• 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 an intermediate case for a turbofan aircraft turbomachine comprising, associated with at least one of its vanes (24), at least one lubricant passage nozzle (88a) having a lubricant passage (98a). extending along a passage axis (134a) and opening into the lubricant line (55a). Also, the passage axis (134a) and the orifice axis (140a) are spaced apart from each other in a circumferential direction (91), and a connecting piece (125a) traversed by a conduit of connector (142a) is partially housed in the blade root (34) so as to communicate the connecting conduit (142a) with the lubricant passage (124a), and partially housed in a bit holder (108a) or in the lubricant nozzle (88a), so as to communicate the coupling duct (142a) with the lubricant passage (98a) of the nozzle.
    公开号:FR3064682A1
    申请号:FR1752791
    申请日:2017-03-31
    公开日:2018-10-05
    发明作者:Cedric ZACCARDI；Laurent Jablonski；Christophe Paul Jacquemard；Christophe Marcel Lucien Perdrigeon
    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 the intermediate casing integrating outlet guide vanes arranged in the secondary air flow of the turbomachine. Such vanes, also called OGV (from the English “Outlet Guide Vane”), are provided to straighten the air flow at the outlet of the blower.
    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 accessories box (from AGB for "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, makes it possible in particular 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. Furthermore, the reduction / elimination of ACOC exchangers can allow reductions in engine mass.
    The fact of associating with at least some of these blades a heat exchanger function requires the provision of means of arrival and / or outlet of lubricant cooperating with the blade, in particular in the hub of the intermediate casing. However, this environment is already heavily congested by the presence of other easements, and the installation of lubricant pipes as well as their fluid connections to the blades prove to be complicated. This problem is all the more important when the outlet guide vanes are connected near the flow separation nozzle, in a narrow zone where the space available in the hub is extremely limited. Thus, there is a need to optimize the intermediate casings incorporating such a function, in particular so as to reduce the size of the fluid connections, while facilitating the manufacture of the casing, its assembly / disassembly, as well as maintenance operations.
    STATEMENT OF THE INVENTION
    To respond at least partially to this need, the invention firstly relates to an intermediate casing for an aircraft turbomachine with double flow, comprising a hub, an outer shroud as well as outlet guide vanes mounted at their ends on the hub and on the outer shroud, at least some of said outlet guide vanes each having a heat exchanger function and comprising a lubricant passage intended to be cooled by the secondary flow conforming to an exterior surface of the outlet guide vane, a foot of the outlet guide vane comprising at least one lubricant passage orifice extending along an orifice axis (140a, 140b) and communicating with a lubricant line integral with the hub.
    According to the invention, the intermediate casing further comprises, associated with at least one of the outlet guide vanes, at least one lubricant passage nozzle having a lubricant passage extending along a passage axis and opening into the lubricant line, the passage axis and the orifice axis being spaced from one another in a circumferential direction of the casing. In addition, a connecting piece traversed by a connecting duct is partly housed in the blade root so as to communicate the connecting conduit with the lubricant passage orifice of the blade root, and on the other hand partially housed in a nozzle holder device or in the lubricant passage nozzle, so as to make the connection conduit communicate with the lubricant passage of the nozzle.
    The invention is first of all remarkable in that it allows a reduced bulk in the radial direction of the casing, thanks to the circumferential offset between the nozzle and the lubricant passage orifice of the blade root. The implantation advantageously becomes easy, even near the flow separation nozzle.
    In addition, the invention provides a clever solution to the search for optimization mentioned above. In fact, the connecting piece, in addition to being easy to manufacture, for example by machining, constitutes an intermediate connecting piece between the blade root and the pipe carried by the hub, thus offering flexibility in mounting. The positioning of the connecting piece can effectively be adjusted, to a certain extent, relative to the blade and to the hub, so that this connecting piece is positioned at best relative to these two elements. The flexibility provided by this arrangement not only facilitates assembly / disassembly, but also limits hyperstatism in the assembly of the blade. This proves to be advantageous in particular when the blade has an additional structural function of passage of forces, in the direction of an engine attachment on the aircraft. Indeed, in this case, the forces then pass mainly through the fastenings of the blade on the hub, and not through the lubricant passage nozzles.
