• 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 guide blade arranged in an air flow of a blower (15) of a turbofan aircraft turbofan, the blade being made using an extrados body (32a) and a lower body (32b) between which is arranged a heat conduction matrix (80). In addition, the fastening means of the two bodies (32a, 32b) are arranged outside the aerodynamic portion (32) of the blade.
    公开号:FR3077850A1
    申请号:FR1851199
    申请日:2018-02-13
    公开日:2019-08-16
    发明作者:Cedric ZACCARDI；Christophe Marcel Lucien Perdrigeon；Paul Antoine Foresto；Adrien Jacques Philippe FABRE
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    OUTPUT DIRECTIVE VANE FOR TURBOMACHINE, MADE FROM SEVERAL PARTS ASSEMBLED BETWEEN THEM
    BY MEANS OF FIXING OFF THE VEIN
    DESCRIPTION
    TECHNICAL AREA
    The present invention relates to the field of aircraft turbomachines with double flow, and in particular to the design of guide vanes arranged in all or part of an air flow of a fan of the turbomachine.
    They are preferably outlet guide vanes, also called OGV (from the English “Outlet Guide Vane”), intended to straighten the air flow at the outlet of the blower. Alternatively or simultaneously, guide vanes could if necessary be placed at the inlet of the blower. The guide vanes are conventionally arranged in the secondary stream of the turbomachine.
    The invention preferably relates to an aircraft turbojet engine equipped with such outlet guide vanes.
    STATE OF THE PRIOR ART
    On certain double-flow turbomachines, it is known to install outlet guide vanes downstream of the fan to straighten the flow which escapes therefrom, and also possibly to fulfill a structural function. This latter function is in fact intended to allow the passage of the forces from the center of the turbomachine towards an outer shroud situated in the extension of the fan casing. In this case, an engine attachment is conventionally arranged on or near this outer shell, to ensure the attachment between the turbomachine and an aircraft pylon.
    Recently, it has also been proposed to assign an additional function to the output guide vanes. It is a heat exchanger function between the outside air passing through the crown of outlet guide vanes, and the lubricant circulating inside these vanes. This heat exchanger function is for example known from document US 8,616,834, or from document FR 2,989,110.
    The lubricant intended to be cooled by the outlet guide vanes can come from different areas of the turbomachine. It may indeed be a lubricant circulating through the lubrication chambers of the rolling bearings supporting the motor shafts and / or the fan hub, or else a lubricant dedicated to the lubrication of the mechanical transmission elements of the accessories box (from the English AGB "Accessory Geared Box"). Finally, it can also be used for the lubrication of a fan drive reduction gear, when such a reduction gear is provided on the turbomachine in order to reduce the speed of rotation of its fan.
    The growing needs for lubricant require adapting the heat dissipation capacity, associated with the exchangers intended for cooling the lubricant. The fact of assigning a role of heat exchanger to the outlet guide vanes, as in the solutions of the two documents cited above, in particular makes it possible to reduce, or even eliminate conventional exchangers of the ACOC type (from the English “ Air Cooled Oil Cooler ”), These ACOC exchangers being generally arranged in the secondary stream, their reduction / elimination makes it possible to limit the disturbances of the secondary flow, and thus to increase the overall efficiency of the turbomachine.
    Within the interior lubricant cooling passage, it is possible to install obstacles to the circulation of the lubricant, such as studs intended to disrupt the flow and to increase the wetted surface, and this in order to ensure better heat exchange.
    However, making this type of blade can be difficult, if not impossible, with certain techniques that are deemed to be interesting. This is for example additive manufacturing, also called 3D printing or direct manufacturing, which may prove to be unsuitable for producing a single piece of the blade integrating the matrix, in particular when this blade has too large dimensions. and / or a network of studs with geometry unsuitable for additive manufacturing.
    To respond to this problem, it has been proposed to make the blade in several separate parts, so as to facilitate its manufacture. However, this type of design usually requires the presence of fixing means arranged on the aerodynamic part of the blade. These fixing means between the various components of the blade are capable of generating aerodynamic losses on the flow passing through this blade.
