• 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 variable-pitch blade for compressor rectifier, the blade (10) having a blade (50) and at least one pivot (20; 21), the pivot (20; 21) having an internal element of pivot (40a, 40b; 41a, 41b) and a pivot cap (30; 31), the blade (50) and the inner pivot member (40a, 40b; 41a, 41b) being each made of a composite material, at least one contact surface (36, 39) of the pivot cap (30; 31) being metallic.
    公开号:FR3014964A1
    申请号:FR1362622
    申请日:2013-12-13
    公开日:2015-06-19
    发明作者:Stephane Pierre Roger Hennequin；Julien Prevost；Ziyad Karmy
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] TECHNICAL FIELD AND PRIOR ART The invention relates to a variable-pitch stator vane structure. Variable valve blades (English variable stator vane or VSV) have the distinction of being able to be operated. As their name suggests, their angle of incidence relative to the airflow from the upstream stage is changed during the different phases of flight. This angle of incidence is called the wedging angle. VSVs are highly stressed by their environment (pressure, temperature, mechanical stress, etc.). In these difficult conditions, the VSVs must be able to play at least two roles: - straighten the flow of air coming from the upstream stage: aeromechanical function to which the geometry of the blade responds; - Being able to pivot about the axis of wedging: mechanical function performed by means of a rotation guide and a drive system. From the prior art, all-metal variable pitch vanes are known. In general, it is desirable to reduce the mass of the components of an aircraft engine. The invention relates to a new variable-pitch blade architecture of reduced mass compared to a blade of the prior art. PRESENTATION OF THE INVENTION The variable-pitch blade according to the invention comprises a blade and at least one pivot, the pivot comprising an internal structural pivot element and a cap, the blade and the internal pivot structural element being each made in a composite material, at least one contact surface of the pivot cap, the cap being metallic. The invention thus advantageously makes it possible to manufacture the caps, the blade and the internal structural elements of the pivots separately so as to dissociate the manufacture of a complex shape into simpler processes. Thus, the manufacturing costs remain low, the overall mass of the blade remains low and each subcomponent can benefit from a material chosen with respect to its own manufacturing constraints.
    [0002] Thus, the structural parts of the rectifiers (blade and internal structural elements of the pivots) are made of composite materials, while the surfaces of the pivots in contact with the other parts of the engine are metallic. The invention therefore has the advantage of substantially reducing the total mass of the variable-pitch vanes (VSV) compared to the existing, while having metal contact surfaces, good friction properties, good strength and duration of optimal life. The reduction of mass thus makes it possible to reduce the consumption of the engine. In addition, the variable-pitch vanes of the prior art comprise a connection fillet between the blade and the pivot. The blade structure according to the invention makes it possible to overcome the presence of such a connection fillet in the turbomachine vein. In the absence of fillet between the blade and the pivots, the flow of the air flow is more laminar and thus improves the performance of the stator grid. The gain provided by this lack of connection radius is all the more visible on the small-sized blades where the ratio between the radius and the height of the aerodynamic profile is low. Indeed the scaling of this radius is not always feasible on a forged rectifier. The invention still has the advantage of being competitive in terms of manufacturing costs.
    [0003] Advantageously, the inner pivot member is assembled on a tab which is made in one piece and comes from material with the blade. Advantageously, the blade is made of a first composite material and the inner pivot element is made of a second composite material distinct from the first composite material.
