• 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:
    Rectifier for a turbomachine, comprising an annular body (12) having an axis defining an axial direction, a radial direction and an azimuthal direction, at least a first blade (20) and a second blade azimutally adjacent to the first blade (20), each blade (20) being fixed to the annular body (12) by a main attachment (24), and a platform (40) located between the first blade (20) and the second blade (30). The platform (40) is attached to the first blade by a first auxiliary attachment (26) separate from the main attachment (24).
    公开号:FR3032753A1
    申请号:FR1551254
    申请日:2015-02-16
    公开日:2016-08-19
    发明作者:Virginie Guilbert；Xavier Durand；Lise Lacroix
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present disclosure relates to a rectifier for a turbomachine and a turbomachine equipped with such a rectifier. It will be recalled that a turbomachine designates any gas turbine apparatus producing a motive power, among which are distinguished in particular turbojet engines providing a thrust necessary for propulsion by reaction to the high speed ejection of hot gases, and turbine engines in which motive power is provided by the rotation of a motor shaft. For example, turboshaft engines are used as the engine for helicopters, ships, trains, or as an industrial engine. Turboprops (turbine engine driving a propeller) are also turboshaft engines used as aircraft engines. Recall also that a rectifier is a device for rectifying the flow of air passing through the turbomachine in the direction of flow. BACKGROUND ART Document FR 2 958 980 describes an example of a known rectifier, comprising an annular body, vanes fixed on the annular body and a platform disposed between each pair of adjacent vanes. Such a rectifier is generally heavy, which penalizes the performance of the turbomachine. There is therefore a need for a rectifier for lighter turbomachine. PRESENTATION OF THE INVENTION One embodiment relates to a rectifier for a turbomachine, comprising an annular body having an axis defining an axial direction, a radial direction and an azimuthal direction, at least a first blade and a second blade azimutally adjacent to the axis. first blade, each blade being fixed to the annular body, and a platform located between the first blade and the second blade, characterized in that each blade is fixed to the annular body by at least one main attachment and the platform is fixed on the first blade by a first auxiliary attachment distinct from the main attachment. The annular body is a tubular piece, which may be cylindrical, frustoconical or of any shape. Most often, the annular body 5 is of generally symmetrical shape. The annular body has an axis. The axial direction corresponds to the direction of the axis of the annular body and a radial direction is a direction perpendicular to the axis of the annular body and intersecting this axis. An azimuthal direction (also referred to as tangential or circumferential) is a direction perpendicular to a radial direction and not intersecting the axis of the annular body. Similarly, an axial plane is a plane containing the axis of the annular body and a radial plane is a plane perpendicular to this axis. Unless stated otherwise, the front and rear adjectives are used with reference to the axial direction, it being understood that the rectifier input is located on the front side of the rectifier while its output is on the back side. Finally, unless otherwise stated, the adjectives inner, inner, outer and outer are used with reference to a radial direction so that the inner (respectively inner) part of an element is, in a radial direction, closer to the axis of the annular body as the outer (respectively external) part of the same element. The platform is a separate part of the blades; the platform and the first dawn do not form a single room. In particular, the platform can be removably mounted on the first blade. It is therefore understood that the platform is not integrated, welded or the like. The platform is fixed on the first dawn. Thus, there is no direct connection between the platform and the annular body. In other words, the platform is linked to the annular body via dawn. The platform is therefore fixed only on one or more blades. It is understood that each blade may be fixed on the annular body by its own main attachment, or that a group of vanes may be fixed on the annular body by a single main attachment, or that all the vanes can be fixed on the annular body by a single main attachment. In the case where the rectifier comprises several main fasteners, the auxiliary fastening is distinct from all the main fasteners.
