• 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 an aircraft turbomachine, the aerodynamic part (32) of the vane being defined by an upper surface body (32a) and a lower surface body (32b), the part ( 32) comprising an interior passage (50a) for cooling the lubricant equipped with studs (80a, 80b) flow disrupters, among which a first series of studs (80a) produced integrally with the upper surface body (32a) , and a second series of studs (80b) produced integrally with the lower surface body (32b), the studs of the second series defining between them a second inter-stud space (84b) penetrated by the studs (80a ) of the first series while a first inter-stud space (84a) is penetrated by the studs (80b) of the second series. In addition, the end of the studs (80a) is located at a distance from the lower surface body (32b), just as the end of the studs (80b) is located at a distance from the upper surface body (32a).
    公开号:FR3075256A1
    申请号:FR1762405
    申请日:2017-12-19
    公开日:2019-06-21
    发明作者:Mohammed-Lamine BOUTALEB；Amelie Argie Antoinette Chassagne；Dimitri Daniel Gabriel Marquie
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    OUTPUT DIRECTIVE VANE FOR AIRCRAFT TURBOMACHINE, INCLUDING A LUBRICANT COOLING PASS EQUIPPED WITH FLOW DISTURBORING PADS
    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. It also relates to a method of manufacturing such a blade.
    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 3,046,811.
    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 studs intended to disturb the flow of lubricant and to increase the wetted surface, in order to ensure better heat exchange. Thus, the higher the thermal performance sought, the longer and more costly the manufacture, especially when the blade has a long length.
    Consequently, there remains a need to arrive at a design providing an efficient thermal function, while facilitating the manufacture of this blade with integrated exchanger.
    STATEMENT OF THE INVENTION
    To respond at least partially to this need, the invention firstly relates to a guide vane intended to be arranged in all or part of an air flow from 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, the blade comprising an upper surface body defining at least part of a upper surface of the aerodynamic part, as well as a lower surface body defining at least a part of a lower surface of the aerodynamic part, the latter comprising at least one internal lubricant cooling passage equipped with studs flow disrupters and delimited at least in part by the lower and upper bodies fixed to one another.
    According to the invention, a first series of studs is produced in one piece with the upper surface body, the studs of the first series defining between them a first inter-stud space, a second series of studs is made of a integral with the lower surface body, the studs of the second series defining between them a second inter-stud space penetrated by the studs of the first series while the first interplot space is penetrated by the studs of the second series, and finally , the end of the studs of the first series is located at a distance from the lower surface body, just as the end of the studs of the second series is located at a distance from the upper surface body.
    Thus, the invention cleverly provides for an interpenetration of the two series of studs arranged respectively on the upper and lower surface bodies, which leads to increasing the heat exchanges without requiring complex manufacture. Indeed, due to the interpenetration of studs specific to the invention, the disturbances generated by these studs cause the lubricant to also move in the direction of the thickness of the blade, which increases the wetted surface as well as the convection phenomenon. Furthermore, the studs can be produced in a conventional manner on each of the two bodies of the blade, for example by simple machining, or even by molding.
    In other words, the proposed invention contrasts with the previous embodiments in that it provides studs made on the two bodies which form the blade, and which interpenetrate in order to further promote disturbances in the flow of lubricant. circulating in the interior passage.
    The invention preferably provides at least any one of the following optional characteristics, taken individually or in combination.
    Each of the first and second series of plots is in the form of a matrix defining rows and columns of plots. This particular arrangement facilitates the manufacture of the studs, in particular when they are produced by machining.
    The pads of the first and second series of pads are then preferably arranged in staggered rows. Alternatively, they can for example be arranged so as to define an alternation of columns produced exclusively with studs from the first series, and columns produced exclusively with studs from the second series.
    According to another embodiment, within each of the first and second series of studs, the studs are arranged in staggered rows. It is then preferably made so that the studs of the first and second series of studs are arranged so as to define together a matrix forming rows and columns of studs, each of the rows and columns of the matrix being produced by the alternation of plots of the first series and plots of the second series.
    Whatever the embodiment envisaged, each stud preferably has a section of generally circular, oblong, square or rectangular shape.
    The invention also relates to an aircraft turbomachine, preferably a turbojet engine, comprising a plurality of guide vanes like that described above, arranged downstream or upstream of a fan of the turbomachine.