    Also, the proposed design allows the blade to be easily assembled and disassembled, as well as the maintenance of each end piece is made easy in the event of damage to the latter.
    The invention also has at least one of the following optional features, taken individually or in combination.
    Said connecting piece adopts a generally elongated shape, oriented substantially in the circumferential direction of the housing. It can for example be a connecting piece in the form of a pin.
    Preferably, said connecting piece has a ball joint connection with said blade root, and / or with the bit holder device, and / or with the tip. Alternatively, a connection of the cylinder-cylinder type can be implemented, namely a connection of the pivot-sliding type. In this case, the joint present between these two elements is likely to compress to allow a slight swiveling, and, by this means, a backlash.
    Preferably, said connecting piece is secured to the root of the blade, or on the hub of the intermediate casing, or even on the lubricant pipe, and preferably on one ear of a complementary nozzle provided on the lubricant pipe, l 'complementary nozzle cooperating with the lubricant passage nozzle.
    Preferably, the passage axis and the orifice axis are substantially parallel to each other, and orthogonal to a conduit axis of said connecting conduit.
    Preferably, the bit-holder device comprises a main body fixed on the lubricant line as well as a cowling fixed on the main body, and the connecting piece is housed in a housing formed jointly by the main body and the cowling.
    The main body and the end piece are for example made in one piece, or secured to one another by a welded or screwed connection. For reasons of ease of maintenance, the connection used is preferably removable.
    Preferably, the casing comprises, associated with said blade, at least one secondary vein reconstruction platform, said platform being fixed on the hub and arranged radially outward relative to the blade root and to the bit holder device.
    Preferably, the tip-holder device is arranged between two directly consecutive vanes of said casing, this tip-holder device carrying a first and a second tip for lubricant passage, the two tips:
    - Being associated respectively with one and the other of the two directly consecutive vanes via a first and a second connecting piece; and
    - cooperating respectively with a first and a second lubricant line, these being preferably dedicated to the distribution and collection of lubricant, respectively.
    In this case, the integration is further improved due to the arrangement of the bit holder device between two blades, in the circumferential direction of the housing.
    The subject of the invention is also a method of assembling an intermediate casing as described above, comprising the following steps:
    - mounting the main body of the bit holder device on the pipe (s), so that each tip cooperates with its associated pipe;
    - Installation of each connecting piece on the main body and in the blade root, then fixing of this connecting piece on its associated pipe; and
    - fixing of the cover on the main body so as to enclose each connecting piece between the main body and the cover of the bit holder device.
    Finally, the subject of the invention is an aircraft turbomachine with a double flow comprising such an intermediate casing, arranged downstream of a fan of this turbomachine.
    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 a fan part and the intermediate casing shown in the previous figure, according to a preferred embodiment of the invention;
    - Figure 3 shows an enlarged view, even more detailed, of a part of the intermediate casing shown in the previous figure;
    - Figure 3a shows a sectional view taken along the line IHall la of Figure 3;
    - Figure 4 shows a sectional view taken along the line IV-IV of Figure 3;
    - Figure 4a shows a sectional view taken along the line IVaIVa of Figure 3;
    - Figure 5 shows an alternative embodiment for cooperation between a lubricant passage nozzle and a lubricant line integral with the intermediate casing hub;
    - Figure 6 shows a sectional view taken along the line VI-VI of Figure 5;
    - Figure 7 shows a view similar to that of Figure 5, according to yet another alternative embodiment;
    - Figure 8 shows a purified view from below of that of Figure 3;
    - Figure 9 is a view similar to that of Figure 3a, according to an alternative embodiment;
    - Figure 10 is a view similar to that of Figure 3a, according to yet another alternative embodiment;
    - Figure 11 is a view similar to that of Figure 3a, according to yet another alternative embodiment; and
    FIGS. 12a to 12f represent different stages of a method of assembling the casing shown in FIG. 11.
    DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
    Referring to Figure 1, there is shown a turbofan 1 with double flow and double body, for example 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 of this. 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 therefore being divided at the level of a separation nozzle 21. As is known to those skilled in the art, the secondary stream 18 is delimited radially outwards in part by an outer ferrule 23, preferably metallic, extending towards behind the fan casing 9. As will be described below, it is the outer shell 23 of an intermediate casing 25 located downstream of the flow separation nozzle 21.
    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, actuator relief valve, 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 outlet guide vanes 24 (or OGV, from the English “Outlet Guide Vane”). These stator vanes 24 connect the outer shroud 23 to a hub 26 of the intermediate casing, the latter being thus formed by the outer shroud 23, the outlet guide vanes 24 and the hub 26 being located in the downstream extension of the separation spout 21.
    The blades 24 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 blades 24 can also fulfill a structural function, as is the case in the examples of which are currently 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 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.
    This functionality is shown diagrammatically in FIG. 2 showing only one of the blades 24, but it should be understood that the invention as it will be described below can be applied to all the blades 24 of the stator crown centered on the axis 3, or only some of these blades.
    The blade 24 can be of strictly radial orientation, or alternatively it can be inclined axially as shown in FIG. 2. In all cases, it is preferably straight in side view as shown in FIG. 2, in s extending in a broad 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. It has a leading edge 32a and a trailing edge 32b. On either side of this aerodynamic part 32 which serves 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 hub 26 as will be detailed below, while the head is used for fixing the same blade on the outer shell 23 extending the fan casing 9. In addition , at the level of the foot and of the blade head, platforms are arranged so as to reconstitute the secondary vein 18 between the blades 24. At the level of the foot 34, these are two platforms 40a, 40b arranged at the side and other of the aerodynamic part 32 of the blade, and reconstituting the secondary vein 18 by being arranged so as to cover the foot, that is to say by being arranged radially outward relative to the foot of dawn.
    In the embodiment shown in this FIG. 2, the aerodynamic part 32 is equipped with two interior lubricant passages 50a, 50b substantially parallel to one another, and parallel to the span direction 25. More precisely, it it is a first lubricant passage 50a 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 passage of lubricant 50b 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. 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 one or more elbows 54 at 180 °, corresponding to a hollow made in the aerodynamic part 32. However, it can be provided for several round trips of fluid within the dawn, without departing from the scope of the invention.
    Alternatively, the directions of flow can be reversed. Also, it is possible to provide two independent lubricant passages inside the blade, and not connected to each other within it. According to yet another possibility, the blade can be equipped with a single passage of lubricant, for flow in one direction or the other.
    Returning to the embodiment shown in FIG. 2, it is noted that the internal radial ends of the two passages 50a, 50b communicate with lubricant lines 55a, 55b integrated into the hub 26 of the intermediate casing. These pipes 55a, 55b, spaced axially from each other, form part of a 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 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 .
    Thus, during the operation of the turbomachine, the lubricant is introduced into the first interior passage 50a via one of the two pipes 55a, 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 and the secondary air flow 58 conforming to the exterior surface of the aerodynamic part 32 of the blade. 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 58 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 to the elements to be lubricated, after having passed through the other pipe 55b.
    With reference now to FIGS. 3 to 4a, there will be described more precisely the hub 26 of the intermediate casing, and its cooperation with the blades
    24.
    The hub 26 includes an upstream flange 62 as well as a downstream flange 64 centered on the axis 3, and interconnected by radial arms 66. Each flange ends radially outwards by a track 62a, 64a for fixing the outlet guide vanes 24. In this respect, each blade has, at its foot 34 and near the leading edge 32a, an upstream fixing plate 70 pierced with upstream fixing holes 72, for example two holes through which fixing elements of the screw type 74. Thus, the screws 74 pass through the upstream fixing holes 72 and come to be screwed into tapped holes 76 of the track 62a, in order to press the plate 70 against the latter.