    [0004] In a particularly advantageous embodiment, the first composite material is a long-fiber material, for example of 2D pre-impregnated or 3D woven type. In a particularly advantageous embodiment, the second composite material is a short fiber and organic matrix material. Advantageously, the cap is entirely metallic. Advantageously, the blade comprises an aerodynamic profile provided with an integrated leading edge. In an advantageous embodiment, the inner pivot member is assembled / glued to the tab. Alternatively, the internal pivot member is injected on the tab. The invention also relates to a method of manufacturing a variable pitch blade as described above, comprising the following steps: - assembly of the inner pivot member on a flange flange of the blade; - mounting the cap on the leg. In a particular embodiment, the internal pivot element is injected on the tab before mounting the cap on the tab. Alternatively, the inner pivot member is injected on the leg after mounting the cap on the leg. Alternatively, the inner pivot member is an insert and / or glued on the tab. The invention also relates to a turbomachine comprising a variable pitch blade as described above, the latter being movable in pivot connection with respect to a vein wall of the turbomachine. BRIEF DESCRIPTION OF THE DRAWINGS Embodiments of the invention will now be described, by way of nonlimiting examples, with reference to the accompanying drawings, in which: FIG. 1A is a perspective view of a dawn at variable setting according to the invention, comprising a blade, a lower pivot and an upper pivot; - Figure 1B is a bottom view of the upper pivot of Figure 1A, mounted on the upper part of the blade; - Figure 2 is a perspective view of a blade that comprises the blade of Figure 1A; FIGS. 3A and 3B are perspective views respectively of two internal structural elements of the upper pivot, and of two internal structural elements of the lower pivot; - Figures 4A and 4C are two views respectively in section and in perspective of a cap of the upper pivot; FIG. 4B is a perspective view of a cap of the lower pivot; - Figures 5A and 5B are two views of the upper part of the blade and internal structural elements of the upper pivot; - Figure 5C is a perspective view of the blade and internal structural members of pivot in an assembled state; - Figure 5D is a schematic cross-sectional view of the upper pivot in the assembled state and showing a variant of its internal structural elements. DETAILED DESCRIPTION OF PARTICULAR EMBODIMENTS FIG. 1A illustrates a variable pitch blade 10 of a turbomachine compressor stator. The blade 10 comprises a central part forming a blade 50 movable in pivot connection about a shimming axis XX with respect to a turbomachine stream wall. The blade 10 also comprises an upper pivot 20 and a lower pivot 21 rotated about the axis XX by an external control member. The blade 10 is designed to be disposed among other similar blades in a turbomachine vein in which it is subjected to the upstream-downstream air flow F. The terms 'upstream' and 'downstream' used subsequently mean relative to the flow of air through the turbomachine. The terms 'upper', 'lower', 'front' and 'rear' designate elements arranged respectively at the top, bottom, left and right in the figures accompanying the present application. The upper pivot 20 is shown from below in Figure 1B. The pivot 20 comprises a cap 30 and two inserts or internal structural members 40a and 40b whose structure and assembly will be described below, with reference to Figure 3A. FIG. 2 represents the blade 50, in the central part of the blade 10. The blade 50 comprises the aerodynamic profile 51 in the intermediate portion. An upper lug 52 and a lower lug 53 extend from the airfoil 51 extending from it. The lugs 52 and 53 are monobloc and are made of material with the airfoil 51. Advantageously, the blade 50 is made of long fiber composite material, for example but not limited to a two-dimensional prepreg (2D prepreg) or a woven in three dimensions (woven 3D).
    [0005] In the nonlimiting example shown, each lug 52 and 53 is traversed between two respective parallel surfaces by two orifices 54. The number of orifices 54 may differ from two, for example three or more. The blade here comprises two shoulders 57, each disposed in the upper part of the airfoil 51, in the extension thereof, upstream and downstream of the lug 52. In the non-limiting example shown, the profile aerodynamic 51 is provided on its leading edge 56 of a metal protective member 55. The latter 55 is here a metal plate folded on both sides of the front edge 56 extending from it on a given distance.
    [0006] FIG. 3A illustrates the two internal structural elements 40a and 40b of the pivot 20. In a first embodiment, the elements 40a and 40b are injected separately and then assembled on the upper lug 52. In this first embodiment, the elements 40a and 40b exist as detachable parts of the blade 50.