    Finally, the subject of the invention is a method of manufacturing such a guide blade, comprising a step of producing the studs by machining the upper and lower 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, more detailed, of an outlet guide vane of the turbojet engine shown in the previous figure, according to a first preferred embodiment of the invention;
    - Figure 2a is a sectional view taken along line lla-lla of Figure 2;
    - Figure 2b is a partial and enlarged view of that of Figure 2a;
    - Figure 3 is an enlarged perspective view of part of an upper body of the outlet guide vane shown in Figures 2 to 2b;
    - Figure 4 is an enlarged perspective view of a lower surface body of the outlet guide vane shown in Figures 2 to 2b;
    - Figure 5 shows a partial sectional view along the line V-V of Figure 2a, orthogonally crossing the flow disturbing pads;
    - Figure 5a is a view similar to that of Figure 5, with the studs arranged according to an alternative embodiment; and
    - Figure 6 is a view similar to that of Figure 5, with the studs arranged according to a second preferred embodiment of the invention.
    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 duct 18 is delimited radially outwards in part by an external 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 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 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 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 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 5, one of the outlet guide vanes 24 will be described, according to a first preferred embodiment of the invention. It is noted that the invention which will be described 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 can be of strictly radial orientation as in FIG. 1, or else be slightly inclined axially as shown in the FIG.
    2. In all cases, it is preferably straight in side view as shown in FIG. 2, extending in a direction of span 25.
    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 comprises a foot 34 and a head 36 respectively.
    The foot 34 is used for fixing the blade 24 on the housing of the low pressure compressor, 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. Alternatively, the platforms 40 can be added between the blades 24.
    The aerodynamic part 32 of the blade is preferably manufactured in two separate parts, then fixedly attached to one another. It is first of all an upper body 32a, which includes not only a large part of the aerodynamic part 32, but also the foot 34, the head 36 and the platforms 40. This body 32a is made of '' in one piece, for example by foundry then machining. The other part is formed by a lower face body 32b, in the form of a cover closing the body 32a fixed to the latter by a conventional technique such as welding, brazing or bonding. The intrados body 32b can also be produced in one piece using conventional techniques, for example also by foundry and then machining.
    In this first 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 25. More precisely, it s 'Acts of a first interior passage 50a of lubricant cooling, 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, a second interior passage 50b for cooling the lubricant is provided, 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. The first passage 50a is therefore intended to be crossed radially outward 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 °, corresponding to a hollow formed in the aerodynamic part 32. 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 aerodynamic part 32. To fluidly connect one to the other outside of 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 56, shown diagrammatically by the element 56 in FIG. 2. This circuit 56 notably comprises a pump (not shown), making it possible to apply to the lubricant 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 and the elbow 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 optimize the best 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 d Attack 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 only a single internal cooling passage, without departing from the scope of the invention. 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 upper surface body 32a comprises, at the aerodynamic part 32, an upper surface 72, a solid area 74 located near the trailing edge 62, a solid area 76 located near the leading edge 64, as well as a central solid zone 78. These three zones 74, 76, 78 are in contact with the lower surface body 32b, and the two zones 74, 76 have recesses for the support and the fixing of this lower surface body 32b. The central zone 78 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 aerodynamic part 32, according to the span direction 25.
    The first passage 50a is formed between the solid zones 74, 78, while the second passage 50b is formed between the solid zones 76, 78. The passages 50a, 50b extend transversely in the direction 60 with a variable thickness between the two bodies 32a, 32b. The maximum thickness of these passages can be of the order of a few millimeters. Alternatively, the passages 50a, 50b could have a constant thickness, without departing from the scope of the invention.
    The lower surface body 32b defines the lower surface 70, or a large part thereof.
    The two interior passages 50a, 50b for cooling the lubricant have the particularity of integrating flow-disturbing studs. These studs are provided on the upper surface body 32a as well as on the lower surface body 32b, and interpenetrate within the passages 50a, 50b, as will be detailed below.
    The arrangement and the shape of the studs are substantially identical or similar in the two passages 50a, 50b. They are also provided in the same densities, although it could be otherwise, without departing from the scope of the invention. Consequently, only the studs of the first interior passage 50a will now be described, but it should be understood that this description is also applicable by analogy to the studs of the second interior passage 50b. Furthermore, it is noted that the elbow 54 defines an interior space which is preferably free of studs.