    Similarly, each blade comprises, at its foot 34 and near the trailing edge 32b, a downstream fixing plate 80 pierced with downstream fixing holes 82, for example two holes crossed by fixing elements of the screw type 84. Thus, the screws 84 pass through the downstream fixing holes 82 and are screwed into threaded holes 86 of the track 64a, in order to press the plate 80 against the latter.
    The plates 70, 80 are preferably made in one piece with the aerodynamic part of the blade, and with the foot 34 of which they are part.
    The two lubricant lines 55a, 55b each run in a circumferential direction 91 of the hub 26. Each line extends annularly over an angular sector of the order of 360 °. In this regard, it is noted that each pipe 55a, 55b can be interrupted or continuous over 360 °. By way of example, it can be provided that each pipe is made using two 180 ° segments, or four 90 ° segments. This makes it possible to constitute a pipe for the inlet of the fluid, and another for the outlet of the fluid.
    Each pipe 55a, 55b is arranged between the two flanges 62, 64, carried by the outer radial end of the arms 66. The two pipes are therefore substantially parallel, and connected at one of their ends to the rest of the hydraulic circuit.
    Line 55a on the right in FIG. 3 corresponds to a first line forming a lubricant distributor, while line 55b on the left corresponds to a second line forming a lubricant manifold.
    Associated with blade 24, the first pipe 55a comprises a lateral opening cooperating with a first nozzle 88a for the passage of lubricant. More specifically, the pipe 55a comprises, from its lateral opening, a first complementary tip 92a projecting radially outward and receiving the tip 88a. To ensure sealing, a first O-ring 94a is placed between the two end pieces 88a, 92a, being compressed radially in relation to the coincident axes of the two end pieces. In this regard, it is noted that to provide even greater flexibility in the arrangement, a ball joint could be implemented between the two ends. Anyway, the joint between these two tips allows a slight swiveling, and, because bias, a backlash.
    Thus, the lubricant circulating in the first line 55a can join a first passage of lubricant 98a crossing the end piece 88a, and go towards the blade 24. It is noted that in the embodiment of FIGS. 3 to 4a, the first line 55a is of cross section in the form of a quadrilateral, but that another shape could be adopted, for example a substantially circular shape as in the embodiment of FIGS. 5 and 6. In addition, the seal between the two end pieces 88a, 92a could be produced using a seal no longer compressed radially, but stressed axially as in the embodiment in FIG. 7.
    Returning to FIGS. 3 to 4a, it is noted that for this embodiment, all of the characteristics described above with reference to the first nozzle 88a and to the first pipe 55a, are implemented in an identical or similar manner for the second pipe 55b and a second nozzle 88b cooperating with this pipe 55b. In the figures, the elements bearing the same reference numbers correspond to identical or similar elements, only the extension “a” having been modified by the extension “b” for the elements associated with the second pipe 55b forming a lubricant manifold.
    Located radially outward relative to the blade root 34, one of the two platforms 40a associated with the blade 24 covers the end piece 88a. This platform 40a, preferably produced by simple machining and extending circumferentially between two directly consecutive casing vanes in the circumferential direction 91, is fixed to the hub 26 by conventional means. Its circumferential end therefore covers the blade root 34, as well as the end piece 88a which is here housed in a housing orifice 132a of a circumferential projection 130a of the blade root. More specifically, the end piece 88a is inserted radially from the outside towards the inside until its head abuts on a shoulder of the housing orifice 132a.
