• 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 vane (24) for a turbofan aircraft turbomachine, its aerodynamic portion (34) comprising a first internal passage (50a) lubricant cooling in which are arranged thermal transfer means and a second lubricant cooling inner passage (50b) in which thermal transfer means is arranged, the aerodynamic portion comprising a welded zone (54) connecting a lubricant outlet end of the first inner passage (50a) to an inlet end lubricant of the second passage (50b), the bend zone extending along a curved generatrix and being partially defined by the intrados wall and the extrados wall of the blade. According to the invention, the bent zone (54) comprises one or more lubricant guides (84) arranged between the intrados and extrados walls of the blade, and each extending substantially parallel to the curve generatrix of the bent area (54).
    公开号:FR3059353A1
    申请号:FR1661643
    申请日:2016-11-29
    公开日:2018-06-01
    发明作者:Cedric ZACCARDI；Marcel Lucien Perdrigeon Christophe；Mohamed-Lamine BOUTALEB；Vincent Francois Dreano Sebastien
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    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 blower 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 shroud, to ensure 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 accessory box, from 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 decrease 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, makes it possible in particular to reduce, or even eliminate conventional exchangers of the ACOC type (from the English " Air Cooled OR 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.
    The heat exchanger function is obtained on the blade by providing one or more interior passages within this blade, and by installing heat transfer means within these passages delimited by the lower surface wall and the extrados. When two passages are provided respectively for the outward path of the lubricant in the blade, and for its return path, a bent zone connects these two passages. The bent area is generally left free to limit the pressure losses that could be caused by the presence of heat transfer means of the type of those installed in the interior passages connected by this bent area.
    However, this bent area is likely to be the seat of a phenomenon of recirculation of the lubricant at the outlet of the interior passage, due to the gross rupture of section between this enlarged hollowed area, and the end of the interior passage structured by the presence of heat transfer means. The lubricant in fact undergoes a loss of speed in certain parts of the bent zone, which causes recirculations of lubricant disturbing its flow.
    In addition, the absence of heat transfer means in the bent zone significantly reduces the overall heat exchange capacity of the blade, and reduces the mechanical resistance of this zone, however subjected to high lubricant pressures (for example ten bars).
    STATEMENT OF THE INVENTION
    To respond at least partially to these problems, the invention firstly relates to a guide vane intended to be arranged in all or part of an air flow of a fan of an aircraft turbomachine with double flow, the guide blade comprising a foot, a head, as well as an aerodynamic flow straightening part arranged between the foot and the head of the blade, said aerodynamic part of the blade comprising a first internal lubricant cooling passage in which are arranged heat transfer means, the first internal passage extending in a first main direction of flow of the lubricant going from the foot towards the head of the blade, said first internal passage being partly delimited by a wall of lower surface and by an upper surface of the blade, the aerodynamic part also comprising a second internal lubricant cooling passage in which transfer means are arranged t thermal, the second interior passage extending in a second main direction of flow of the lubricant going from the head towards the foot of the blade, said second interior passage being partly delimited by the bottom surface and by the wall dawn extrados.
    According to the invention, the aerodynamic part comprises a bent zone connecting one end of the first interior passage to one end of the second passage, the bent zone extending along a curved generatrix and being partly delimited by the lower surface wall and by the dawn upper surface. In addition, the bent zone comprises at least one lubricant guide arranged between the lower surface and the upper wall of the blade, and each extending substantially parallel to the curved generator of the bent zone.
    Thanks to the presence of the lubricant guide (s), the recirculation of the lubricant is advantageously avoided. In addition, the guide (s) reinforce the heat transfers due to the increase in the surface wetted by the lubricant, just as they are capable of improving the mechanical strength of the bent area.
    The invention also has at least one of the following optional features, taken individually or in combination.
    Preferably, the end of the first passage is a lubricant outlet end, and the end of the second interior passage is a lubricant inlet end. A reverse solution can obviously be envisaged, without departing from the scope of the invention.
    Each lubricant guide is a wall having a first end facing the end, for example of the lubricant outlet, of the first interior passage, as well as a second end facing the end, for example of the lubricant inlet. , from the second interior passage.
    Preferably, each lubricant guide comprises, between its first and its second end, at least one wall interruption forming a space separating two wall sections. The design in sections of wall spaced from each other makes it possible to increase the phenomenon of convection, and constitutes a simple solution to favor the evacuation of the powders in the event of additive manufacture of the guides of lubricant.
