite material polymerized in a mold comprising a lower part (16) and an upper part, comprising at least one closure step at during which the upper part of said mold is brought to the lower part (16) of the mold containing the preform (10). The method comprises, prior to said closing step, at least one substep of insertion in the preform (10) of a marker (28) of position, and at least one substep of control of the position of the marker (28) relative to a mark (30) of the mold (18).
    公开号:FR3029134A1
    申请号:FR1461819
    申请日:2014-12-02
    公开日:2016-06-03
    发明作者:Marc-Emmanuel Techer；Nicolas Ashtari
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The field of the present invention is that of the manufacture of gas turbine engines, such as turbomachines, and in particular those intended for the propulsion of aircraft. The present invention more particularly relates to a method of manufacturing a turbomachine blade of composite material, a preform for forming the blade of the turbomachine, and a mold for carrying out such a method. A turbomachine blade typically has a foot and a blade, the foot having oblique lateral faces connected to the blade and intended to form bearing surfaces in a mounting cell of a rotor disc. The dawn is generally made of lightweight materials in order to participate in the lightening of the turbomachine and to limit the inertia of the rotor of which it is part. A turbine engine blade is also subjected to particularly important stresses at the level of his foot, particularly at the bearing surfaces. Indeed, the forces exerted on the air flow by the blade, in the radially outer zone thereof, creates high stresses at its attachment zone, that is to say in the foot of the blade. 'dawn. This leads to using a material both light and resistant for the manufacture of dawn. A known solution to these constraints is to use a composite material. It is thus known to make a blade using a preform formed by weaving fibers, said fibers being compacted and embedded in a thermosetting resin matrix. The fibers thus provide the function of mechanical reinforcement, the resin matrix to ensure the holding of the blade. Document EP-A1-1.526.285, in the name of the Applicant, describes a process for manufacturing a preform by three-dimensional weaving of fibers, in particular of carbon fibers. The preform thus obtained comprises a foot portion and a blade portion, connected by oblique lateral faces intended to form bearing surfaces of the foot in a mounting cell of a rotor disc. As described in EP-A1-1.777.063, also in the name of the Applicant, the preform is then placed in a mold whose footprint comprises a foot zone and a blade zone, which are connected to one another. to the other by oblique lateral faces corresponding to the aforementioned lateral faces of the preform. The relaxation of the fibers after weaving of the preform generates a swelling thereof, also known as the phenomenon of expansion. The preform then has dimensions greater than the dimensions of the part to be produced. The preform is first compacted in a mold having a lower portion and an upper portion. To do this, the preform is disposed in the lower part of the mold, then the mold is closed by bringing the upper part of the mold to the lower part, transversely to the longitudinal axis of the blade, and axially the foot of the preform using a movable part of the mold which is interposed between the lower and upper parts. The role of this mobile part is to force the fibers of the foot of the preform to press against the oblique faces of the mold. Then a partial vacuum is made in the mold and a thermosetting resin is injected into the mold so as to impregnate the entire preform.
    [0002] The preform and the resin are then heated to polymerize - and thus cure - the resin. The fibers are then held in position by the resin matrix and the assembly forms a blade which is both light and rigid. The plating of the fibers of the preform against the oblique lateral faces of the mold makes it possible to limit the hollows at its zones intended to form the bearing surfaces of the foot in a mounting cell of a rotor disc.
    [0003] The existence of numerous cavities indeed generates, after injection of the resin, clusters or pockets of resin which, alone, have low mechanical strengths. The bearing surfaces being areas subject to high stresses, it is necessary to limit the appearance of such clusters or pockets of resin, which is obtained by soliciting the foot of the preform using the moving part of the mold. However, it has been found that another source of defects is the positioning of the fabric preform in the lower part of the mold.
    [0004] Indeed, the positioning of this tissue preform in the injection mold is delicate but essential. However, the closure of the upper part of the mold is likely to apply a force on the preform that may tend to move in the mold and to move in the wrong position. Therefore, the preform may locally no longer be pressed against the walls of the mold, and therefore the surface of the blade may have, after injection of the resin, clusters or pockets of resin corresponding to areas not having been occupied by weaving.
    [0005] The mechanical strength of these zones is less than that normally required for such a blade, and for this reason the presence of such clusters or pockets of resin must absolutely be avoided.
