• 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 platform (10) of composite material with integrated joints for a turbomachine blower, the platform comprising a base (12) and a stiffener (14), the method comprising three-dimensional weaving of a one-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to the longitudinal direction of the base of the platform, forming of the fiber blank to form a fiber preform having a first base preform portion and a second stiffener preform portion, positioning platform seals (20) at lateral ends of the first portion of the fiber preform forming basic preform, placement of the fibrous preform with seals in an injection mold, injection of resin into the injection mold, compaction of the assembly, heating fage injection mold to solidify the resin, and demolding the platform obtained.
    公开号:FR3018473A1
    申请号:FR1452167
    申请日:2014-03-17
    公开日:2015-09-18
    发明作者:Yann Didier Simon Marchal；Bruno Jacques Gerard Dambrine
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of manufacture of blade platforms made of composite material with integrated joints for a turbomachine blower. The turbine engine fan blade platforms, in particular the turbojet engine, are arranged between the blades of the fan in the extension of the inlet cone thereof. They allow in particular to delimit, on the inner side, the annular air intake duct in the blower, this duct being delimited on the outer side by a casing. These blower blade platforms can be reported separately or integrated directly into the duct. the base of the fan blades, between the stilt extending them and the blade thereof.
    [0002] The realization of such platforms in composite material has already been proposed. For example, reference may be made to document WO 2013/088041, which describes the production of a n-section fiber preform, in particular for a fan blade platform of composite material, from a fibrous structure obtained by weaving. three-dimensional one-piece with a base preform portion and another stiffener leg portion. Document WO 2013/104852 also discloses a method of manufacturing a fan blade made of composite material in which the platforms are integrated. In this document, the fan blade is made from a fibrous preform obtained by three-dimensional weaving in one piece with a blade preform portion and another platform preform portion. Furthermore, it is known to equip the blades of gas blower blades to ensure a seal between the platforms and the blades between which they are arranged. The presence of such joints is intended to limit aerodynamic performance losses associated with air recirculation. Typically, such joints are glued to each lateral end of the platform by means of an adhesive film extending the entire length of the platform. However, the bonding of these joints is a complicated operation that requires a significant amount of time. In addition, the joints tend to peel off quickly. OBJECT AND SUMMARY OF THE INVENTION There is therefore a need to be able to have a fan blade platform of composite material that does not have the aforementioned disadvantages relating to seals. According to the invention, this object is achieved by a method of manufacturing a blade platform of composite material with integrated joints for a turbomachine blower, the platform comprising a base extending in a longitudinal direction. and having two opposite faces and a stiffener extending from a face of the base, the method comprising: three-dimensional weaving of a one-piece fibrous blank with a plurality of longitudinal yarn layers extending into a direction corresponding to the longitudinal direction of the base of the platform and interconnected by threads of a plurality of transverse son layers by providing between two layers of longitudinal threads two main open loops which each extend from a side edge of the fiber blank and which are intended to form a stiffener preform; shaping the fiber blank to form a fiber preform having a first base preform portion and a second stiffener leg preform portion; positioning platform seals at lateral ends of the first portion of the basic preform fiber preform; placing the fibrous preform with the seals in an injection mold; injection of resin into the injection mold; compaction of the whole; heating the injection mold to solidify the resin; and the demolding of the platform obtained. The manufacturing method according to the invention is remarkable in that the seals are directly integrated with the fiber preform before the injection step with a resin. At the time of this manufacturing step, the preform is indeed flexible enough to nest the joints. After injection, the joints are found directly attached to the platform. The use of glue with the disadvantages that this entails is particularly avoided.