    [0007] The elements 40a and 40b are therefore shown in isolation from the blade 50 in FIG. 3A for a reason of readability. Here, the element 40a comprises a disk portion-shaped base 42a, and a tongue 44a connected to the base 42a by a fillet 48. Similarly, the element 40b includes a base 42b and a tongue 44b connected to the base 42b by leave. Linking pins 46 connect the tongue 44a to the tongue 44b. Here, the pins 46 are made of material with one of the elements 40a or 40b. Alternatively, without departing from the scope of the invention, other structures (for example the choice of draft angles) or other connecting members that the pins 46 are provided on or between the elements 40a and 40b and / or the blade 50 to prevent the dissociation of the elements 40a and 40b from the blade 50. As a non-limiting variant, the connecting pins 46 are metallic and allow the assembly of the two internal structural elements of the pivots during assembly.
    [0008] FIG. 3B illustrates two internal structural elements 41a and 41b of the lower pivot 21. In the first embodiment, the elements 41a and 41b are successively injected separately and then assembled on the lower lug 53. In this first embodiment, the elements 41a and 41b exist as detachable parts of the blade 50. The elements 41a and 41b are therefore shown separately from the blade 50 in Figure 3B for reasons of readability. In the example shown, these elements 41a and 41b are each in the form of disk portions. Linking pins 46 connect the elements 41a and 41b. The pins 46 are made of material with one of the elements 41a and 41b. As before, the connecting pins 46 may be metal and reported to the assembly. Alternatively, other structures (for example the choice of draft angles) or other connecting members that the pins 46 are provided to prevent the dissociation of the elements 41a and 41b from the blade 50 without leaving the frame of the invention. FIG. 5A illustrates the upper part of the blade 50 on which the element 40b is assembled by gluing on a first surface 520 of the lug 52. The connecting pins 46 pass through the orifices 54 and their respective end 460 is therefore projecting from the second surface 521 opposite to the first surface 520. FIG. 5B illustrates the same upper part of the blade 50 after a second step of bonding the complementary element 40a to the second surface 521, covering the projecting ends 460 of the pions 46. Finally, FIG. 5C illustrates the blade 50 as a whole after successive assembly of the internal elements 41a and 41b on the lower lug 53. Advantageously, the internal elements 40a, 40b, 41a and 41b are made of a compound-type material i.e. a short fiber material with an organic matrix. In a second embodiment, the internal elements 40a, 40b (respectively 41a and 41b) are injected simultaneously on the tab 52 (respectively the tab 53). The bases 42a and 42b and the shoulders 57 together form a foot 22, here disc-shaped. The tabs 44a and 44b and the tab 52 form a rod 23. The disk 22 and the rod 23 form here the internal structure or the body of the upper pivot 20. The rod 23 has in Figure 3 a cylindrical shape with a circular cross section. As a non-limiting variant, the section of the foot 22 and / or of the rod 23 may be different, for example polygonal and more particularly of square shape as illustrated in FIG. 5D. The elements 41a, 41b and the lower leg 53 form a foot 24, here disc-shaped. The disc 24 here forms the internal structure or the body of the lower pivot 21. The geometry of the internal pivot structures (that is to say the foot 22 and the rod 23 on the one hand, and the foot 24 of other hand) is chosen to prevent any dissociation between the elements 40a, 40b, 41a and 41b and the blade 50. The respective geometry of the elements 40a, 40b, 41a and 41b and the blade 50 is optimized so as to maximize the surface of the blade. bonding and / or distribution of efforts. FIG. 4A and FIG. 4C illustrate the cap 30 of the upper pivot 20.