    In the first passage 50a, a first series of studs 80a is first provided made in one piece with the upper surface body 32a. For the formation of these studs 80a, it is preferable to machine the surface of the body 32a opposite the surface of the upper surface 72. The studs 80a are thus produced projecting in the direction of the lower surface body 32b, being substantially orthogonal to direction 52a. The height of the pad in the direction of the body 32b is for example of the order of one or more millimeters. In at least one zone of the passage 50a, and preferably in the entirety of the latter, the studs 80a are provided in a density for example of approximately 3 studs / cm 2 . More generally, the density is for example between about 1 and 5 pads / cm 2 on average.
    The studs 80a can adopt a section of generally rectangular shape as shown in FIG. 5, or else of oblong shape as shown in FIG. 3. This oblong shape is preferred, in particular when its major axis 81 is arranged parallel to the direction 52a . However, other shapes can be adopted for the section which is preferably substantially identical over the entire height of the stud, such as for example a generally square shape.
    In this first preferred embodiment, the first series of pads 80a is in the form of a matrix defining first columns of pads CPI, as well as first rows of pads LP1. The columns of pads CPI follow one another in the direction 60, while the rows of pads LP1 succeed one another in the direction 52a. The rows and the columns are preferably substantially straight with regular spacings inherent in the matrix shape, which allows simple machining of the studs 80a, by making parallel and perpendicular passes between them.
    In the passage 50a, several tens of lines LP1 of pads 80a thus succeed one another in the first direction 52a. In addition, a number of CPI columns can be provided between 2 and 8, for example 4.
    Finally, it is noted that the pads 80a of the first series define between them a first inter-pad space 84a.
    With regard to the lower surface body 32b, a similar embodiment is carried out. Indeed, in the first passage 50a, a second series of studs 80b is also provided, made in one piece with the lower surface body 32b. For the formation of these studs 80b, it is preferable to machine the surface of the body 32b opposite the lower surface 70. The studs 80b are thus produced projecting in the direction of the upper surface body 32a, being substantially orthogonal to direction 52a. The height of the stud, the shape and the density are preferably identical or similar to those of the first series of studs 80a.
    The second series of pads 80b is also in the form of a matrix defining second columns of pads CP2, as well as second rows of pads LP2. The columns of pads CP2 follow one another in the direction 60, while the rows of pads LP2 succeed one another in the direction 52a. The number, the shape, the composition as well as the spacings of the rows and of the columns are preferably identical to those of the first series of studs 80a.
    Finally, it is noted that the pads 80b of the second series define between them a second inter-pad space 84b, referenced in FIG. 2a.
    One of the other particularities of the invention resides in the fact that the studs 80a, 80b interpenetrate, that is to say that the studs 80a of the first series penetrate into the second inter-stud space 84b, of even that the pads 80b of the second series enter the first inter-pad space 84a. The cooperation between the two bodies 32a, 32b is retained so that all of the studs 80a, 80b, formed by the first and second series, are arranged in staggered rows for better disturbance of the lubricant flow and increased heat exchange. This staggered arrangement is shown in FIG. 5. It is easily obtained by alternating first and second columns CPI, CP2, as well as by alternating first and second lines LP1, LP2. To do this, it is sufficient to offset the matrix of studs 80b (having the least tight hatching) from the matrix of studs 80a (having the tightest hatching), according to a value of half a step in the direction 52a, as well as a value of a half step in direction 60. In this regard, it is noted that within the matrices, the step between the columns may differ from the step between the lines, or else this step may be identical.
    As shown in Figures 2a and 2b, the studs 80a, 80b do not contact the opposite body 32a, 32b. In other words, the end of the studs 80a of the first series is located at a distance from the surface of the body 32b from which the studs 80b of the second series protrude, as does the end of these studs 80b is located at a distance from the surface of the body 32a from which the studs 80a of the first series protrude. These distances “D” of spacing between the studs and their opposite body have been referenced in FIG. 2b. These distances are preferably identical, for example from 0.5 to 3 mm. Consequently, the interpenetration of the pads which results therefrom makes it possible to further promote heat exchanges, since the lubricant is forced to also move in the direction of the thickness of the blade when it flows from the foot towards the head, which increases the wetted surface.