    STATEMENT OF THE INVENTION
    To respond at least partially to the drawbacks encountered with the embodiments of the prior art, the invention firstly relates to a guide vane intended to be arranged in all or part of an air flow of a blower of aircraft turbomachine with double flow, the guide blade comprising an aerodynamic flow straightening part intended to be matched by said whole or part of the fan air flow, said blade being produced using:
    - a lower surface body defining at least part of a lower surface of the aerodynamic part, the lower surface body comprising at least a first head fixing member intended for fixing the blade on a outer casing element, as well as at least a first foot fixing member intended for fixing the blade on an inner casing element;
    - an upper surface body defining at least part of an upper surface of the aerodynamic part, the upper surface body comprising at least a second head fixing member intended for fixing the blade on the 'outer casing element, as well as at least a second foot fixing member for fixing the blade on the inner casing element;
    - a thermal conduction matrix arranged in a space delimited between the lower and upper surface bodies, said matrix being intended to be crossed by lubricant and integrating obstacles to the circulation of lubricant; and
    - means for fixing the lower surface body to the upper surface body.
    According to the invention, said means for fixing the lower surface body to the upper surface body are constituted by first fixing means arranged radially outwards relative to the first and second head fixing members, and by second fastening means arranged radially inwards relative to the first and second foot fastening members.
    Consequently, the invention provides a solution making it possible to facilitate its manufacture, while exhibiting high aerodynamic performance. Indeed, the manufacture of the blade is made easy by the multiplicity of components adopted, these components each being able to be produced by conventional techniques even for large blades. In addition, the fact of moving the fastening means of these components outside the aerodynamic part of the blade, avoids the degradation of the aerodynamic flow passing through the blade.
    The invention thus offers a satisfactory compromise responding effectively to the problem posed, in particular by ensuring a separation of the thermal, aerodynamic and possibly structural functions of the blade.
    The invention therefore allows easier manufacturing, reduced cost and increased aerodynamic performance.
    The invention preferably provides at least any one of the following optional characteristics, taken individually or in combination.
    Said first fixing means and said second fixing means comprise bolts passing through orifices of passages made through the bodies of lower and upper surfaces. Alternatively or simultaneously, these fixing means can be of the welding, brazing or bonding type.
    Said thermal conduction matrix includes an outer sheath which is impervious to the lubricant, arranged in said space delimited between the lower and upper bodies. According to an alternative embodiment, the blade has a lubricant sealing device, arranged between the lower and upper bodies. This arrangement is used in particular when the matrix used has a permeable character.
    Said space housing the heat conduction matrix has a general U-shape defining two lubricant passages connected together by an elbow. Alternatively, the space could define a single passage, or else two passages intended to be connected to one another outside of dawn.
    The heat conduction matrix is made in one piece, or using several separate matrix elements arranged end to end or spaced from each other.
    The invention also relates to an aircraft turbomachine, preferably a turbojet engine, comprising a plurality of guide vanes such as that described above, these vanes being arranged downstream or upstream of a fan of the turbomachine.
    Preferably, the first and second fixing means are arranged outside said whole or part of the fan air flow, delimited by at least one aerodynamic wall arranged between the exterior and interior elements of the casing.
    Finally, the subject of the invention is a method of manufacturing a blade as described above, comprising the following steps:
    a) production of the intrados and extrados bodies and of said thermal conduction matrix;
    b) fixing the lower surface body to the upper surface body, using the first and second fixing means.
    Preferably, the thermal conduction matrix is produced independently of the intrados and extrados bodies, and more preferably by the additive manufacturing technique.
    Alternatively, at least part of the thermal conduction matrix can be made in one piece with at least one of the lower and upper bodies. For example, all the obstacles in the matrix can be made in one piece with one of the lower and upper bodies. According to another example, part of these obstacles can be made in one piece with one of the lower and upper surface bodies, and the other obstacles made in one piece on the other of these two bodies. .
    Other advantages and characteristics of the invention will appear in the detailed non-limiting description below.
    BRIEF DESCRIPTION OF THE DRAWINGS
    This description will be made with reference to the accompanying drawings, among which;
    - Figure 1 shows a schematic side view of a turbojet engine according to the invention;
    - Figure 2 shows an enlarged view, in more detail, of an outlet guide vane of the turbojet engine shown in the previous figure, the blade appearing according to a preferred embodiment of the invention;
    - Figure 3 corresponds to a sectional view taken along the line III-III of Figure 2;
    - Figure 3a is a view similar to that of Figure 3, showing an alternative embodiment;
    - Figure 4 shows a perspective view of part of the blade shown in the previous figures;
    - Figure 5 shows a perspective view of the upper surface body forming part of the blade shown in the previous figures;
    - Figure 6 shows a perspective view similar to the previous one, from another angle of view;
    - Figure 7 shows a perspective view of the lower surface body forming part of the blade shown in the previous figures;
    - Figure 8 shows a perspective view similar to the previous one, from another angle of view;
    - Figure 9 is a schematic view in longitudinal section of a portion of the turbojet engine comprising the blade shown in the preceding figures; and
    - Figure 10 is a view similar to that of Figure 9, according to an alternative embodiment.
    DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
    Referring to Figure 1, there is shown a turbofan 1 with double flow and double body, having a high dilution rate. The turbojet engine 1 conventionally comprises a gas generator 2 on either side of which are arranged a low pressure compressor 4 and a low pressure turbine 12, this gas generator 2 comprising a high pressure compressor 6, a combustion chamber 8 and a high pressure turbine 10. Subsequently, the terms “front” and “rear” are considered in a direction 14 opposite to the main direction of flow of the gases within the turbojet engine, this direction 14 being parallel to the axis. longitudinal 3 thereof. On the other hand, the terms “upstream” and “downstream” are considered according to the main direction of flow of the gases within the turbojet engine.
    The low pressure compressor 4 and the low pressure turbine 12 form a low pressure body, and are connected to each other by a low pressure shaft 11 centered on the axis 3. Likewise, the high pressure compressor 6 and the high pressure turbine 10 form a high pressure body, and are connected to each other by a high pressure shaft 13 centered on the axis 3 and arranged around the low pressure shaft 11. The shafts are supported by bearings bearing 19, which are lubricated by being arranged in oil chambers. It is the same for the fan hub 17, also supported by rolling bearings 19.
    The turbojet engine 1 also comprises, at the front of the gas generator 2 and of the low pressure compressor 4, a single blower 15 which is here arranged directly behind a cone of air intake of the engine. The fan 15 is rotatable along the axis 3, and surrounded by a fan casing 9. In FIG. 1, it is not driven directly by the low pressure shaft 11, but only indirectly driven by this shaft via a reducer 20, which allows it to rotate with a slower speed. Nevertheless, a solution with direct drive of the fan 15, by the low pressure shaft 11, comes within the scope of the invention.
    In addition, the turbojet engine 1 defines a primary stream 16 intended to be traversed by a primary flow, as well as a secondary stream 18 intended to be crossed by a secondary stream located radially outward relative to the primary stream, the stream of the fan being therefore divided. As is known to a person skilled in the art, the secondary stream 18 is delimited radially outwards in part by an outer ferrule 23, preferably metallic, extending rearward the fan casing 9. Alternatively, an aerodynamic wall forms the external delimitation of the secondary vein 18 as will be detailed below with reference to FIG. 9.
    Although this has not been shown, the turbojet engine 1 incorporates a set of equipment, for example of the fuel pump, hydraulic pump, alternator, starter, variable-timing stator (VSV) actuator, discharge valve actuator, or even an electric power generator. This is in particular an equipment for the lubrication of the reduction gear 20. This equipment is driven by an accessories box or AGB (not shown), which is also lubricated.
    Downstream of the fan 15, in the secondary vein 18, there is provided a crown of guide vanes which are here outlet guide vanes 24 (or OGV, from the English “Outlet Guide Vane”). These stator vanes 24 connect an outer casing element, here the outer shell 23, to an inner casing element 25 arranged externally with respect to a casing 26 of low pressure compressor 4. The inner casing element 25 here corresponds to the hub of intermediate casing, and it receives the foot of the blades 24. In this regard, it is noted that the outer shell 23 forms the periphery of this intermediate casing, of which the blades 24 also form part by mechanically connecting these two elements 23, 25. Finally , it is noted that the intermediate casing hub 25 is mechanically connected to the reduction gear 20, so as to together constitute a path for the passage of forces towards a motor attachment 30 carried by the outer shell 23.
    The blades 24 are spaced circumferentially from one another, and allow the secondary flow to be straightened after it has passed through the blower 15. In addition, as mentioned above, these blades 24 can also fulfill a structural function. They then ensure the transfer of forces from the reduction gear 20 and the rolling bearings 19 associated with the motor shafts and the fan hub, to the outer shroud 23 and its engine attachment 30 (intended to connect the engine to a suspension pylon) .
    Finally, the outlet guide vanes 24 provide, in the embodiments which are presently described, a third function of heat exchanger between the secondary air flow passing through the crown of blades, and of the lubricant circulating inside these vanes 24. The lubricant intended to be cooled by the outlet guide vanes 24 is that used for the lubrication of the rolling bearings 19, and / or the equipment of the turbojet engine, and / or the accessories box, and / or the reducer 20. These vanes 24 thus form part of the fluid circuit (s) in which the lubricant is circulated in order to successively lubricate the associated element (s), then to be cooled.