    [0002] The first dawn and the second dawn are azimutally adjacent, which means there is no other dawn between the two. However, other elements may be located between two adjacent blades, for example the platform. Subsequently, unless explicitly stated otherwise or contextual, the description elements provided about a blade in general can be applied to both the first blade and the second blade. This remark also applies to the first and second main and auxiliary fasteners. Thanks to the proposed rectifier, the assembly and disassembly of the platform are made independent of the assembly and disassembly of the blades. In addition, the use of an auxiliary fastening separate from the main fastening makes it possible to make independent the tightening torques applied to the fixing of the blade on the annular body (main attachment) and to the fixing of the platform on the dawn (auxiliary fixation). Indeed, the blade is highly mechanically stressed and needs to be securely fixed on the annular body, while the platform is comparatively little stressed and can be fixed less tightly on the blade. Decorrelating the tightening torques makes it possible to apply a lower tightening torque to the auxiliary fastener without compromising the good resistance of the blade to the annular body. Consequently, it is possible to reduce the thickness of the platform or to use a less dense material for the platform without damaging the platform during its assembly by applying too much tightening torque. This results in a lightening of the rectifier without compromising the mechanical strength of the various components. In addition, the platforms of such a rectifier are easily removable in situ, "under the wing", that is to say without removing the turbine engine of the aircraft on which it is fixed. In some embodiments, the platform is secured to the second blade by a second auxiliary attachment separate from the main attachment. This allows a better attachment of the platform and a better distribution of the stresses induced on the blades. In the case where the rectifier comprises several main fasteners, in particular one per blade, the second auxiliary fastener is distinct from all the main fasteners.
    [0003] In some embodiments, the second auxiliary fastener is identical or analogous to the first auxiliary fastener. This allows a simplification of the rectifier and a reduction in production costs. In some embodiments, the first auxiliary fastener 20 and / or the second auxiliary fastener is accessible on the side of the platform radially opposite to the annular body. Thus, the auxiliary attachment is particularly easy to access, which simplifies the assembly and disassembly of the platform. In these embodiments, the term "accessible" means that there is direct access to the portion that allows the auxiliary mount to be mounted or removed. The accessible side may allow tools to be brought near the auxiliary attachment for assembly or disassembly purposes. In some embodiments, the first and second vanes are attached to the annular body at their radially inner end.
    [0004] In these embodiments, the annular body is therefore a radially internal body, sometimes called a hub by the person skilled in the art although it is fixed. The inner ends of the blades being closer to each other than the outer ends, there is little space on the annular body to attach the platform. The proposed solution is therefore all the more advantageous in the sense that the auxiliary attachment is not placed on the annular body. In some embodiments, each blade includes a profile and a fastener portion at one end of the profile, the platform being attached to the fastening portion of the profile side and the fastening portion attached to the annular body. on the side of the attachment portion radially opposite the profile. Thus, in succession in a radial direction, the rectifier comprises the annular body, the attachment portion and the platform. The attachment portion is preferably formed by the root of blade 15 (radially inner end), but may also be formed by the head of the blade (radially outer end). The face of the platform radially opposite to the annular body, which is on the side of the profile, and the profiles of the first and second blades thus define a space in which is air.
    [0005] In some embodiments, the platform has a density less than the density of the first blade. For example, the platform may be plastic, while the blade may be of composite material or metal. In particular, the platform may have a density (or density) less than or equal to 1500 kg / m3, preferably less than or equal to 1350 kg / m3. It is thus understood that the platform may be in a material different from the material of the blades, which is made possible by the decoupling of torques or clamping forces between the main fasteners and the auxiliary fasteners. The first and second blades 30 may be made of the same material.
    [0006] In some embodiments, the first blade and / or the second blade is a composite material. In some embodiments, the first auxiliary attachment and / or the second auxiliary attachment includes a floating nut. A floating nut 5 is a fastening system comprising for example a cage and a threaded barrel retained by the cage and mounted to move relative to the cage. A floating nut makes it possible to adjust the position of the threaded drum, for example along three axes. In some embodiments, the platform includes support pads configured to rest on the first blade and / or the second blade. In these embodiments, the sloshing of the platform, subjected to a flow of air, is minimized. The present disclosure also relates to a turbomachine comprising a rectifier according to any one of the previously described embodiments. BRIEF DESCRIPTION OF THE DRAWINGS The invention and its advantages will be better understood on reading the following detailed description of embodiments of the invention given as non-limiting examples. This description refers to the appended drawings, in which: FIG. 1 represents a schematic view in partial section of a turbomachine; FIG. 2 is an exploded perspective view of a rectifier sector according to one embodiment; Figures 3A and 3B are perspective views, respectively of the outer side and the inner side, of a platform according to one embodiment; - Figure 4 is a sectional view of a portion of the rectifier of Figure 2; Figure 5 shows a detail of Figure 4; Figure 6 is a perspective diagram of a floating nut; - Figure 7 schematically shows a blade root configured for fixing a platform according to one embodiment of the invention.