    [0006] In fact, an inadequate positioning of the fabric of the preform can be observed only after injection and demoulding of the part. No repair procedure is possible and the part must be scrapped.
    [0007] The invention overcomes this disadvantage by proposing a manufacturing method for determining the position of the preform in the mold to avoid any error positioning. Thus, the invention proposes a method for manufacturing a turbomachine blade of composite material comprising: a first step of producing a preform of axial general orientation, by three-dimensional weaving of yarns, said preform comprising a blade root portion and a blade blade portion; - a second step of placing the preform in a lower portion of a mold, a footprint of which is substantially complementary to lower portions of the foot portion; blade and vane blade portion of the preform; - a third mold closing step of feeding an upper portion of said mold, a footprint of which is complementary to upper portions of the blade root portion; and the blade blade part of the preform, on the lower part of the mold containing the preform, - a fourth step of compacting the preform in said mold, and - a fifth injection step vacuum molding of a resin in the mold to impregnate the compacted preform and form a rigid blade after polymerization of the resin. According to the invention, this method is characterized in that it comprises during the first step, at least one insertion sub-step in the preform of a position marker, and during the second step, at least one substep of controlling the position of the marker with respect to a marker of the mold. According to other features of the method: during the control sub-step, the control of the position of the marker is optically performed; during the control sub-step, the control of the position of the marker; is performed visually by an operator. the method comprises, during the second step, prior to the control substep, a substep of mounting in the mold of a marker insert, the position of said insert being unambiguously defined with respect to the lower part of the mold, the control substep comprises at least the visual measurement of the position of the marker relative to a wall of the insert along the longitudinal general direction of the preform of the blade, this wall determining the reference of the mold.
    [0008] The invention also provides a blade preform obtained by three-dimensional weaving of yarns, said preform comprising a blade root portion and a blade blade portion.
    [0009] According to the invention, this blade preform is characterized in that it comprises a position marker inserted into the weave of said preform. According to other features of the preform: - said position marker is inserted in an area of the blade root part of the preform intended to be the subject of a cutting operation for obtaining the dawn finite, - the marker is a different color wire than the son used for weaving the preform, - the marker is a fiberglass or Kevlar thread, in the weaving of the son of the preform that are fiber of carbon.
    [0010] Finally, the invention proposes an impregnating mold for the manufacture of a blade made of composite material for a turbomachine, comprising a lower mold part of which a substantially longitudinal orientation impression is substantially complementary to a lower part of a preform. blade, and an upper portion of which an imprint of substantially longitudinal orientation is substantially complementary to an upper portion of the blade preform, said upper portion being adapted to be attached to said lower portion.
    [0011] According to the invention, this mold is characterized in that it comprises at least one insert which is intended to be fixed by a first end in a unambiguous position relative to the lower part of the mold and which is intended to extend substantially longitudinally above the footprint of the lower part of the mold. This insert comprises at least one opposite second end comprising at least one transverse wall capable of forming a mark when the upper part of the mold is not attached to said lower mold part, and it is able to be entirely received in a complementary cavity an upper portion of the mold when said upper portion is attached to said lower portion, flush within the cavity of said upper portion, to define a portion of said fingerprint of said upper portion. The invention will be better understood and other details, characteristics and advantages of the present invention will appear more clearly on reading the following description given by way of non-limiting example and with reference to the accompanying drawings, in which: Figure 1 is a schematic sectional view representative of the third step of closing a mold of a molding process according to a prior art; FIG. 2 is a schematic view of a preform in its state at the end of the sub-step of inserting a marker in said preform according to the method of the invention; FIG. 3 is a diagrammatic sectional view representative of the substep of controlling the position of the marker with respect to a marker of the mold according to the method of the invention; - Figure 4 is a schematic sectional view representative of the third step of closing the mold according to the method of the invention.
    [0012] In the following description, like reference numerals designate like parts or having similar functions.