    According to an alternative embodiment shown in FIG. 5a, the relative arrangement of the two matrices of studs 80a, 80b differs compared to that of FIG. 5. In fact, if there is always a half-step offset between the two dies in the transverse direction 60, there is however no longer any offset in the direction of flow flow 52a. Consequently, the pads 80a, 80b of the first and second series of pads are arranged so as to define an alternation between first columns CPI each carried out exclusively with pads 80a of the first series, and second columns CP2 each carried out exclusively with studs 80b of the second series. On the other hand, the first and second lines LP1, LP2 are grouped two by two so that within the same line LP of this set of studs 80a, 80b also in the form of a matrix, the studs 80a of the first series are arranged alternately with the pads 80b of the second series.
    Finally, according to a second embodiment shown in FIG. 6, the studs 80a of the first series are made in staggered rows, just as the studs 80b of the second series are also made in staggered rows. Once the lower surface body is assembled on the upper surface body, the set of studs 80a, 80b forms a matrix with columns of studs CP ', and rows of studs LP'. Each line LP 'is formed by the alternation between pads 80a and pads 80b, just as each column CP' is formed by the alternation between pads 80a and pads 80b.
    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 studs 80a, 80b of the first passage 50a, and the secondary flow conforming to the exterior 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.
    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, the technical characteristics specific to each of the embodiments described above can be combined with one another, without departing from the scope of the invention. Finally, it is noted that in the non-illustrated case of the inlet guide vanes to straighten the air flow upstream of the blower, these blades are arranged throughout the air flow of the blower around a cone d non-rotating air inlet, the feet of the blades then being connected to this fixed air inlet cone.
    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, the blade comprising an upper surface body (32a) defining at least part of a upper surface (72) of the aerodynamic part (32), as well as a lower surface body (32b) defining at least part of a lower surface (70) of the aerodynamic part (32), that -this comprising at least one interior passage (50a, 50b) for cooling the lubricant equipped with studs (80a, 80b) flow disrupters and delimited at least in part by the lower and upper surface bodies fixed one on the other, characterized in that a first series of studs (80a) is made in one piece with the upper surface body (32a), the studs of the first challenge series connecting between them a first inter-stud space (84a), in that a second series of studs (80b) is made in one piece with the lower surface body (32b), the studs of the second series defining between them a second inter-stud space (84b) penetrated by the studs (80a) of the first series while the first inter-stud space (84a) is penetrated by the studs (80b) of the second series, and in that the end of the studs (80a) of the first series is located at a distance from the lower surface body (32b), just as the end of the studs (80b) of the second series is located at a distance from the upper surface body (32a) ).
    [2" id="c-fr-0002]
    2. Dawn according to claim 1, characterized in that each of the first and second series of studs (80a, 80b) is in the form of a matrix defining rows and columns of studs (LP1, LP2, CPI, CP2).
    [3" id="c-fr-0003]
    3. Dawn according to claim 2, characterized in that the studs (80a, 80b) of the first and second series of studs are staggered.
    [4" id="c-fr-0004]
    4. Dawn according to claim 2, characterized in that the studs (80a, 80b) of the first and second series of studs are arranged so as to define an alternation of columns (CPI) produced exclusively with studs (80a) of the first series, and columns (CP2) produced exclusively with studs (80b) of the second series.
    [5" id="c-fr-0005]
    5. Dawn according to claim 1, characterized in that within each of the first and second series of studs (80a, 80b), the studs are staggered.
    [6" id="c-fr-0006]
    6. Dawn according to claim 5, characterized in that the studs (80a, 80b) of the first and second series of studs are arranged so as to define together a matrix forming rows (LP ') and columns (CP') of studs, each of the rows and columns of the matrix being produced by alternating studs (80a) from the first series and studs (80b) from the second series.
    [7" id="c-fr-0007]
    7. Dawn according to any one of the preceding claims, characterized in that each stud (80a, 80b) has a generally circular, oblong, square or rectangular shape.
    [8" id="c-fr-0008]
    8. Dawn according to any one of the preceding claims, characterized in that each stud (80a, 80b) has a generally oblong cross-section, with the major axis (81) arranged parallel to a main direction of flow of the lubricant ( 52a) in the cooling passage (50a).