    Preferably, each lubricant guide comprises, between its first and its second end, a plurality of wall interruptions each forming a space separating two wall sections.
    Preferably, for any two lubricant guides which are directly consecutive in a span direction of the blade, the wall sections are staggered. This further increases the convection phenomenon.
    For example, for each lubricant guide, the number of wall sections is between 2 and 40. In this regard, it is noted that the number of sections depends in particular on the desired mechanical strength, on the mass allocated for the guides and / or their method of manufacture.
    Preferably, the lubricant guides define lubricant passage channels therebetween, and the guides are spaced from each other by spacing distances of which at least two of them are different. Consequently, in this case, the width of the passage channels may differ, which makes it possible to locally adapt to the thickness of the bent zone in order, for example, to present channels all having sections which are substantially equivalent in terms of area. This results in better balancing of the lubricant flow rates in each of the passage channels.
    Preferably, each lubricant guide is a wall connecting the lower surface wall to the upper wall, and in any cross section of the bent area, said wall forming the lubricant guide is inclined locally with respect to a normal to each of the lower and upper surfaces. This makes it possible to implement additive manufacturing according to conventional methods and principles for the bent zone and the part of the blade which surrounds it.
    However, it is noted that each lubricant guide could be a wall connecting the lower surface wall to the upper wall, regardless of the inclination of this wall. This feature makes it possible to reinforce the mechanical strength of the blade at the bent zone subjected to high lubricant pressures.
    Preferably, the number of lubricant guide is between 1 and 10. This number depends in particular on the dimensions of the bent zone and the thickness of material forming the guides.
    Finally, the invention also relates to an aircraft turbomachine, preferably a turbojet engine, comprising a plurality of guide vanes arranged downstream or upstream of a fan of the turbomachine, said vanes preferably having a structural function. In this way, the blades are capable of ensuring the passage of forces from the center of the turbomachine towards an outer shroud located in the extension of the fan casing.
    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, more detailed, of a portion of the guide vane outlet of the turbojet engine shown in the previous figure;
    - Figure 3 is a sectional view taken along the line III-III of Figure 2;
    - Figure 3a is a view similar to that of Figure 3, according to an alternative embodiment;
    - Figure 4 is an enlarged view of that of Figure 2, showing more specifically the bent area;
    - Figure 5 is a sectional view taken along the line V-V in Figure 4;
    - Figure 6 is a view similar to that of Figure 5, according to an alternative embodiment;
    - Figures 7 to 9 are views similar to that of Figure 4, according to alternative embodiments; and
    - Figure 10 is a figure similar to that of Figure 3, 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. The same is true 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 blower 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 duct 18 is delimited radially outwards in part by an outer ferrule 23, preferably metallic, extending rearward the fan casing 9.
    Although this has not been shown, the turbojet engine 1 is equipped with a set of equipment, for example of the fuel pump, hydraulic pump, alternator, starter, variable-timing stator (VSV) actuator, valve actuator or 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 stream 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 the outer shell 23 to a casing 26 surrounding the low pressure compressor 4. They are spaced circumferentially from one another, and make it possible to straighten the secondary flow after it has passed through the blower 15. In addition, these vanes 24 can also fulfill a structural function, as is the case in the exemplary embodiments which are presently described. They transfer the forces coming from the reduction gear and the rolling bearings 19 of the motor shafts and of the fan hub, to the outer shell 23. Then, these forces can pass through a motor attachment 30 fixed on the shell 23 and connecting the turbojet engine. to an attachment pylon (not shown) of the aircraft.
    Finally, the outlet guide vanes 24 provide, in the embodiments which are described here, 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 of the turbojet engine equipment, and / or of the accessories box, and / or of the reducer 20. These vanes 24 thus form part of the fluid circuit (s) in which the lubricant is put into circulation in order to successively lubricate the associated element (s), then to be cooled.
    With reference now to FIGS. 2 to 3a, one of the outlet guide vanes 24 will be described, according to a first preferred embodiment of the invention. In this regard, it is noted that the invention as it will be described below 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 as shown in FIG. 2. In all cases, it is preferably straight in side view as shown in the Figure 2, extending in a span direction 25, or radial direction of the blade.