    [0003] According to one embodiment, the step of three-dimensional weaving of the fibrous blank further comprises the production of closed secondary delimitations at the lateral ends of a portion of the fibrous blank intended to form the base preform, the secondary delimitations being open and the seals inserted inside them prior to the placement step of the fiber preform in the injection mold. In this embodiment, the opening of each secondary debonding may comprise cutting the part of the fibrous blank intended to form a base preform according to a cutting plane opening inside said secondary delimitation. In this case, the cutting plane is preferably previously identified on the fiber blank. Still in this embodiment, the seals may each comprise a fastener portion which is inserted longitudinally within the secondary delimitations once opened. In another embodiment, the seams are sewn together at the lateral ends of the first portion of the preform fiber preform prior to the step of placing the fiber preform in the injection mold.
    [0004] In this embodiment, carbon threads may be used to assemble the seals on the lateral ends of the first portion of the basic preform fiber preform. In yet another embodiment, the seals are placed in the injection mold at the lateral ends of the first portion of the basic preform fiber preform without mechanical connection therewith. The stiffener of the platform may comprise two legs. It may further comprise a stiffening wall connecting the legs at a free end. The subject of the invention is also a blade platform of composite material for a turbine engine with integrated joints obtained by a method as defined. previously.
    [0005] BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will emerge from the description given below, with reference to the accompanying drawings which illustrate embodiments having no limiting character. In the figures: FIG. 1 is a schematic view showing a fan blade platform of composite material obtained by the method according to a first embodiment of the invention; - Figure 2 is a sectional view along II-II of Figure 1; FIGS. 3 and 4 show different steps of the method of obtaining the blade platform of FIGS. 1 and 2; and FIGS. 5 and 6 are diagrammatic views of a fan blade platform of composite material according to a second embodiment of the invention. DETAILED DESCRIPTION OF THE INVENTION FIGS. 1 and 2 show a turbine engine fan platform 10 to which the invention applies in particular. The platform 10 comprises a first portion forming a base 12 and a second stiffener portion 14. The base extends 25 in a longitudinal direction of the platform with an opposite upper face 12a and a lower face 12b. This base comprises at each of its longitudinal ends a step 16, that is to say that these ends are bent inwardly along substantially transverse lines. These steps 16 make it possible to secure the platform on the structure of the turbomachine. The stiffener 14 of the platform comprises two legs 18 (or legs) which extend from the inner face 12b of the base along its entire length. These legs make it possible to stiffen the platform so as to prevent any displacement thereof under the centrifugal force due to the speed of rotation of the fan.
    [0006] The platform 10 thus formed has a t-shaped section as shown in dashed lines in FIG. 1. In a variant shown in dotted lines in FIG. 2, the stiffener 14 of the platform may further comprise a stiffening wall 19 interconnecting the legs 18 at their free end so as to form a closed box under the base 12 of the platform. Furthermore, in order to ensure a seal with the blades positioned on either side of the platform, the latter is equipped with seals 20 which are assembled on each lateral end of its base 12 and which extend between the longitudinal ends of it. As shown more precisely in FIG. 2, the seals 20 have an attachment part 20a on the platform and a flexible part 20b which is intended to bear against the adjacent blade. Typically, these seals 20 are made of an elastomeric material. FIG. 3 very schematically represents a weft plane of a fiber blank 100 from which a fibrous platform preform can be shaped, before resin injection or densification by a matrix and possible machining, in order to obtain According to a first embodiment of the invention, the composite material blower platform 10 illustrated in FIGS. 1 and 2. The fiber blank 100 comprises two opposite outer 100a and inner 100b faces between which extend 9 layers of chain yarns c1 to cg and 9 layers of weft yarns t1 to tg with a double cross between the yarns of weft yarn group t2 to t6 and yarns of weft yarn group t7 to t9 in two crossing areas 102a, 102b. Two main open loosings 104a, 104b materialized by solid lines in FIG. 1 are formed between the layers of adjacent threads c6 and c7, these main delimitations extending in lateral portions of the fibrous blank between the lateral edges 100c and 100d thereof at which they open and crossing areas 102a, 102b. These main delimitations 104a, 104b result in the absence of weft threads passing through them to bind together the warp yarns of the warp yarn layers located on either side of the main tie-offs.