    With reference now to FIGS. 2 to 8, one of the outlet guide vanes 24 will be described, according to a preferred embodiment of the invention. It is noted that the invention as it will be described with reference to these figures can be applied to all the vanes 24 of the stator ring centered on the axis 3, or even only to some of these vanes.
    The blade 24 may be of strictly radial orientation as in FIG. 1, or else be slightly inclined axially upstream or downstream, as shown in FIG. 2. In all cases, it is preferably right in side view as shown in FIG. 2, extending in a span direction 27.
    The outlet guide vane 24 has an aerodynamic part 32 which corresponds to its central part, that is to say that exposed to the secondary flow flowing through the secondary vein 18. On either side of this aerodynamic part 32 serving to straighten the flow leaving the fan, the blade 24 comprises a foot 34 and a head 36 respectively.
    The foot 34 is used for fixing the blade 24 on the inner casing element, while the head 36 is used for fixing the same blade on the outer shell extending the fan casing. Although this has not been shown, the blade 24 may include at the level of its foot and of its head platforms serving to reconstitute the secondary vein between the blades 24, in the circumferential direction. Alternatively, these platforms can be added elements between the feet and the blade heads, without departing from the scope of the invention.
    As will be detailed below, the blade 24 is preferably manufactured using two bodies 32a, 32b fixedly attached to one another, and a thermal conduction matrix 80 arranged in a space 81 delimited between these two bodies.
    In this preferred embodiment of the invention, the aerodynamic part 32 is equipped with two interior passages 50a, 50b substantially parallel to each other, and parallel to the span direction 27. More precisely, there is acts of a first interior passage 50a for cooling the lubricant, which extends in a first main direction 52a of flow of the lubricant. This direction 52a is substantially parallel to the span direction 27, and has a direction going from the foot 34 towards the head 36. In a similar manner, there is provided a second interior passage 50b for cooling the lubricant, which extends in a second main direction 52b of lubricant flow within this passage. This direction 52b is also substantially parallel to the span direction 27, and has an opposite direction going from the head 36 to the foot 34. The first passage 50a is therefore intended to be crossed radially outwards by the lubricant, while the second passage 50b is intended to be crossed radially inward. To ensure the passage from one to the other, near the head 36, the external radial ends of the two passages 50a, 50b are fluidly connected by an elbow 54 at 180 °, this elbow 54 being also defined by the space 81. Alternatively, the passages 50a, 50b do not connect within the aerodynamic part 32 of the blade 24, but each extend separately over the entire length of the blade. To fluidly connect to each other outside the blade 24, there is for example provided a connection elbow arranged radially outward relative to the blade head 36, for example resting on this head.
    The internal radial ends of the two passages 50a, 50b are in turn connected to the lubricant circuit, shown diagrammatically by the element 56 in FIG. 2. This circuit 56 notably includes a pump (not shown), making it possible to apply the lubricant to the desired direction of circulation within the passages 50a, 50b, namely the introduction of the lubricant by the internal radial end of the first passage 50a, and the extraction of the lubricant by the internal radial end of the second passage 50b. Connections 66 ensure fluid communication between the internal radial ends of the passages 50a, 50b and the circuit 56, these connections 66 passing through the foot 34. The connections 66 passing through the foot 34 can also be defined by the space 81.
    The two passages 50a, 50b and the elbow 54 together form the space 81 in the general shape of a U, with the first passage 50a and the second passage 50b offset from each other in a transverse direction 60 of the blade. substantially orthogonal to the span direction 27. To best optimize heat exchange, the first passage 50a is located on the side of a trailing edge 62 of the blade 24, while the second passage 50b is located on the side d 'A leading edge 64. However, a reverse situation can be retained, without departing from the scope of the invention. It is also noted that the invention could provide an aerodynamic part 32 with a single interior cooling passage. In this case, certain blades would be crossed by the lubricant from the inside to the outside, while other blades would be crossed in the opposite direction.
    The body 32a of the blade corresponds to an upper surface body which here defines the entire upper surface 72 of the aerodynamic part 32. This body 32a also defines the leading edge 64, the trailing edge 62, the part of the blade root 34 located on the side of the upper surface, as well as the part of the blade head located on the side of this same upper surface 72. Opposite the upper surface 72, the body 32a defines a recess 71 referenced in FIG. 6, this recess housing the other body 32b corresponding to a lower surface body. Once the bodies 32a, 32b are assembled, the inner surface of the body 32a which delimits the recess 71, participates in the definition of the space 81 forming the two interior passages 50a, 50b.