    [0009] The cap 30 comprises a ring 32, a plate 33, a tubular portion 34 and a rod 35, joined in pairs in this order in the direction of the axis XX 'of the cap 30. The ring 32 and the plate 33 define together a housing 37 of complementary shape to the shape of the disk 22. The tubular portion 34 has an inner housing 38 communicating with the housing 37. The housing 38 is of complementary shape to that of the rod 23. Thus, the cap 30 is intended to cover the pivot body formed by the disc 22 and the rod 23. Here, two flats 36, for example parallel to each other, but not limited to, are provided on the cap 30 (see Figure 4C). These two flats 36 form metal contact surfaces for the external control member. The cap 30 is integral in rotation with the disk 22 and the rod 23 to allow the rotation of the blade 10 by the control member. Other rotation control structures of the blade 10 may be envisaged in unrepresented variants. A thread 39 is provided here on the outer surface of the rod 35 for a screw-nut connection with the control member. FIG. 4B illustrates the cap 31 of the lower pivot 21. The cap 31 comprises a ring 62, a plate 63 and a rod 65, joined in pairs in this order along the direction of the axis XX "of the cap 31. The 62 and the plate 63 together form a housing 67 of complementary shape to the shape of the disk 24. The cap 31 is thus intended to cover the pivot body formed by the disk 24. The cap 31 is integral in rotation with the disc 24 The caps 30 and 31 are here entirely metallic The metal of the caps is for example but not limited to titanium, steels or aluminum, the axes XX 'and XX "coincide with the general setting axis of dawn XX. The blade 10 comprising the elementary components described above is assembled according to a first manufacturing method described below in a nonlimiting manner.
    [0010] The blade 50, the internal structural elements 40a, 40b, 41a and 41b and the caps 30 and 31 are manufactured separately from each other then the internal elements 40a, 40b, 41a and 41b are assembled on the blade 50 by gluing and / or nesting. In a second manufacturing process, the two elements 40a and 40b or 41a and 41b of the same pivot body are injected simultaneously. In a third manufacturing method, for the upper pivot 20, a first element among 40a and 40b is injected on the lug 52, then the second. The same method applies for the lower pivot 21 with one then the other among the elements 41a and 41b. The injection order of the elements 40a, 40b, 41a and 41b is non-limiting.
    [0011] At the end of the first, second or third manufacturing process, the caps 30 and 31 are mounted on the appropriate pivot body 22 and 23 or 24 by gluing, by press fitting or by any other method. As an alternative to the second and third manufacturing methods, the internal structure of each pivot 20 or 21 can be directly injected in one piece into the appropriate cap 30 or 31 while the corresponding tab 52 or 53 is in place. For this purpose, it suffices to perform a molding operation from a configuration in which the cap and the blade are positioned in a suitable mold and to inject the internal structure material into the mold through a hole injection.20
    权利要求:
    Claims (14)
    [0001]
    CLAIMS1 Variable-pitch blade for a compressor rectifier, the blade (10) having a blade (50) and at least one pivot (20; 21), the pivot (20; 21) having an internal pivot member (40a, 40b) 41a, 41b) and a pivot cap (30; 31), the blade (50) and the inner pivot member (40a, 40b; 41a, 41b) being each made of a composite material, at least one surface of contact (36, 39) of the pivot cap (30; 31) being metallic.
    [0002]
    2. blade according to claim 1, the inner pivot member (40a, 40b; 41a, 41b) being assembled on a tab (52; 53), the tab (52; 53) being made in one piece and coming from a material with the blade (50).
    [0003]
    3. variable-pitch blade according to one of claims 1 or 2, the blade (50) being made of a first composite material, the inner pivot member (40a, 40b; 41a, 41b) being made of a second material composite distinct from the first composite material.
    [0004]
    4. blade according to claim 3, the first composite material being a long-fiber material, for example of 2D prepreg type or woven 3D.
    [0005]
    5. blade according to one of claims 3 or 4, the second composite material being a short fiber material and organic matrix.
    [0006]
    6. blade according to one of claims 1 to 5, the pivot cap (30; 31) being entirely metallic.
    [0007]
    7. blade according to one of claims 1 to 6, the blade (50) having an airfoil (51) provided with an integrated leading edge (55).
    [0008]
    8. blade according to one of claims 1 to 7, in combination with claim 2, the inner pivot member (40a, 40b; 41a, 41b) being injected on the tab (52; 53).
    [0009]
    9. blade according to one of claims 1 to 7, in combination with claim 2, the inner pivot member (40a, 40b; 41a, 41b) being bonded to the tab (52; 53).