    [0007] Reference can be made to the international patent application WO 2013/088041 which describes in detail the realization by three-dimensional weaving of such a fiber blank 100 with its main delimitations 104a, 104b.
    [0008] The fibrous blank 100 further comprises two secondary closed delimitations 106a, 106b also materialized by solid lines in FIG. 1. These secondary delimitations 106a, 106b extend in the lateral parts of the fibrous blank and are formed between the layers of neighboring son c3 and c4.
    [0009] These secondary delimitations 106a, 106b are said to be "closed" as opposed to the main delimitations 104a, 104b which are said to be "open" in that, unlike the latter, they do not open at a lateral edge 100c, 100d of the fibrous blank.
    [0010] As for the main delimitations, the secondary delimitations 106a, 106b result in the absence of weft threads passing through them to bind together warp son son layers of son located on either side of the secondary delimitations. After weaving the fibrous blank 100, it is shaped to form a fibrous preform 200 of the fan platform as shown in FIG. 4. In particular, the portions 108, 110 of the Fibrous blank adjacent to the main delimitations 104a, 104b and inner face 100b are expanded to form two legs 202, 204 of the preform 200, the remainder of the fiber blank forming the base 206 of the preform. The shaping step of the fibrous blank 100 also consists of opening the secondary delimitations 106a, 106b. For this purpose, the portion of the fibrous blank which is intended to form the base preform 206 (here between the layers of yarns c1 and c6) is partly cut in the direction of the thickness along P section planes. , P 'opening into said secondary delimitations. More specifically, cutting planes P, P 'are previously marked on the fiber blank during weaving thereof, for example by insertion of tracer son 112a, 112b (Figure 3) or any other pattern on the surface of the portion of the fibrous blank intended to form base preform, these tracer son being positioned opposite the secondary delimitations 106a, 106b. With the aid of a cutting tool, a cut is then made in the thickness of the fibrous blank 100 at the level of the tracer strands from the surface of the part of the fibrous blank intended to form a basic preform. until unblocking in the secondary delimitations 106a, 106b (the cut is made here between the layers c6 and C4). Once the secondary delimitations 106a, 106b are open, the seals 20 (Figure 1) can be inserted therein. More precisely, the fastening portion 20a of the seals 20 is positioned inside the secondary delimitations 106a, 106b of the fibrous preform 200. The fiber preform 200 with its seals is then placed in an injection mold (not shown in FIG. the figures) which is closed by a counter-mold before injecting liquid resin (for example epoxide, bismaleimide or polyimide). The assembly (platform preform provided with seals) is then compacted inside the injection mold and the resin is solidified by heating the latter. After demolding, the platform is machined to its final dimensions. This results in a blower platform with integrated joints. The injection process used here is well known per se and is therefore not described in detail. In particular, it is possible to use a process of RTM ("resin transfer molding") type (resin transfer molding). In the embodiment previously described, the number of layers of warp and weft threads in the different parts of the preform (base and legs) may of course be different from those of the illustrated example, provided that three-dimensional weaving is performed in each of these parts. Similarly, in this embodiment, warp and weft can be reversed. Furthermore, in the case of a platform provided under its base with a closed box, reference may be made to the document WO 2013/160584 which describes an embodiment of a fibrous blank making it possible to obtain such a box. platform. The creation of secondary delimitations and their opening for the insertion of seals as previously described applies identically to this type of fibrous blank.