    The lower surface body 32b here defines the entire lower surface 70 of the aerodynamic part 32. It has a thickness in which a U-shaped imprint is made to define the space 81, and more precisely the two passages interiors 50a, 50b, as well as the elbow 54. This imprint is open on the surface opposite to the lower surface 70, opposite surface which is intended to be pressed into the bottom of the recess 71 of the upper surface body 32a. The imprint defines between the two passages 50a, 50b a solid area 76 which also is intended to be pressed into the bottom of the recess 71, as can be seen in FIG. 3. In this figure, a device is also shown. sealing with lubricant. It is a seal 73 arranged at the interface between the two bodies 32a, 32b, in order to maintain the lubricant in the interior passages 50a, 50b. This seal 73 can be completed by other seals at the interface between the two bodies.
    The two bodies 32a, 32b are each made in one piece using a metallic material, for example by forging or by molding, which are techniques making it possible to obtain the surface condition required for surfaces d '' pressure and extrados.
    In the passages defined by these intrados and extrados bodies, the thermal conduction matrix 80 is provided, preferably in the form of a U so as to fill the entire space 81. The presence of this matrix allows improve the heat exchange performance, in particular thanks to the fact that it provides an increase in the wetted surface on the side of the lubricant which passes through the passages 50a, 50b. This matrix 80 also makes it possible to disturb the passage of the lubricant, thereby generating turbulence which directly influences the convection coefficient of the lubricant passing through the matrix. The definition of such a matrix can thus be carried out so as to maximize the performance of exchange, while creating the least pressure losses possible between the entry and the exit of the blade.
    In the embodiment shown in FIG. 3, the matrix 80 is independent of the bodies 32a, 32b, and of a nature permeable to the lubricant which passes through it. It then comprises a plurality of obstacles to the circulation of the lubricant, these obstacles 82 taking the form of studs, walls, tongues, lattice, or other similar elements extending in the thickness of the passages 50a, 50b, and connected to each other. to others. As mentioned above, this matrix could consist of simple obstacles made in one piece with the upper surface body 32a and / or with the lower surface body 32b.
    More specifically, the obstacles 82 are interconnected by contact elements 84a bearing against the lower surface body 32b, as well as by opposite contact elements 84b, bearing against the upper surface body 32a. The obstacles 82 can in turn be arranged in staggered rows. They are for example provided in a density of approximately 3 obstacles / cm 2 . More generally, the density is for example between approximately 1 and 5 obstacles / cm 2 on average, this density being uniform or evolving along the lubricant path. The matrix 80 may have a thickness of the order of several millimeters, which corresponds to the thickness of the interior passages in which it is housed.
    It can be manufactured using an alloy based on aluminum or titanium, or any other material reputed to have good heat dissipation properties. This matrix 80 is preferably produced by additive manufacturing, also called 3D printing, without requiring a structural function since it is imparted by the two bodies 32a, 32b. One of the following techniques can be used for manufacturing the matrix 80:
    - selective fusion by laser (from English “Selective Laser Melting” or “SLM”) or by electron beam (from English “Electron Beam Melting” or “EBM”);
    - selective sintering by laser (from “Selective Laser Sintering” or “SLS”) or by electron beam;
    - any other type of powder solidification technique under the action of a medium to high power source of energy, the principle being to melt or sinter a bed of metal powder by laser beam or electron beam.
    Other more conventional techniques are also possible, such as stamping or stamping.
    To facilitate the manufacture of the matrix 80, instead of being produced in one piece all along the U, it can be produced using several distinct matrix elements, arranged end-to-end or spaced apart. each other. As an example, it can be carried out using three matrix elements corresponding to the two branches of the U and to its base. The smaller size of these matrix elements facilitates their production by additive manufacturing.
    According to an alternative embodiment shown diagrammatically in FIG. 3a, the matrix 80 comprises an outer sheath 84 sealed with the lubricant, and arranged in contact with the two bodies 32a, 32b. This sheath 84 has a shape substantially identical to that of the space 81 in which it is housed. The lubricant thus remains confined in the sheath 84, which eliminates the need to use the sealing device 73 of the mode of FIG. 3. The obstacles 82 thus connect the portions of opposite walls of the sheath 84, according to an identical or similar configuration to that of FIG. 3.