    [0013] In known manner, a method of manufacturing a turbomachine blade of composite material comprises a first step in which is made by weaving in three dimensions of son (not shown), a preform 10, as shown in Figure 2 Such a preform 10 has an axial general orientation, corresponding to the horizontal direction of the figures. The preform 10 is made by one-piece weave, generally made of carbon fibers, and it essentially comprises a blade root portion 12 intended to ensure the fixing of the finished blade to a rotor disk. turbomachine, and a blade blade portion 14 for cooperating with a flow of air or gas within the turbomachine. In a second step of such a process, the preform 10 is placed in a lower part 16 of a mold 18 such as that shown in FIG. 1. The lower part 16 has an imprint 20 which is substantially complementary to a lower portion 21 of the preform, that is to say of the lower portions of the blade root portion 12 and the blade blade portion 14 of the preform 10.
    [0014] The mold 18 comprises an upper part 22 which is attached to the lower part 16 during a third step of closing the mold 18. This upper part 22 has a cavity 24 which is complementary to an upper part 23 of the preform 10 , that is to say, upper parts of the blade root portion 12 and the blade blade portion 14 of the preform 10. The closure of the mold 18 delimits a complete cavity, consisting of 20 and imprint 24, which allows the injection of resin into the preform 10. Then the method comprises a fourth step of compacting the preform 10 in said mold 18. During this step, as illustrated FIG. 1 generally exerts a force on one end 26 of the foot 12 of the preform, so as to compact the fibers in contact with the walls of the imprints 20 and 24, as indicated by the arrows of FIG. 1.
    [0015] Then, during a fifth injection step, a resin is injected under vacuum into the mold 18 in order to impregnate the compacted preform 10, which makes it possible to form a rigid blade after polymerization of the resin.
    [0016] Finally, during a sixth finishing step, the polymerized raw preform 10 is demolded and then cut to separate falls, in order to obtain the final dawn. In particular, significant falls are arranged at the free end 26 of the foot 12.
    [0017] It has been found that correct positioning of the fabric preform in the cavity 20 of the lower portion 16 of the mold 18 is an indispensable condition for obtaining a finished blade having optimum strength characteristics. Indeed, incorrect positioning of the fabric preform in the lower part of the mold 18 may cause the preform 10 to be no longer pressed against the walls of the mold 18, and thus the surface of the blade may have, after injection of the resin, clusters or pockets of resin corresponding to the areas that have not been occupied by the weaving.
    [0018] However, incorrect positioning is not necessarily visible when the preform 10 is disposed in the cavity 20 in the lower part 16 of the mold 18 by the operator. Indeed, an incorrect but non-visible positioning can cause, during the closing of the mold 18, the appearance of forces exerted by the upper portion 22 of the mold 18 on the preform 10 which tend to cause its movement in the mold before the resin injection. It is therefore when the upper part 22 of the mold 18 is folded down on the lower part 16 that the preform 10 is most likely to move, without this movement being apprehended by the operator.
    [0019] The invention overcomes this disadvantage by proposing a manufacturing method for controlling the positioning of the preform 10 in the mold 18. For this purpose, the invention proposes a method of the type described above characterized in that it comprises during of the first step, at least one substep of insertion into the preform 10 of a position marker 28, and then during the second step, at least one substep of controlling the position of the marker 28 relative to at a mark 30 of the mold 18, as shown in FIG.
    [0020] To implement this method, it is necessary to use a preform of the type that has been shown in FIG. 2. The preform 10 is a preform conventionally comprising a blade root portion 12 and a portion of a blade blade. blade 14, obtained in one piece by three-dimensional weaving son, for example carbon son. According to the invention, the preform 10 comprises a position marker 28 which is inserted into the weave of said preform 10 during its manufacture. The insertion of the marker 28 at this stage makes it possible to avoid a subsequent operation of insertion of the marker 28, an operation which could damage the weaving of the preform 10, and secondly enables said marker 28 to be included in the weaving the preform, so that it does not protrude and the preform 10 does not have any roughness that would likely interfere with its contact with the walls of the mold.
    [0021] Preferably, the position marker is inserted into the blade root part 12 of the preform, and more particularly in an area 29 of this foot portion 12 which is intended to be the subject of a cutting operation. the result of the release of the cured dawn, to constitute a fall not participating in the functional characteristics of the dawn.