    [0011] In connection with Figures 5 and 6, there will be described a second embodiment of the integrated joint blower platform according to the invention. This second embodiment differs from the first mode 5 previously described in that the seals 20 'are mechanically bonded to the fiber preform 200' of the platform by stitching. More specifically, the integrated joint blower platform is obtained from a fibrous preform 200 'as shown in FIGS. 5 and 6. This fibrous preform 200' is obtained from a fibrous preform similar to that described with reference to FIG. 3, except for secondary delimitations which are not present here. The fibrous blank is shaped identically to the previous embodiment, in particular by unfolding the portions of the blank adjacent to the main tie-offs 104'a, 104'b and the inner face to form the two legs 202 ' , 204 'of the preform 200', the remainder of the fiber blank forming the base 206 'of the preform. At this stage, the seals 20 'are positioned at the lateral ends of the base preform 206, and then sewn directly onto these ends, for example by means of a plurality of carbon threads 208 longitudinally spaced apart from each other. others over the entire length of the preform. Once the joints 20 'are assembled, the various steps of the previously described manufacturing method are repeated, namely that the assembly is placed in an injection mold which is closed by a counter mold before injecting the mold. resin. The assembly is then compacted inside the injection mold, then the resin is solidified by heating the latter. After demolding, the platform is machined to its final dimensions. This results in a blower platform with integrated joints.
    [0012] According to a third embodiment of the integrated joint blower platform according to the invention (not shown in the figures), it is intended to carry out a direct coking of the fibrous preform of the platform and its joints. without previously mechanically bonding or sewing the joints to the fiber preform.
    [0013] For this purpose, once the fiber preform has been obtained (identical to that described in connection with the second embodiment), it is placed directly in the injection mold. The seals are positioned in the same injection mold at the lateral ends of the base preform, then the mold is closed by a counter-mold before injecting the resin. The steps of the manufacturing process of the two previous embodiments are repeated to finally obtain a platform on which the joints are attached in particular thanks to the solidified resin. According to a provision common to all the embodiments of the method according to the invention, the fan platform of composite material may be of the type integrated with a fan blade. In this alternative embodiment, the fan blade is made from a fibrous preform obtained by three-dimensional weaving in one piece with a blade preform portion and another platform preform portion. Reference can be made to WO 2013/104852 which describes such a manufacturing method. It will be understood that it will suffice then to apply the teachings of the present invention to the production of the part of the preform fiber preform platform. It will also be appreciated that the elastomeric material used for making the joints of the platform will be able to withstand the temperature during injection of the resin into the preform. For example, a silicone elastomer may be used.
    权利要求:
    Claims (12)
    [0001]
    REVENDICATIONS1. A method of manufacturing a blade platform (10) of composite material with integrated joints for a turbomachine blower, the platform comprising a base (12) extending in a longitudinal direction and having two opposite faces (12a 12b) and a stiffener (14) extending from one side of the base, the method comprising: three-dimensional weaving of a one-piece fiber blank (100) with a plurality of longitudinal yarn layers extending in a direction corresponding to the longitudinal direction of the base of the platform and interconnected by threads of a plurality of transverse yarn layers by providing between two longitudinal yarn layers two open main loosings (104a, 104b) which each extend from a side edge (100c, 100d) of the fiber blank and which are intended to form a stiffener preform; shaping the fibrous blank to form a fibrous preform (200) having a first base preform portion (206; 206 ') and a second preform portion (202,204; 202', 204 ') of stiffener; positioning platform seals (20; 20 ') at lateral ends of the first portion of the basic preform fiber preform; Placing the fibrous preform with the seals in an injection mold; injection of resin into the injection mold; compaction of the whole; heating the injection mold to solidify the resin; and demolding the resulting platform.
    [0002]
    The method of claim 1, wherein the step of three-dimensional weaving of the fibrous blank further comprises providing closed secondary delimitations (106a, 106b) at the lateral ends of a portion of the fibrous blank for forming the base preform, the secondary delimitations being open and the seals inserted therein prior to the step of placing the fibrous preform in the injection mold.
    [0003]
    3. The method of claim 2, wherein the opening of each secondary debonding comprises cutting the portion of the fibrous blank to form a base preform along a cutting plane (P, P ') leading to the interior of said secondary delimitations.
    [0004]
    4. The method of claim 3, wherein the cutting plane is previously marked on the fiber blank.
    [0005]
    5. A method according to any one of claims 2 to 4, wherein the seals (20) each comprise an attachment portion (20a) which is inserted longitudinally within the secondary delimitations 15 once open.