    Returning to FIG. 2, during the operation of the engine, the lubricant circulating through the circuit 56 is introduced into the first interior passage 50a, in the first direction 52a going radially outward. At this point, the lubricant has a high temperature. A heat exchange then takes place between this lubricant conforming to the matrix 80 of the first passage 50a, and the secondary flow conforming to the external surface of the pressure and pressure surfaces. The lubricant, after having been redirected by the elbow 54 in the second passage 50b, undergoes in the latter a similar cooling, always by heat exchange with the secondary air flow and by circulating in the second main direction of flow 52b. Then, the cooled lubricant is extracted from the blade 24, and redirected by the closed circuit 56 towards elements to be lubricated and / or towards a reservoir of lubricant from which cooled lubricant is pumped to lubricate elements.
    One of the features of the invention resides in the fixing of the upper surface body 32a to the lower surface body 32b. Indeed, the fixing means used to mechanically connect these two bodies 32a, 32b are offset from the aerodynamic part 32 of the blade, in order to be located exclusively at the foot 34 and the head 36 of this blade. This avoids aerodynamic disturbances of the secondary flow, which no longer meets these means of fixing the two bodies.
    To do this, the means in question consist of first fixing means 90a associated with the head 36 of the blade, and second fixing means 90b associated with the foot 34 of the blade. More specifically, the first fixing means 90a are arranged radially outwards relative to first and second head fixing members of the blade on the outer shell 23. These first and second head fixing members 94a, 94b are respectively provided on the lower surface body 32b and on the upper surface body 32a, at a radially external part of these bodies. Of course, the radial direction must be understood as corresponding to the span direction 27 of the blade.
    The members 94a, 94b preferably take the form of fittings made in one piece with the blade, and extending substantially axially. They define orifices intended to be crossed by fixing elements of the screw or bolt type 96 as has been shown diagrammatically in FIG. 9, and this in order to ensure the mechanical connection of the blade head with the outer ferrule 23. Preferably, two members 94a are provided on the lower surface body 32b, and two members 94b on the upper surface body 32a, with orifices arranged substantially radially through these members.
    Thus, the first fixing means 90a of the bodies 32a, 32b are arranged radially outwards relative to these head fixing members 94a, 94b. The first means 90a comprise passage orifices 92 passing through the two bodies, as well as fixing elements of the screw or bolt type 95 passing through these orifices 92. Preferably, each body has a substantially axial row of passage orifices 92, practiced in the head part of the body concerned. In other words, this row being in the head part of the body concerned, substantially in the direction of the chord of the blade.
    In the example shown in FIG. 9, the secondary vein 18 is not delimited externally by the ferrule 23, but by a non-structural aerodynamic wall 97 arranged radially inwards relative to the head fixing members 94a, 94b . Consequently, this wall 97 makes it possible to hide all of the elements 90a, 94a, 94b of the secondary flow.
    Similarly, the second fastening means 90b are arranged radially inwards with respect to first and second fastening members of the blade at the vane on the intermediate casing hub 25. These first and second fastening devices 98a, 98b are respectively provided on the lower surface body 32b and on the upper surface body 32a, at a radially internal part of these bodies.
    The members 98a, 98b preferably take the form of fittings made in one piece with the blade, and extending substantially axially. They define orifices intended to be crossed by fixing elements of the screw or bolt type 96 as has been shown diagrammatically in FIG. 9, and this in order to ensure the mechanical connection of the blade root with the casing hub intermediate 25. Preferably, two organs 98a are provided on the lower surface body 32b, and two organs 98b on the upper surface body 32a, with orifices arranged substantially radially through these organs.
    Thus, the second fixing means 90b of the bodies 32a, 32b are arranged radially inwards relative to these foot fixing members 98a, 98b. The second means 90b comprise passage orifices 92 passing through the two bodies, as well as fixing elements of the screw or bolt type 95 passing through these orifices 92. Preferably, each body has a substantially axial row of passage orifices 92, practiced in the foot part of the body concerned.
    In the example shown in FIG. 9, the secondary stream 18 is not delimited internally by the intermediate casing hub 25, but by a non-structural aerodynamic wall 99 arranged radially outward relative to the foot fastening members 98a, 98b. Consequently, this wall 99 makes it possible to hide all of the elements 90b, 98a, 98b of the secondary flow.
    Alternatively, it is noted that the first and second fixing means 90a, 90b described above can be replaced by means of the welding, brazing or even bonding type, always being located outside of the aerodynamic part 32.
    Finally, it is noted that the blade 24 can be manufactured simply by separately producing each of its three constituent parts, namely the two bodies 32a, 32b and the matrix 80, then by putting the latter in place in the space 81 between the two bodies, before fixing them using bolts 95.