    [0010]
    10. A method of manufacturing a variable-pitch blade according to one of claims 1 to 9, comprising the following steps: - assembly of the inner pivot member (40a, 40b; 41a, 41b) on a tab (52); 53) of the blade (50); - Mounting the cap (30; 31) on the leg (52; 53).
    [0011]
    11. Manufacturing method according to claim 10, the inner pivot member (40a, 40b; 41a, 41b) being injected onto the tab (52; 53) before mounting the cap (30; 31) on the tab. (52; 53).
    [0012]
    12. Manufacturing method according to claim 10, the inner pivot member (40a, 40b; 41a, 41b) being injected onto the tab (52; 53) after mounting the cap (30; 31) on the tab (52; 53). 25
    [0013]
    13. Manufacturing method according to claim 10, the inner pivot member (40a, 40b; 41a, 41b) being an insert insert and / or glued on the tab (52; 53).
    [0014]
    14. A turbomachine comprising a variable pitch blade according to one of claims 1 to 9, the blade being movable in pivot connection relative to a vein wall of the turbomachine.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3014964B1|2018-09-28|
    US10024186B2|2018-07-17|
    GB2522770A|2015-08-05|
    GB2522770B|2020-06-17|
    US20150167490A1|2015-06-18|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5392514A|1992-02-06|1995-02-28|United Technologies Corporation|Method of manufacturing a composite blade with a reinforced leading edge|
    EP1215365A1|2000-12-12|2002-06-19|Snecma Moteurs|Adjustable guide vane and method of production therefor|
    DE10323132A1|2003-05-22|2004-12-16|Mtu Aero Engines Gmbh|Adjustable guide vane for gas turbines, has adjustable turbine blade, made from fiber-reinforced synthetic material e.g. carbon fiber, with portions fixed in between parts of corresponding bearing journals|
    FR2897639A1|2006-02-23|2007-08-24|Snecma Sa|Air inlet`s guiding vane angular position controlling device for e.g. jet engine of airplane, has clamping bolt to fix rod end on pivot, of vane, rotating inside smooth bearing, made of alumina/zirconia, passing over turbomachine body|
    FR2933955A1|2008-07-18|2010-01-22|Snecma|DEVICE FOR ATTACHING A VARIABLE SHIFT BLADE|
    DE4237031C1|1992-11-03|1994-02-10|Mtu Muenchen Gmbh|Adjustable guide vane|
    US7753653B2|2007-01-12|2010-07-13|General Electric Company|Composite inlet guide vane|
    EP2196629B1|2008-12-11|2018-05-16|Safran Aero Boosters SA|Segmented composite shroud ring of an axial compressor|
    EP2472063B1|2010-12-30|2015-02-11|Techspace Aero S.A.|Vane made of a composite material|
    US9228438B2|2012-12-18|2016-01-05|United Technologies Corporation|Variable vane having body formed of first material and trunnion formed of second material|ES2797733T3|2016-03-16|2020-12-03|MTU Aero Engines AG|Adjustable guide vane for turbine, turbine and manufacturing method|
    US10273976B2|2017-02-03|2019-04-30|General Electric Company|Actively morphable vane|
    WO2018181939A1|2017-03-30|2018-10-04|三菱日立パワーシステムズ株式会社|Variable stator blade, and compressor|
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    法律状态:
    2015-12-17| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-09| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362622|2013-12-13|
    FR1362622A|FR3014964B1|2013-12-13|2013-12-13|VARIABLE TIMING RECTIFIER IN COMPOSITE MATERIALS|FR1362622A| FR3014964B1|2013-12-13|2013-12-13|VARIABLE TIMING RECTIFIER IN COMPOSITE MATERIALS|
    US14/566,889| US10024186B2|2013-12-13|2014-12-11|Variable pitch guide vane made of composite materials|
    GB1422166.7A| GB2522770B|2013-12-13|2014-12-12|Variable pitch guide vane made of composite materials|
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