    [0007] DETAILED DESCRIPTION OF THE INVENTION The overall architecture of a turbomachine that can incorporate an embodiment of the invention will be described with reference to Figure 1, which has an axial half-section of a turbomachine 100. Upstream the turbomachine 100 comprises a fan 200 for the air intake. At the outlet of the fan 200, the air flow separates in two. A first portion of the air flow is sent into a low-pressure compressor 300 and then a high-pressure compressor 400. This first portion of the air flow is then injected into a combustion chamber 500, at the exit of which it drives a turbine. 600. A second part of the air stream, at the outlet of the fan 200, is sent into a rectifier 10 to be rectified and then mixed with the gases leaving the turbine 600. The second part of the air flow can be used, in part, the cooling of the turbomachine 100. More particularly, the rectifier 10 comprises a set of 20 blades or blades 20 arranged radially between an inner annular body 12 and an outer annular body 14. These blades 20 are sometimes called guide vanes. Outlet Guide (OGV). In the present embodiment, the blades 20 are made of composite material. In the remainder of the present description, the attachment of the vanes to the inner annular body 12 will be detailed, but the description which follows may apply analogously, mutatis mutandis, to the outer annular body 14. The rectifier 10 has an axis X which is here confused with the axis of the turbomachine. The X axis defines the axial direction.
    [0008] Figure 2 shows in perspective a portion of the rectifier 10 according to one embodiment of the invention. In the present case, there is shown a first blade 20 and a second blade 30 azimutally adjacent to the first blade 20. The first and second blades 20, 30 follow one another in an azimuthal direction. Each blade 20, 30 is intended to be fixed to the annular body 12 by a main attachment. To do this, in the present embodiment, each blade 20, 30 has respective orifices 22, 32. The orifices 22, 32 are able to receive a main attachment, which will be described later, to fix the blades 20, 30. to the annular body 12. As indicated above, the rectifier 10 comprises at least one platform 40, here a plurality of platforms 40. In particular, the rectifier 10 comprises a platform 40 located between the first blade 20 and the second blade 30. As one as can be seen in FIG. 2, the face of the platform 40 radially opposite the annular body 12 and the profiles of the first and second blades 20, 30 are configured to define, when assembled, an air passage P. To do this, the edges of the platform 40 can match the shape of the portion of the adjacent blades 20, 30 between which said platform 40 is located. In the present embodiment, the platform 40 is made of plastic, for example polyetherimide resin and / or thermoplastic and / or amorphous, loaded or not, for example Ultem resin (polyetherimide resin comprising 25% short carbon fibers). ). The density of the platform is of the order of 1350 kg / m3, which allows a relief of the rectifier 10 compared to a composite platform (about 1500 kg / m3) or metal (aluminum: about 2800 kg / m3 ), without constraint on the respective tightening torques of the first main attachment and the first auxiliary attachment.
    [0009] 303 2 7 5 3 9 The platform 40 is intended to be fixed to the first blade 20 and the second blade 30. The remainder of this presentation focuses more particularly on the first blade 20 but the description that follows may apply in the same way at the second dawn 30.