    One of the features of the invention resides in the fact that the first lubricant passage 98a has a first passage axis 134a, preferably oriented substantially radially with respect to the axis of the intermediate casing, and which is spaced circumferentially from a first orifice axis 140a on which is centered a first lubricant passage orifice 124a formed in the foot 34. The first orifice axis 140a is also preferably substantially radial, and its associated passage orifice 124a opens into the first passage 50a of the aerodynamic part 32 of the blade. However, this orifice 124a does not entirely cross the blade root 34, since it is closed at the internal radial end of this foot, for example by a plug 136a put in place after machining the orifice.
    Consequently, to ensure fluid communication between the orifice 124a and the lubricant passage 98a which is substantially parallel thereto, there is provided a first connecting piece 125a which here takes an elongated shape oriented substantially in the circumferential direction 91. It s 'Acts preferably a pin 125a, housed in a housing 127a of circumferential orientation, and provided within the foot through the orifice 124a and the passage of lubricant 98a, preferably substantially orthogonally. The pin 125a is itself traversed by a first connecting conduit 142a, having a conduit axis 144a substantially orthogonal to the two axes 134a, 140a. The first connecting duct 142a is of substantially circumferential orientation in side view.
    In FIG. 3a, the left part of the pin 125a is housed in the blade root so as to make the connecting duct 142a communicate with the orifice 124, via an opening 129a made through the wall of the delimiting pin the connecting duct 142a. Similarly, the right part of the pin 125a is housed in the upper part of the end piece 88a so as to make the connection conduit 142a communicate with the passage of lubricant 98a, via an opening 131a made through the wall of the pin delimiting the connecting duct 142a.
    The head 133a of the first pin 125a forms a circumferential stop against the blade root 34. It is preferably fixed either to the blade root 34, or to the hub 26, or to the pipe 55a, for example using one or more screws.
    Two O-rings 151a seal between the upper part of the nozzle 88a and the pin 125a, being arranged on either side of the opening 131a. Similarly, two O-rings 153a seal between the blade root 34 and the pin 125a, being arranged on either side of the opening 129a.
    Thus, once assembled, the connecting piece 125a in the form of a pin fulfills the function of intermediate connecting piece between the blade root and the pipe 55a, thus offering flexibility which not only facilitates assembly / disassembly, but which also limits hyperstatism in the setting of dawn. The risk of damage to the tips is advantageously reduced.
    It is noted that in the embodiment which has just been described, a connection of the cylinder-cylinder type is adopted between the pin and the blade root as well as between the pin and the end piece. These connections are thus of the pivot-sliding type, but the presence of the aforementioned joints 151a, 153a between these parts allows a slight swiveling, offering even more flexibility in assembly.
    Here again, it is noted that all of the characteristics described above in relation to the first connecting piece 125a and its associated elements, are implemented in an identical or similar manner at the level of a second connecting piece 125b cooperating with the second nozzle 88b and with the pipe 55b forming a collector. In the figures, the elements bearing the same reference numbers correspond to identical or similar elements, only the extension “a” having been modified by the extension “b” for the elements associated with the second connecting piece 125b.
    As can be seen in particular in FIG. 8, the two end pieces 88a, 88b are axially spaced from one another, and both are arranged axially between the upstream 72 and downstream 82 holes for fixing the blade 24. In the circumferential direction, each passage axis 134a, 134b is spaced from a connection zone 150 between the blade root 34 and the aerodynamic part 32, the profile of which is shown diagrammatically by the dotted lines in FIG. 8. Always with reference to this, it is noted that the two end pieces 88a, 88b could be arranged on the same side of the aerodynamic part, but that they are preferably arranged on either side of this part 34 to further facilitate further integration. Thus, the first endpiece 88a and its associated pin 125a are arranged on the underside side, and the second endpiece 88b and its associated pin 125b are arranged on the upper surface side, or vice versa.
    Referring now to an alternative embodiment shown in Figure 9, the tip 88a is no longer housed in an orifice of the blade root, but offset from the latter in the circumferential direction 91. Maintaining the tip 88a is then ensured either simply by its cooperation with the pin 125a and the complementary tip 121a, or by a tip-holder device 108a fixed on one and / or the other of the pipes, or directly on the hub 26.