    [0022] This configuration thus makes it possible to guarantee that the insertion of the marker 28 has no consequences on the mechanical strength of the finished blade. As can be seen in Figure 2, the line 32 in dotted lines represents the limit of this cut. The marker 28 is preferably placed close to this cutting line 32. Advantageously, a simple embodiment of the marker 28 consists in using, for its production, a colored yarn different from that of the yarns used for weaving the preform 10. inserted on the weave of the preform 10. This on the one hand makes it possible to ensure homogeneity of the weave and on the other hand to form an optical pattern on the surface of the preform 10. For example, the marker is a thread 28 in fiberglass or possibly in Kevlar.
    [0023] It will thus be understood that, during the control substep, the control of the position of the marker 28 is performed optically, that is to say the marker 28 is intended to form a pattern whose presence, absence or position relative to the fixed reference 30 of the mold 28, is detectable by any method involving the reflection of light rays on the surface of the marker 28.
    [0024] Thus, in the preferred embodiment of the invention, during the control sub-step, the control of the position of the marker 28 is performed very visually by an operator.
    [0025] To do this, during the second step, prior to the control sub-step, the method comprises a substep of mounting in the mold of an insert 34 forming a marker, the position of said insert 34 being defined uniquely relative to the lower part 16 of the mold 18. For example, as illustrated in FIG. 3, the insert 34 has a first end 36 through which it is fixed by means of a connecting means 38, such as a screw or a tie rod, at the lower part 16 of the mold 18. For example, in a nonlimiting manner of the invention, the insert 34 is fixed on an upper face 40 of the lower part 16 of the mold 18. insert 34 is fixed in a unambiguous position relative to the lower part 16 of the mold 18, so that its position is known and invariable.
    [0026] The insert 34 can be fixed to the lower part 16 of the mold 18 after the introduction of the preform 10 in the lower part of the mold 18, or alternatively, the insert can be put in place and the preform 10 is introduced. under the insert 34.
    [0027] The insert 34 extends substantially longitudinally above the cavity 20 of the lower part 16 of the mold 18. The insert comprises at least one opposite second end 42 comprising the mark 30. This end 42 comprising at least one transverse wall 30 suitable for forming a reference mark as long as the upper part 22 of the mold 18, shown in FIG. 4, is not attached to said lower part 16 of the mold 18.
    [0028] To perform the sub-step of controlling the position of the marker 28 with respect to the marker 30 of the mold 18, an operator can for example position his eye in the direction of the arrow "R" and note the position of the marker 28.
    [0029] In this case, several measurement methods can be envisaged according to the positioning tolerances of the marker 28. According to a design involving strict positioning, it is considered that the position of the marker 28 is correct only in the case of its alignment with the marker. transverse wall 30 of the insert 32. In this case, any deviation of the marker 28 with this position, especially when it deviates from the wall 30, to the right of Figure 3 or disappears under the insert 34, to the left of Figure 3, is synonymous with incorrect positioning.
    [0030] It will be noted that according to this design, the transverse wall 30 of the insert could advantageously be replaced by a vertical well or a lumen (not shown) formed in a longer insert 34, a correct position of the marker 28 then corresponding to the alignment of this well or this light with the marker 28. In this case, it is the absence of the marker 28 in front of this well or this light which stigmatizes the positioning defect of the preform 10. According to a design involving a positioning in a determined range of values, it is considered that the position of the marker 28 is correct within a given range of values. The operator is then in charge of measuring the distance between the marker 28 and the wall 30 and to determine if this position, along the longitudinal general direction of the preform of the blade, falls within the range of values corresponding to a correct positioning. of the preform.
    [0031] It will be understood that according to other designs, the control of the position of the marker 28 can be performed optically and assisted, or even automated, but not directly visual.
    [0032] Thus, it is also possible to control the strict positioning of the marker 32 by means of a monochromatic or laser beam of light emitted in the direction "R" or in a transverse plane containing the direction "R", the reflection of the beam on the marker 28 and the capture of the reflected beam corresponding to a correct positioning of the marker 28 and therefore to a correct positioning of the preform 10, while inversely the absorption of the beam by the carbon fibers of the preform 10 corresponds to a incorrect positioning of the preform 10. Similarly, it is possible to perform an optical measurement using a camera placed in the direction "R", whose image is processed by an appropriate algorithm to determine, according to the tolerances envisaged, if the position of the marker 28 is strictly respected or if it is part of a determined range of values associated with the validation of the positioning of the preform.
    [0033] More generally, it will be understood that any optical or visual measurement method may be suitable for implementing the sub-step of controlling the position of the marker 28 with respect to the wall 30 forming the marker of the mold 18.