    The example of FIG. 10 is similar to that of FIG. 9. The only differences reside in the design of the ferrule 23 and of the intermediate casing hub 25, at the level of the blades 24. Indeed, in this other example of the FIG. 10, the elements 23, 25 define housings 100 in which the feet 34 and the heads 36 of the blades are inserted.
    Of course, various modifications can be made by those skilled in the art to the invention which has just been described, only by way of nonlimiting examples and the scope of which is delimited by the appended claims. In particular, it is noted that in the non-illustrated case of the inlet guide vanes for straightening the air flow upstream of the blower, these blades are arranged throughout the air flow of the blower around a cone non-rotary air inlet, the feet of the blades then being connected to this fixed air inlet cone.
    Furthermore, other engine architectures also fall within the scope of the invention, by responding to the designation "turbomachine of an aircraft with double flow". It may for example be a triple body architecture (namely comprising three shafts connecting respectively first stages of turbine to a blower, second stages of turbine to stages of low pressure compressor, and third stages of turbine at high pressure compressor stages).
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Directing vane (24) intended to be arranged in all or part of an air flow of a fan (15) of a turbomachine of an aircraft with double flow, the directing vane comprising an aerodynamic part (32) of flow straightening intended to be matched by said whole or part of the fan air flow, said blade being produced using:
    - a lower body (32b) defining at least part of a lower surface (70) of the aerodynamic part (32), the lower body comprising at least a first head fixing member ( 94a) intended for fixing the blade on an external casing element (23), as well as at least a first foot fixing member (98a) intended for fixing the blade on an internal casing element ( 25);
    - an upper body (32a) defining at least part of an upper surface (72) of the aerodynamic part (32), the upper body comprising at least a second head fixing member ( 94b) for fixing the blade on the outer casing element (23), as well as at least one second foot fixing member (98b) for fixing the blade on the inner element of housing (25);
    - a thermal conduction matrix (80) arranged in a space (81) delimited between the lower and upper surface bodies (32b, 32a), said matrix being intended to be crossed by lubricant and integrating obstacles ( 82) to the circulation of lubricant; and
    - Means (90a, 90b) for fixing the lower surface body (32b) to the upper surface body (32a), characterized in that said means for fixing the lower surface body to the upper surface body are constituted by first fastening means (90a) arranged radially outward relative to the first and second head fastening members (94a, 94b), and by second fastening means (90b) arranged radially inward relative to the first and second foot fixing members (98a, 98b).
    [2" id="c-fr-0002]
    2. Guide vane according to claim 1, characterized in that said first fixing means (90a) and said second fixing means (90b) comprise bolts (95) passing through passage openings (92) formed through the bodies of '' lower and upper surfaces (32b, 32a).
    [3" id="c-fr-0003]
    3. Guiding vane according to claim 1 or claim 2, characterized in that said thermal conduction matrix (80) comprises an outer sheath (84) sealed with lubricant, arranged in said space (81) delimited between the lower body and extrados.
    [4" id="c-fr-0004]
    4. Guide vane according to claim 1 or claim 2, characterized in that it comprises a device (73) for sealing the lubricant arranged between the intrados and extrados bodies (32b, 32a).
    [5" id="c-fr-0005]
    5. Guide vane according to any one of the preceding claims, characterized in that said space (81) housing the thermal conduction matrix (80) has a general U shape defining two lubricant passages (50a, 50b) connected together by an elbow (54).
    [6" id="c-fr-0006]
    6. Directing vane according to any one of the preceding claims, characterized in that the thermal conduction matrix (80) is made in one piece, or else using several distinct matrix elements arranged end-to-end or spaced one another.
    [7" id="c-fr-0007]
    7. aircraft turbomachine (1), preferably a turbojet engine, comprising a plurality of guide vanes (24) according to any one of the preceding claims, arranged downstream or upstream of a fan (15) of the turbomachine .
    [8" id="c-fr-0008]
    8. Turbomachine according to claim 7, characterized in that the first and second fixing means (90a, 90b) are arranged outside said whole or part of the fan air flow (15), delimited by at least one aerodynamic wall (97, 99) arranged between the outer and inner elements of the casing (23, 25).
    [9" id="c-fr-0009]
    9. A method of manufacturing a blade (24) according to any one of claims 1 to 6, characterized in that it comprises the following steps:
    a) production of the intrados and extrados bodies (32b, 32a) and of said thermal conduction matrix (80);
    b) fixing the lower surface body (32b) to the upper surface body (32a), using the first and second fixing means (90a, 90b).