    [0010] The platform 40 is shown in perspective in FIGS. 3A and 3B, respectively showing opposite faces of the platform. The faces shown in FIGS. 3A and 3B are opposed radially with respect to each other when the platform 40 is mounted on the rectifier. The face shown in Fig. 3A is configured to face the air passage, while the face shown in Fig. 3B is configured to face the annular body 12. As shown in Fig. 3A, the platform 40 comprises holes 42, here two holes 42. In this embodiment, the holes 42 are intended to accommodate an auxiliary attachment to secure the platform 40 to a blade. The holes 42 here are through holes, the walls of the holes 42 being provided with a bore. As illustrated in FIG. 3B, the platform 40 further comprises support pads 44, here two support pads 44. In this case, the support pads 44 take the form of non-emerging hollow cylinders. Thanks to the support pads 44, the platform 40 is configured to bear on the blades 20, 30. This allows in particular to limit its sloshing. The assembly of the rectifier 10 is shown in FIG. 4, which is a sectional view along a plane passing through the centers of the two holes 42. As illustrated in FIG. 4, the first blade 20 is fixed to the annular body 12 by a first main attachment 24. In this case, the first main attachment 24 cooperates with the orifices 22. In addition, in this example, the first blade 20 comprises a fastening portion and a profile extending radially from the attachment portion. The attachment portion is formed by a blade root 21. The first blade 20 is attached to the annular body 12 at its foot 21, i.e., its radially inner portion. As shown in FIGS. 2 and 4, the annular body 12 here has a substantially U-shaped axial section. The first blade 20 is fixed to each branch of the U formed by the annular body (see FIG. 4), ie - say at the front and back of the annular body. In addition, the platform 40 is fixed to the first blade by a first auxiliary attachment 26. As can be seen in FIG. 4, the first auxiliary attachment 26 is distinct from the first main attachment 24. In this embodiment, the platform is fixed to the foot 21 of the first blade 20. This location of the auxiliary attachment 26 makes it possible not to disturb the aerodynamic characteristics of the profile of the blade 20. The auxiliary attachment 26 is shown in detail in FIG.
    [0011] On the one hand, in the assembled position, the walls of the hole 42 rest on the blade 20, particularly on the blade root 21. On the other hand, the hole 42 is arranged in alignment with an orifice 28 provided in the blade 20, here in the blade root 21, so that it can engage the auxiliary attachment 26.
    [0012] The auxiliary attachment 26 comprises, in this embodiment, a floating nut 34 and a screw 38. The fixed part of the floating nut 34, an embodiment of which will be described in more detail with reference to FIG. 6, is riveted to the blade root 21 by rivets 36. The floating nut 34 is positioned so that its opening is aligned with the orifice 28 of the blade root 25. The screw 38 is engaged in the hole 42 of the platform, the aperture 28 of the blade root and the floating nut 34. As illustrated in Figure 5, the head of the screw 38 rests on the bore of the hole 42 of the platform so as to lock the platform 40 in position. Moreover, in order to ensure a good regularity of the air flow, the first auxiliary fastener 26, particularly the head of the screw 38, may be covered with a resin, for example an RTV resin. English "Room-Temperature Vulcanization", vulcanization at room temperature). Figure 6 shows an embodiment of the floating nut 34. In this embodiment, the floating nut 34 comprises an outer cage 34a and a threaded shaft 34d mounted floating relative to the outer cage 34a, here by intermediate of an inner cage 34c. The outer cage 34a is fixed on the blade root 21. In this case, the rivets 36 are engaged in openings 34b of the outer cage 34a and in corresponding openings of the blade root 21. The inner cage 34c 10 has a clearance relative to the outer cage 34a, which allows to adjust the position of the threaded barrel 34d relative to the orifice 28 to obtain an excellent alignment. In addition, the use of a floating nut 34 is particularly advantageous in the case where the first blade 20 is made of composite material. Indeed, it is difficult to make a tapping directly in the composite material. With the floating nut 34 which has a threaded barrel 34d, it is possible to drill only the composite material, in this case to provide the orifice 28 and the openings for the floating nut nut. The drilling operation is simpler and better controlled in the context of composite materials. The orifice 28 can thus be a smooth hole, just like the hole 42 of the platform. FIG. 7 represents a view from below of the root 21 of the first vane 20, before mounting of the vane 20 on the annular body 12 and of the platform 40 on the vane 20. The face of the vane foot 21 represented in Figure 7 is intended to face the annular body 12. This figure shows the relative arrangement between the orifices 22 provided for fixing the first blade 20 on the annular body 12 and the floating nuts 34 assembled at the foot of the dawn at the exit of the orifices 28.