    [0006]
    The method of claim 1, wherein the seams are seam-bonded to the lateral ends of the first portion of the preform fiber preform prior to the step of placing the fiber preform in the injection mold. .
    [0007]
    The method of claim 6, wherein carbon yarns (208) are used to assemble the seals on the lateral ends of the first portion of the basic preform fiber preform.
    [0008]
    The method of claim 1, wherein the seals are placed in the injection mold at the lateral ends of the first portion of the base preform fiber preform without mechanical connection therewith.
    [0009]
    9. Method according to any one of claims 1 to 8, wherein the seals are made of elastomer.
    [0010]
    The method of any one of claims 1 to 9, wherein the stiffener (14) of the platform comprises two legs (18).
    [0011]
    The method of claim 10, wherein the stiffener of the platform further comprises a stiffening wall (19) connecting the legs at a free end.
    [0012]
    12. Composite material blade platform (10) for an integrated joint turbine engine blower obtained by a method according to any one of claims 1 to 11.
    类似技术:
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    同族专利:
    公开号 | 公开日
    WO2015140442A1|2015-09-24|
    FR3018473B1|2016-04-08|
    US10293530B2|2019-05-21|
    US20180117807A1|2018-05-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2010066833A1|2008-12-12|2010-06-17|Snecma|Seal for a platform in the rotor of a turbine engine|
    WO2010103213A1|2009-03-09|2010-09-16|Snecma|Turbine ring assembly|
    WO2012156625A1|2011-05-13|2012-11-22|Herakles|Composite turbomachine blade with in-built root|
    WO2013088041A2|2011-12-14|2013-06-20|Snecma|Fibrous preform having a π-shaped cross-section, in particular for a composite material blower platform|
    WO2013104853A2|2012-01-09|2013-07-18|Snecma|Pi-section reinforcing piece made of composite material, notably turbomachine fan platform, and method of manufacturing same|
    WO2013160584A1|2012-04-26|2013-10-31|Snecma|Fibrous blank woven in one piece by three-dimensional weaving for producing a platform with a closed box structure for a turbomachine fan made of composite material|WO2020260810A1|2019-06-26|2020-12-30|Safran Aircraft Engines|Inter-blade platform with a sacrificial box section|
    WO2021176160A1|2020-03-03|2021-09-10|Safran Aircraft Engines|Method for manufacturing a composite platform for an aircraft turbine engine fan|
    CN113459540A|2021-06-25|2021-10-01|成都飞机工业（集团）有限责任公司|Forming device and forming method for slender part with closed angle|FR2949091B1|2009-08-17|2015-06-26|Snecma|METHOD FOR PRODUCING A HOLLOW MONOBLOCK HOLLOW DISC|
    US9771810B2|2012-01-09|2017-09-26|Snecma|Fiber preform for a turbine engine blade made of composite material and having an integrated platform, and a method of making it|US11028714B2|2018-07-16|2021-06-08|Raytheon Technologies Corporation|Fan platform wedge seal|
    法律状态:
    2015-03-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-03-14| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1452167A|FR3018473B1|2014-03-17|2014-03-17|METHOD FOR MANUFACTURING A CAMERA PLATFORM IN COMPOSITE MATERIAL WITH INTEGRATED JOINTS FOR TURBOMACHINE BLOWER|FR1452167A| FR3018473B1|2014-03-17|2014-03-17|METHOD FOR MANUFACTURING A CAMERA PLATFORM IN COMPOSITE MATERIAL WITH INTEGRATED JOINTS FOR TURBOMACHINE BLOWER|
    PCT/FR2015/050543| WO2015140442A1|2014-03-17|2015-03-05|Method for manufacturing a blade platform in composite material with in-built seals for a turbo machine fan|
    US15/126,982| US10293530B2|2014-03-17|2015-03-05|Method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan|
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