    [10" id="c-fr-0010]
    10. The manufacturing method according to claim 9, characterized in that the thermal conduction matrix (80) is produced independently of the intrados and extrados bodies (32b, 32a), preferably by additive manufacturing.
    [11" id="c-fr-0011]
    11. The manufacturing method according to claim 9, characterized in that at least a part of the thermal conduction matrix (80) is made in one piece with at least one of the lower and upper bodies ( 32b, 32a).
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    同族专利:
    公开号 | 公开日
    GB2572680B|2022-03-16|
    US10830076B2|2020-11-10|
    GB2572680A|2019-10-09|
    GB201901681D0|2019-03-27|
    FR3077850B1|2020-03-13|
    US20190249558A1|2019-08-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB523038A|1937-12-23|1940-07-03|Bayerische Motoren Werke Ag|Hollow blade for exhaust gas turbine rotors|
    GB2376269A|2001-06-08|2002-12-11|Rolls Royce Plc|A gas turbine engine breather outlet|
    US20080159851A1|2006-12-29|2008-07-03|Thomas Ory Moniz|Guide Vane and Method of Fabricating the Same|
    US8616834B2|2010-04-30|2013-12-31|General Electric Company|Gas turbine engine airfoil integrated heat exchanger|
    US20150315923A1|2012-04-05|2015-11-05|Snecma|Stator vane formed by a set of vane parts|
    US20170284417A1|2016-04-01|2017-10-05|Safran Aircraft Engines|Output director vane for an aircraft turbine engine, with an improved lubricant cooling function using a heat conduction matrix housed in an inner duct of the vane|
    US20170292531A1|2016-04-06|2017-10-12|Rolls-Royce North American Technologies, Inc.|Fluid cooling system integrated with outlet guide vane|FR3110630A1|2020-05-20|2021-11-26|Safran Aircraft Engines|TURBOMACHINE OUTPUT DIRECTOR VANE, MADE FROM SEVERAL PARTS ASSEMBLED BETWEEN THEM|FR2989110B1|2012-04-05|2016-09-09|Snecma|DAWN OF STATOR FORMED BY A SET OF DAWN PARTS|
    FR3071008B1|2017-09-11|2019-09-13|Safran Aircraft Engines|DRAFT OUTPUT DIRECTOR FOR TURBOMACHINE, COMPRISING A LUBRICANT COOLING PASSAGE EQUIPPED WITH COMPRESSED THERMAL CONDUCTION MATRIX BETWEEN THE INTRADOS AND EXTRADOS WALLS|FR3059353B1|2016-11-29|2019-05-17|Safran Aircraft Engines|AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN|
    FR3066532B1|2017-05-22|2019-07-12|Safran Aircraft Engines|AIRBOARD TURBOMACHINE EXIT OUTPUT AUBE, COMPRISING A LUBRICANT COOLING PASS WITH FLOW-MAKING FLUID DISRUPTORS OF SIMPLIFIED MANUFACTURING|
    FR3071008B1|2017-09-11|2019-09-13|Safran Aircraft Engines|DRAFT OUTPUT DIRECTOR FOR TURBOMACHINE, COMPRISING A LUBRICANT COOLING PASSAGE EQUIPPED WITH COMPRESSED THERMAL CONDUCTION MATRIX BETWEEN THE INTRADOS AND EXTRADOS WALLS|
    US20210087955A1|2019-09-20|2021-03-25|United Technologies Corporation|Integrated lubricating fluid filtering and metering device|
    法律状态:
    2019-01-23| PLFP| Fee payment|Year of fee payment: 2 |
    2019-08-16| PLSC| Publication of the preliminary search report|Effective date: 20190816 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 3 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 4 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1851199A|FR3077850B1|2018-02-13|2018-02-13|OUTPUT DIRECTIVE VANE FOR TURBOMACHINE, MADE FROM SEVERAL PARTS ASSEMBLED BETWEEN THEM BY MEANS OF ATTACHMENT OF THE VEIN|
    FR1851199|2018-02-13|FR1851199A| FR3077850B1|2018-02-13|2018-02-13|OUTPUT DIRECTIVE VANE FOR TURBOMACHINE, MADE FROM SEVERAL PARTS ASSEMBLED BETWEEN THEM BY MEANS OF ATTACHMENT OF THE VEIN|
    GB1901681.5A| GB2572680B|2018-02-13|2019-02-07|Outlet guide vane for turbomachine, made from several parts assembled together by attachment means outside the flow stream|
    US16/270,771| US10830076B2|2018-02-13|2019-02-08|Outlet guide vane for turbomachine, made from several parts assembled together by attachment means outside the flow stream|
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