    [0034] As has been seen, during a third mold closing step, an upper portion 22 of said mold 18 is reported on the lower part 16 of the mold 18 containing the preform 10.
    [0035] Advantageously, the insert 34 is able to be entirely received in a cavity 44 complementary to the upper part 22 of the mold 18 when said upper part 18 is attached to the lower part 16. The insert 34 is then flush with the inside of the cavity 24 of the upper part 22, to define a part of said cavity 24.
    [0036] This configuration makes it possible to avoid dismantling the insert 34, an operation which on the one hand would be time-consuming and unnecessary, and on the other hand could cause movement of the preform 10 in the lower part 16 of the mold 18.
    [0037] The invention therefore proposes a particularly simple and advantageous method which makes it possible to control any unwanted displacements of a woven preform in a mold 18 during a molding process of a blade by resin injection, and consequently to limit defects that could lead to dawn scrapping. Given the high polymerization time of such a blade, the use of this method, by drastically reducing the number of blades discarded, significantly increases the production of turbomachine blades. 20
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A process for manufacturing a turbomachine blade of composite material comprising: a first step of producing a preform (10) of axial general orientation, by three-dimensional weaving of yarns, said preform comprising a portion (12) of foot blade and a portion (14) of blade blade, a second step of placing the preform (10) in a lower portion (16) of a mold (18), including an imprint (20) is substantially complementary to lower portions of the blade root portion (12) and the blade blade portion (14) of the preform (10), a third mold closing step (18) of reporting a upper portion (22) of said mold, an indentation (24) of which is complementary to upper portions of the blade root portion (12) and the blade blade portion (14) of the preform (10), on the lower part (16) of the mold (18) containing the preform (10), a fourth step of compacting the preform (10) in said mold (18), and 20 - a fifth step of vacuum injection into the mold (18) of a resin to impregnate the compacted preform (10) and form a rigid blade after polymerization of the resin, characterized in that it comprises: during the first step, at least one insertion sub-step in the preform (10) of a marker (28) of position, during the second step, at least one substep of controlling the position of the marker (28) relative to a mark (30) of the mold (18).
    [0002]
    2. Manufacturing method according to the preceding claim, characterized in that, during the control sub-step, the control of the position of the marker (28) is performed optically.
    [0003]
    3. Manufacturing method according to the preceding claim, characterized in that, during the control sub-step, the control of the position of the marker (28) is visually performed by an operator.
    [0004]
    4. Manufacturing process according to the preceding claim, characterized in that it comprises, during the second step, prior to the substep control, a substep of mounting in the mold (18) of an insert (34) forming a marker, the position of said insert (34) being uniquely defined with respect to the lower portion (16) of the mold (18).
    [0005]
    5. Manufacturing process according to the preceding claim, characterized in that the control sub-step comprises at least the visual measurement of the position of the marker (28) relative to a wall of the insert (34) in the general direction longitudinal of the preform (10) of the blade, this wall determining the mark (30) of the mold.
    [0006]
    6. blade preform (10) obtained by weaving three-dimensional son, said preform comprising a portion (12) of blade root and a portion (14) of blade blade, characterized in that it comprises a position marker (28) inserted into the weave of said preform.
    [0007]
    The blade preform (10) according to claim 6, characterized in that said position marker (28) is inserted in a zone (29) of the part (12) of the blade root of the preform (10). intended to be the subject of a cutting operation for obtaining the finished blade.
    [0008]
    8. blade preform (10) according to claim 6 or 7, characterized in that the marker (28) is a different color wire than the son used for weaving the preform (10).
    [0009]
    9. blade preform (10) according to one of claims 6 to 8, characterized in that the marker is a fiberglass wire or Kevlar in the weaving of the son of the preform which are carbon fiber .