    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. On either side of this aerodynamic part 32 serving to straighten the flow leaving the fan, the blade 24 has a foot 34 and a head 36 respectively.
    The foot 34 is used for fixing the blade 24 on the low pressure compressor housing, while the head is used for fixing the same blade on the outer shell extending the fan housing. In addition, the blade 24 comprises at the level of its foot and of its head, platforms 40 serving to reconstitute the secondary vein between the blades 24, in the circumferential direction.
    The aerodynamic part 32 of the blade, without its thermal conduction matrices which will be described below, is for example made in one piece, obtained for example by additive manufacturing called 3D printing or direct manufacturing. The additive manufacturing of the aerodynamic part 32 is for example carried out by any of the following techniques:
    - selective fusion by laser (from the English “Selective Laser Melting” or “SLM”) or by electron beam (from the English “Electron Beam Melting” or “EBM”);
    - selective sintering by laser (“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.
    The powder used is based on aluminum or titanium, or on the basis of another metallic material or any other material having satisfactory thermal conduction characteristics.
    The aerodynamic part 32 of the blade could nevertheless be produced using more conventional techniques, making it possible to reveal a hollowed portion in which the matrix would then be introduced, before the installation of a closure plate for example by welding, gluing or brazing.
    In addition, the manufacture of the single piece may include the foot 34, and / or the head 36, and / or the platforms 40, without departing from the scope 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 25. More specifically, it is a first interior passage 50a for cooling lubricant, which extends in a first main direction 52a of lubricant flow. This direction 52a is substantially parallel to the span direction 25, 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 25, and has an opposite direction going from the head 36 to the foot 34. In the embodiment considered, the first passage 50a is therefore intended to be crossed radially towards the outside 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 a bent zone 54 also called elbow, which extends over substantially 180 ° . This bent area 54, which is specific to the present invention and which will be detailed below, corresponds to a hollow made in the aerodynamic part 32, and equipped with specific means for guiding the lubricant.
    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 comprises 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 two passages 50a, 50b as well as the bent zone 54 together have a general U shape, with the first passage 50a and the second passage 50b offset from one another in a transverse direction 60 of the blade substantially orthogonal to the large-scale direction 25. 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 of an edge Attack 64. However, an opposite situation can be retained, without departing from the scope of the invention.
    The aerodynamic part 32 of the outlet guide vane 24 comprises a lower surface 70, an upper surface 72, a solid area 74 connecting the two walls 70, 72 near the trailing edge 62, a solid area 76 connecting the two walls 70, 72 near the leading edge 64, as well as a central solid area 78. This latter area 78 connects the two walls 70, 72 at a substantially central portion thereof, according to the direction of the dawn rope. It also serves as structural reinforcement and extends from the foot 34 to the elbow 54, while the solid zones 74, 76 extend over substantially the entire length of the part 32, in the span direction 25. The first passage 50a is formed between the walls 70, 72 and between the solid areas 74, 78, while the second passage 50b is formed between the walls 70, 72 and between the solid areas 76, 78. The lower and inner walls upper surfaces 70, 72 have, with regard to the passages 50a, 50b which they delimit, substantially constant thicknesses. On the other hand, the passages 50a, 50b extend transversely in the direction 60 by presenting a variable height between the two walls 70, 72. Alternatively, these passages could have a constant height, and the two walls 70, 72 would then preferentially adopt a variable thickness to obtain the aerodynamic profile of the blade.
    The two interior passages 50a, 50b for cooling the lubricant have the particularity of integrating thermal conduction means preferably comprising walls and / or fins 80. In FIG. 3, these means take the form of thermal conduction matrices, provided in particular with main heat transfer fins and also called convection matrices. These dies 50a ', 50b' are inserted in the interior passages 50a, 50b. By way of example, each matrix 50a ′, 50b ′ comprises rows of main heat transfer fins 80 succeeding each other in the direction of span 25. The main fins 80 are locally arranged substantially orthogonally to the lower and upper surfaces 70, 72 In addition, they each extend parallel to the first direction 52a, these fins being spaced from one another in this same first direction 52a, as well as in the transverse direction 60. They have an average height Hm, between the two walls. 70, 72, of the order of 4 to 8 mm. Their thickness E, in the transverse direction 60, has a preferably constant value preferably between 0.5 and 20 mm, while their length in the direction 52a has a preferential constant value between 1 and 40 mm. Furthermore, the spacings / pitch "P" between the fins 80 in each of the two directions 52a, 60, are for example of the order of 2 to 4 mm.