    [0013] In the embodiment described, the attachment portion comprises the blade root 21. However, according to one variant, the attachment portion may comprise the head of the blade 20. In addition, unlike the representation of Figure 7, the feet 5 of the blades 20, 30 may include lateral recesses so as to reduce their mass. Indeed, insofar as the blade roots 20, 30 are covered by the platforms 40, said feet no longer play aerodynamic role and can be lightened. In the embodiment shown, there is shown first and second auxiliary fasteners which are similar. Indeed, they differ only in the size of the screw 38. However, the second auxiliary attachment could differ more from the first auxiliary attachment. In addition, despite the use of the singular, the main attachment and / or the auxiliary attachment may comprise several attachment subassemblies. Although the present invention has been described with reference to specific exemplary embodiments, modifications can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. Rectifier (10) for a turbomachine, comprising an annular body (12) having an axis (X) defining an axial direction, a radial direction and an azimuthal direction, at least a first blade (20) and a second blade (30) azimuthally adjacent to the first blade (20), each blade (20, 30) being attached to the annular body (12), and a platform (40) located between the first blade (20) and the second blade (30), the straightener being characterized in that each blade (20, 30) is attached to the annular body by at least one main attachment (24) and the platform (40) is secured to the first blade by a first auxiliary attachment (26) separate from the main attachment (24).
    [0002]
    The rectifier (10) of claim 1, wherein the platform (40) is attached to the second blade (30) by a second auxiliary attachment separate from the main attachment (24).
    [0003]
    3. Rectifier (10) according to claim 1 or 2, wherein the first auxiliary fastener and / or the second auxiliary fastener (26) is accessible on the side of the platform (40) radially opposite to the annular body (12).
    [0004]
    4. Rectifier (10) according to any one of claims 1 to 3, wherein the first and second blades (20, 30) are attached to the annular body (12) at their radially inner end.
    [0005]
    5. Rectifier (10) according to any one of claims 1 to 4, wherein each blade (20, 30) comprises a profile and a fastening portion (21) at one end of the profile, the platform (40). being attached to the fastening portion (21) on the side of the profile while the fastening portion (21) is attached to the annular body (12) on the side of the radially opposite fastening portion. to the profile.
    [0006]
    6. Rectifier (10) according to any one of claims 1 to 5, wherein the platform (40) has a density less than the density of the first blade (20).
    [0007]
    7. Rectifier (10) according to any one of claims 1 to 6, wherein the first blade (20) and / or the second blade (30) is composite material.
    [0008]
    8. Rectifier (10) according to any one of claims 1 to 7, wherein the first auxiliary attachment and / or the second auxiliary attachment (26) comprises a floating nut (34).
    [0009]
    The rectifier (10) according to any one of claims 1 to 8, wherein the platform (40) comprises bearing pads (44) configured to abut the first blade (20) and / or the second dawn (30).
    [0010]
    10. A turbomachine (100) comprising a rectifier (10) according to any one of claims 1 to 9.
    类似技术:
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    同族专利:
    公开号 | 公开日
    FR3032753B1|2018-11-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2685383A1|1991-12-18|1993-06-25|Snecma|STRUCTURAL ARM OF THE CASING OF A TURBOMACHINE.|
    EP2108785A2|2008-04-11|2009-10-14|United Technologies Corporation|Turbine blade and vane assembly with a ceramic platform|
    FR2958980A1|2010-04-14|2011-10-21|Snecma|RECTIFIER DEVICE FOR TURBOMACHINE|
    EP2472060A1|2010-12-30|2012-07-04|General Electric Company|Vane with spar mounted composite airfoil|FR3056250A1|2016-09-19|2018-03-23|Safran Aircraft Engines|AUBE WHEEL RECTIFIER IN INTERMEDIATE CASING|
    FR3070427A1|2017-08-24|2019-03-01|Safran Aircraft Engines|INSERT FOR FIXING A COMPONENT ON A TURBOMACHINE SUPPORT|
    FR3089258A1|2018-12-03|2020-06-05|Safran Aircraft Engines|Blower comprising an inter-blade platform fixed radially by a sacrificial protective sheet|
    法律状态:
    2016-02-12| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-19| PLSC| Publication of the preliminary search report|Effective date: 20160819 |
    2017-02-13| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-23| 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 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 7 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1551254A|FR3032753B1|2015-02-16|2015-02-16|RECTIFIER FOR A TURBOMACHINE|
    FR1551254|2015-02-16|FR1551254A| FR3032753B1|2015-02-16|2015-02-16|RECTIFIER FOR A TURBOMACHINE|
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