    [9" id="c-fr-0009]
    9. 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 .
    [10" id="c-fr-0010]
    10. A method of manufacturing a guide blade (24) according to any one of claims 1 to 8, characterized in that it comprises a step of producing the studs (80a, 80b) by machining the upper surface bodies and lower surface (32a, 32b).
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    EP1413771B1|2007-05-23|Casing, compressor, turbine and gas turbine engine having such casing
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    同族专利:
    公开号 | 公开日
    EP3508701A1|2019-07-10|
    FR3075256B1|2020-01-10|
    EP3508701B1|2021-03-03|
    US10883382B2|2021-01-05|
    US20190186293A1|2019-06-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4914904A|1988-11-09|1990-04-10|Avco Corporation|Oil cooler for fan jet engines|
    EP1630358A2|2004-08-26|2006-03-01|United Technologies Corporation|A gas turbine engine frame with an integral fluid reservoir and air/fluid heat exchanger|
    US8616834B2|2010-04-30|2013-12-31|General Electric Company|Gas turbine engine airfoil integrated heat exchanger|
    FR2989110A1|2012-04-05|2013-10-11|Snecma|Stator blade for use in blade adjustment outlet of e.g. turbojet of aircraft, has blade parts arranged against each other to define passages for flow of airflow, and circulation unit for circulating fluid to be cooled by airflow|
    EP2783075A1|2011-11-25|2014-10-01|Siemens Aktiengesellschaft|Airfoil with cooling passages|
    US9470095B2|2012-04-24|2016-10-18|United Technologies Corporation|Airfoil having internal lattice network|
    FR3046811B1|2016-01-15|2018-02-16|Snecma|DAUGHTER OUTPUT DIRECTOR FOR AIRCRAFT TURBOMACHINE, HAVING AN IMPROVED LUBRICANT COOLING FUNCTION|
    FR3054263B1|2016-07-20|2018-08-10|Safran Aircraft Engines|INTERMEDIATE CASING OF AIRCRAFT TURBOMACHINE MADE OF ONE PIECE OF FOUNDRY WITH A LUBRICANT CHANNEL|
    FR3063767B1|2017-03-13|2019-04-26|Safran Aircraft Engines|OUTPUT DIRECTOR FOR AIRCRAFT TURBOMACHINE WITH IMPROVED LUBRICANT COOLING FUNCTION|
    FR3064682B1|2017-03-31|2019-06-14|Safran Aircraft Engines|INTERMEDIATE CASE FOR AIRCRAFT TURBOMACHINE COMPRISING A LUBRICANT PASSING BIT CONNECTED TO A CARTER BOLT BY A CONNECTING PART|
    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|
    FR3081912B1|2018-05-29|2020-09-04|Safran Aircraft Engines|TURBOMACHINE VANE INCLUDING AN INTERNAL FLUID FLOW PASSAGE EQUIPPED WITH A PLURALITY OF DISTURBING ELEMENTS WITH OPTIMIZED LAYOUT|
    法律状态:
    2018-11-26| PLFP| Fee payment|Year of fee payment: 2 |
    2019-06-21| PLSC| Publication of the preliminary search report|Effective date: 20190621 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 3 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-11-18| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1762405A|FR3075256B1|2017-12-19|2017-12-19|OUTPUT DIRECTIVE VANE FOR AIRCRAFT TURBOMACHINE, INCLUDING A LUBRICANT COOLING PASS EQUIPPED WITH FLOW DISTURBORING PADS|
    FR1762405|2017-12-19|FR1762405A| FR3075256B1|2017-12-19|2017-12-19|OUTPUT DIRECTIVE VANE FOR AIRCRAFT TURBOMACHINE, INCLUDING A LUBRICANT COOLING PASS EQUIPPED WITH FLOW DISTURBORING PADS|
    US16/222,020| US10883382B2|2017-12-19|2018-12-17|Outlet guide vane for aircraft turbomachine, comprising a lubricant cooling passage equipped with flow disturbance studs|
    EP18213732.3A| EP3508701B1|2017-12-19|2018-12-18|Outlet guide vane for aircraft turbine engine, comprising a lubricant cooling passage equipped with flow interruption pads|
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