    The fins 80 can be arranged in staggered rows, with a density for example of around 3 fins / cm 2 . More generally, the density is for example between about 0.2 and 5 fins / cm 2 on average.
    In addition, each row comprises joining fins 80 'each connecting two main fins 80 directly consecutive in the transverse direction 60. The joining fins 80' are arranged substantially orthogonally to the main fins 80, being located flat on the wall d 'lower surface 70 or on the upper surface 72. More specifically, the fins of the same row are alternately in internal contact with the lower surface 70, and in internal contact with the upper surface 72. Each row forms thus, with all of its main fins 80 and its junction fins 80 ', a transverse structure of general shape in slots.
    Once produced, each die 50a ', 50b' is inserted into its associated passage 50a, 50b, from the base 34 of the blade made in one piece. The insertion is carried out via an introduction orifice 49a, 49b formed through this same blade root 34, and having a section substantially identical to that of the passages 50a, 50b. These introduction orifices 49a, 49b, visible in FIG. 2, then open into the fittings 66 leading to the circuit 56. A solution with plugs could also be used to partially close the introduction orifices 49a, 49b, after the insertion of the dies in the passages. In this case, the connectors 66 of smaller section would be connected to the plugs, at the level of a lubricant circulation channel formed through each of these plugs.
    Each heat conduction matrix 50a ', 50b' extends over all or part of the radial length of its associated passage 50a, 50b. Preferably, more than 80% of the radial length of each passage 50a, 50b is occupied by its corresponding matrix 50a ', 50b'.
    Alternatively, as visible in FIG. 3a, the fins 80 can be made in one piece by additive manufacturing with the lower and upper surfaces 70, 72 which they connect.
    Referring now to Figures 4 and 5, the bent area 54 is shown in more detail. This zone 54, in the general shape of a U and therefore ensuring a substantially 180 ° turn for the lubricant, extends between an end 50al of the first passage 50a, and an end 50bl of the second internal passage 50b. It is also delimited by the walls of lower surface 70 and upper surfaces 72, as well as by the solid central area 78. Its cross section can be reduced by going towards the head of the blade, but there is preferably no break in section between the ends of the branches of the U of the bent zone 54, and the ends 50al, 50bl of the interior passages. In the embodiment considered, the end 50al of the first passage 50a is a lubricant outlet end, and the end 50bl of the second interior passage 50b is a lubricant inlet end.
    The bent zone 54 extends along a curved generatrix 82 in the shape of a semicircle, or of oval shape, or of any other similar shape. The generator can here be likened to a center line of the bent area, according to the curvature thereof. One of the features of the invention resides in the fact that this bent zone 54 is internally equipped with one or more lubricant guides 84 which each extend substantially parallel to the curved generator 82, that is to say having a curvature similar to the general curvature of the bent zone 54.
    Each lubricant guide 84 has the shape of a wall having a first end facing the outlet end 50al of lubricant from the first passage 50a, as well as a second end facing the inlet end 50bl of lubricant of the second passage 50b. Each wall 84 extends for example over a length corresponding to 75 to 100% of the total length of the bent zone 54, in the direction of the curved generator 82.
    By being parallel, these guides 84 define between them lubricant passage channels 86 which therefore also extend parallel to the curved generator 82. Two channels 86 are also defined between the body of the aerodynamic part 32 and the two guides 84 located at the ends of the bent zone, in the direction 25. The spacing distances dl, d2, d3 between the guides 84 can vary, in particular so as to locally adapt to the thickness of the bent zone and ensure that the channels 86 all have substantially equivalent cross-sections in terms of area. This leads to better balancing of the lubricant flow rates in each of the passage channels 86, between the two interior passages 50a, 50b of the blade. By way of an indicative example such as that shown in FIG. 5, if the thickness of the area 54 between the lower and upper surfaces 70, 72 increases by going radially inwards, then the distances from spacing referenced dl, d2 and d3 are decreasing. Anyway, the density and spacing of the guides can be adapted according to the needs encountered, so as to best guide the lubricant between the two passages 50a, 50b. In this regard, it is noted that the number of lubricant guides 84 is for example of the order of 4 or 5, thus forming a number of channels 86 of 5 or 6. The thickness of each guide 84 is itself on the order of 1 to 5 mm. Depending on the number of channels desired, in particular depending on the mechanical constraints and / or the manufacturing method used, the thickness of the guides can be from 15 to 20 mm.