    [0010]
    10. Impregnation mold (18) for the manufacture of a blade of composite material for a turbomachine, comprising a lower portion (16) of mold, an imprint (20) of substantially longitudinal orientation is substantially complementary to a portion lower part (21) of a blade preform (10), and an upper part (22) of which an impression (24) of substantially longitudinal orientation is substantially complementary to an upper part (23) of the preform (10). blade, said upper portion (22) being adapted to be attached to said lower portion (16), characterized in that it comprises at least one insert (34) which is intended to be fixed by a first end (36) in a unambiguous position relative to the lower part (16) of the mold (18), and which is intended to extend substantially longitudinally above the cavity (20) of the lower part (16) of the mold (185). ), and: - which has at least one second extrem an opposite side (42) having at least one transverse wall (30) capable of forming a mark when the upper part (22) of the mold (18) is not attached to said lower mold part (16), which is suitable to be entirely received in a cavity (44) complementary to an upper portion (22) of the mold when said upper portion (22) is attached to said lower portion (16), flush with the interior of the cavity (24); ) of said upper portion (22) to define a portion of said fingerprint (24) of said upper portion (22).
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    引用文献:
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    FR3100739A1|2019-09-12|2021-03-19|Safran Aircraft Engines|RESIN INJECTOR FOR THE MANUFACTURE OF A COMPOSITE PART, IN PARTICULAR FOR AN AIRCRAFT ENGINE|
    FR3101570A1|2019-10-07|2021-04-09|Safran|COMPOSITE PART MANUFACTURING PLANT, IN PARTICULAR FOR AN AIRCRAFT ENGINE|
    WO2021105612A1|2019-11-29|2021-06-03|Safran|Process for manufacturing a composite blade for an aircraft engine|
    WO2021105600A1|2019-11-29|2021-06-03|Safran|Composite blade for an aircraft engine, and processes of manufacturing and repairing same|
    FR3105076A1|2019-12-23|2021-06-25|Safran Aircraft Engines|PROCESS FOR MANUFACTURING A CASING FOR AN AIRCRAFT TURBOMACHINE|
    WO2021255368A1|2020-06-18|2021-12-23|Safran Aircraft Engines|Method for manufacturing a composite part for a turbomachine|FR2861143B1|2003-10-20|2006-01-20|Snecma Moteurs|TURBOMACHINE BLADE, IN PARTICULAR BLADE OF BLOWER AND METHOD OF MANUFACTURING THE SAME|
    FR2892339B1|2005-10-21|2009-08-21|Snecma Sa|PROCESS FOR MANUFACTURING A COMPOSITE TURBOMACHINE BLADE, AND BLADE OBTAINED BY THIS PROCESS|
    FR2950286B1|2009-09-24|2013-08-09|Snecma|PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE OF COMPOSITE MATERIAL|
    BR112014018031B1|2012-01-25|2020-12-01|Safran|process and tool for making a propeller blade|
    FR3026980B1|2014-10-10|2017-03-31|Snecma|METHOD FOR IMMOBILIZING A PREFORM IN A MOLD|FR3096375B1|2019-05-21|2021-04-30|Safran Ceram|Fibrous texture comprising a marking thread and its method of obtaining|
    EP3854560A1|2020-01-27|2021-07-28|Siemens Gamesa Renewable Energy A/S|Method for fabricating a wind turbine shell, wind turbine blade, wind turbine and method for repair of a wind turbine blade shell|
    法律状态:
    2015-12-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-06-03| PLSC| Publication of the preliminary search report|Effective date: 20160603 |
    2016-12-09| PLFP| Fee payment|Year of fee payment: 3 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 4 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-11-27| PLFP| Fee payment|Year of fee payment: 5 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 6 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1461819A|FR3029134B1|2014-12-02|2014-12-02|METHOD FOR CONTROLLING THE POSITION OF A TURBOMACHINE COMPOSITE BLADE PREFORM IN A MOLD|FR1461819A| FR3029134B1|2014-12-02|2014-12-02|METHOD FOR CONTROLLING THE POSITION OF A TURBOMACHINE COMPOSITE BLADE PREFORM IN A MOLD|
    JP2017528926A| JP6701193B2|2014-12-02|2015-11-24|How to check the preform position in the mold|
    CN201580064817.8A| CN107000340B|2014-12-02|2015-11-24|Method for checking the position of a preform in a mould|
    PCT/FR2015/053201| WO2016087747A1|2014-12-02|2015-11-24|Method for checking the position of a preform in a mould|
    US15/531,714| US10864689B2|2014-12-02|2015-11-24|Method for checking the position of a preform in a mould|
    EP15808729.6A| EP3227076A1|2014-12-02|2015-11-24|Method for checking the position of a preform in a mould|
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