    In order to reinforce the mechanical strength of the bent zone and to increase the heat exchanges between the lubricant and the air, each guide 84 in the form of a wall connects the lower surface 70 to the upper surface 72. Even more preferably , the guides 84 are made in one piece with the other elements of the aerodynamic part 32, preferably by additive manufacturing.
    In addition, to improve the heat exchange by convection, each guide 84 may be in the form of several wall sections 84a spaced from one another by interruptions 84b, forming free spaces between these sections 84a. These interruptions 84b promote the wetting of the wall sections 84a, without however generating harmful disturbances on the flow of the lubricant.
    The section of these guides or guide sections may be of the regular slender type as shown in the figures, but may alternatively have oblong profiles, in diamond shape generally oriented in the direction of the flow, in NACA type profile with widening flare in the direction of flow, etc.
    For each guide 84, the number of sections 84a can be between 2 and 40. Preferably, the length of the wall sections 84a is greater than that of the interruptions 84b, even if an opposite solution could be adopted, without departing from the scope of the invention.
    To further improve the convection exchanges, it is preferably provided that the wall sections 84a of the different guides 84 which follow one another in the direction 25, are arranged in staggered rows as can be seen in FIG. 4.
    FIG. 5 represents lubricant guides 84 oriented substantially straight relative to the walls of the pressure side 70 and pressure faces 72, but to facilitate the additive manufacturing of the assembly, these guides can be inclined. This alternative is represented in FIG. 6, showing in cross section one of the guides 84 of the bent zone, with the wall inclined locally by an angle A relative to a normal 90 to each of the lower surfaces 70 and d 'upper surface 72. This angle A is for example between 20 and 60 °, and in particular between 30 and 55 °.
    The following figures show possible alternative embodiments, in which the guides 84 are of different shapes. In FIG. 7, the guides are continuous, that is to say that they do not have any interruptions. In FIG. 8, a single interruption 84b is provided per guide 84, preferably at the bottom of the U to facilitate the evacuation of the powders in the case of additive manufacturing. Finally, in FIG. 9, the guides 84 are provided with several interruptions and with several wall sections, with the sections 84a which are no longer staggered but distributed in rows.
    Returning to FIG. 2, during the operation of the turbomachine, the lubricant 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 marrying the first thermal conduction matrix, and the secondary flow marrying the external surface of the pressure and pressure surfaces 70, 72 carrying these fins. The lubricant, after having passed through the bent zone 54 in which it is cooled thanks in particular to the lubricant guides 84, enters the second passage 50b. In the latter, it undergoes similar cooling, always by heat exchange with the secondary air flow and by circulating in the second main direction of flow 52b, through the second thermal conduction matrix. Then, the cooled lubricant is extracted from the blade 24, and redirected by the closed circuit 56 to the elements to be lubricated.
    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. 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.
    Also, the invention is not limited to cases where the blade incorporates only two passages 50a, 50b, a greater number of passages can in fact be adopted, for example three, or four passages 50a, 50b, 50c as on the alternative embodiment shown in Figure 10. In this case, bent areas 54 according to the invention are preferably arranged between the passages 50a, 50b, 50c directly consecutive in the direction of the lubricant flow.
    权利要求:
    Claims (10)
    [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 an aircraft turbomachine with double flow, the directing vane comprising a foot (34), a head (36), as well as an aerodynamic flow straightening part (32) arranged between the foot and the blade head, said aerodynamic part of the blade having a first interior passage (50a) for cooling lubricant in which are arranged heat transfer means (80), the first interior passage (50a) extending in a first main direction (52a) of lubricant flow from the foot (34) to the head (36) of the blade, said first interior passage (50a) being partly delimited by a lower surface wall (70) and by an upper surface wall (72) of the blade, the aerodynamic part (32) also comprising a second internal passage ( 50b) cooling of lubricant in which heat transfer means are arranged (80), the second interior passage (50b) extending in a second main direction (52b) of flow of the lubricant going from the head (36) to the foot (34) of the blade, said second interior passage ( 50b) being partly delimited by the lower surface wall (70) and by the upper surface wall (72) of the blade, and characterized in that the aerodynamic part (32) comprises a bent zone (54) connecting a end (50al) of the first interior passage (50a) to one end (50bl) of the second passage (50b), the bent zone extending along a curved generatrix (82) and being partially delimited by the wall of lower surface (70) and through the upper surface wall (72) of the blade, and in that the bent zone (54) comprises at least one lubricant guide (84) arranged between the lower surface wall (70) and the upper surface wall (72) of the blade, and each extending substantially parallel to the curved generator (82) of the bent zone (54).
    [2" id="c-fr-0002]
    2. Guiding vane according to claim 1, characterized in that each lubricant guide (84) is a wall having a first end opposite the end (50al) of the first interior passage (50a), as well as a second end opposite the end (50bl) of the second interior passage (50b).
    [3" id="c-fr-0003]
    3. Guiding vane according to claim 2, characterized in that each lubricant guide (84) comprises, between its first and its second end, at least one wall interruption (84b) forming a space separating two wall sections (84a) .
    [4" id="c-fr-0004]
    4. Guide vane according to claim 3, characterized in that each lubricant guide (84) comprises, between its first and its second end, a plurality of wall interruptions (84b) each forming a space separating two sections of wall ( 94a).
    [5" id="c-fr-0005]
    5. Directing vane according to claim 4, characterized in that for any two lubricant guides (84) and directly consecutive in a span direction (25) of the blade, the wall sections (84a) are arranged in staggered rows .
    [6" id="c-fr-0006]
    6. Guide vane according to any one of claims 3 to 5, characterized in that for each lubricant guide (84), the number of wall sections (84a) is between 2 and 40.
    [7" id="c-fr-0007]
    7. Guide vane according to any one of the preceding claims, characterized in that the lubricant guides (84) define between them lubricant passage channels (86), and in that the guides are spaced from one another according to spacing distances (dl, d2, d3) of which at least two of them are different.
    [8" id="c-fr-0008]
    8. Guide vane according to any one of the preceding claims, characterized in that each lubricant guide (84) is a wall connecting the lower surface wall (70) to the upper surface wall (72), and in that in any cross section of the bent zone (54), said wall forming the lubricant guide is inclined locally with respect to a normal (90) to each of the lower surface (70) and upper surface (72) walls.
    5
    [9" id="c-fr-0009]
    9. Guide vane according to any one of the preceding claims, characterized in that the number of lubricant guide (84) is between 1 and 10.
    [10" id="c-fr-0010]
    10. Aircraft turbomachine (1), preferably a turbojet,
    10 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, said vanes (24) preferably having a structural function.
    S.61459
    0 DDDDDO
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    法律状态:
    2017-10-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-06-01| PLSC| Publication of the preliminary search report|Effective date: 20180601 |
    2018-10-24| PLFP| Fee payment|Year of fee payment: 3 |
    2019-10-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-10-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-10-20| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1661643|2016-11-29|
    FR1661643A|FR3059353B1|2016-11-29|2016-11-29|AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN|FR1661643A| FR3059353B1|2016-11-29|2016-11-29|AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN|
    CA3044490A| CA3044490A1|2016-11-29|2017-11-28|Aircraft turbomachine exit guide vane comprising a bent lubricant passage of improved design|
    EP17811663.8A| EP3548706B1|2016-11-29|2017-11-28|Aircraft turbomachine exit guide vane comprising a bent lubricant passage of improved design|
    BR112019010314-7A| BR112019010314A2|2016-11-29|2017-11-28|outlet guide blade for an aircraft turbo engine comprising a curved lubricant passage zone having an improved design|
    US16/462,264| US11125091B2|2016-11-29|2017-11-28|Aircraft turbo machine exit guide vane comprising a bent lubricant passage of improved design|
    RU2019119838A| RU2747652C2|2016-11-29|2017-11-28|Aircraft turbomachine outlet guide blade containing a curved lubricant channel of improved design|
    PCT/FR2017/053265| WO2018100278A1|2016-11-29|2017-11-28|Aircraft turbomachine exit guide vane comprising a bent lubricant passage of improved design|
    JP2019527552A| JP2020501066A|2016-11-29|2017-11-28|Aircraft turbomachine exit guide vanes include an improved design of flexed lubricant passages|
    CN201780073394.5A| CN109996933B|2016-11-29|2017-11-28|Aircraft turbine outlet guide vane comprising a curved lubricant duct of improved design|
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