    According to yet another alternative shown in FIG. 10, at the junction between the blade root 34 and the pin 125a, a ball joint is provided, further promoting the flexibility of the assembly. This type of connection can be ensured by providing an attachment piece for reconstituting the blade root, making it possible to close the cage forming the ball joint. One of the other advantages of this type of connection lies in the fact that it allows the pin 125a to be held in position. In this regard, it is noted that a similar connection can also be provided between the end piece 88a and the pin 125a.
    FIG. 11 shows another embodiment, in which the tip holder 108a is associated with two tips 88a, 88b, the first cooperating with the line 55a for the distribution of lubricant in a blade 24, and the second cooperating with the line 55b for the collection lubricant in a directly consecutive blade 24, in the circumferential direction. The two nozzles 88a, 88b are here spaced axially from one another, the bit holder 108a which is common to both is in turn arranged circumferentially between the two blades 24, and radially between the lubricant lines 55a, 55b and platform 40a.
    The tip-holder device 108a is preferably made in two separate parts, namely a main body 160 fixed for example by screws on the pipes 55a, 55b or the hub, and a closure cowl 162 fixed by screws on the main body 160. Between the main body 160 and the closing cover 162, a first housing 164a is defined in which the first pin 125a is arranged, as well as a second housing 164b in which the second pin 125b is arranged.
    In addition, each end piece 88a, 88b is preferably carried by the main body using a connection which is preferably a screw connection, but which could be a flanged, welded connection, or the like. It is also possible to manufacture each end piece in one piece with the main body 160, without departing from the scope of the invention. However, one of the advantages of having a removable / reversible connection between each end piece and the main body 160 is the ease of removing the end piece, and, if necessary, being able to place a plug on this main body. to isolate the blade in question from the rest of the lubricant circuit.
    Finally, as is visible for the first pin 125a, the latter has, at its head 133a, a fixing lug 166a allowing its mounting by screws on a complementary fixing lug 168a, integral with the complementary tip 92a equipping the first pipe 55a. A similar attachment is made for the second pin 125b.
    FIGS. 12a to 12f represent different stages of a method of assembling the intermediate casing shown in FIG. 11.
    First of all, the hub is equipped with its pipes 55a, 55b, as shown diagrammatically in FIG. 12a. Then, with reference to FIG. 12b, the main body 160 of the common bit holder is fixed on the pipes, making sure that each bit enters its complementary tip 92a, 92b. The two directly consecutive blades 24 are then put in place and fixed on the hub as shown in FIG. 12c, then the two pins 125a, 125b are placed on the main body 160. This step is shown in FIG. 12d, step during from which the pins are also inserted into their associated blade root, then fixed by their ears 166a, 166b. The next step, shown diagrammatically in FIG. 12e, consists in fixing the cowling 162 on the main body, before the platform 40a comes to cover the assembly as shown in FIG. 12f. These steps are repeated for all the doublets of blades directly consecutive from the casing which incorporate a heat exchanger function.
    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.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. Intermediate casing (25) for an aircraft turbomachine with double flow, comprising a hub (26), an outer shroud (23) as well as outlet guide vanes (24) mounted at their ends on the hub and on the shroud external, at least some of said outlet guide vanes (24) each having a heat exchanger function and comprising a lubricant passage (50a, 50b) intended to be cooled by the secondary flow (58) conforming to an external surface of the outlet guide vane, a foot (34) of the outlet guide vane comprising at least one lubricant passage orifice (124a, 124b) extending along an orifice axis (140a, 140b) and communicating with a pipe lubricant (55a, 55b) integral with the hub (26), characterized in that the intermediate casing also comprises, associated with at least one of the outlet guide vanes (24), at least one lubricant passage end piece ( 88a, 88b) having a lubricant passage (98a, 98b) extending along a passage axis (134a, 134b) and opening into the lubricant line (55a, 55b), and in that the passage axis (134a, 134b) and the orifice axis (140a, 140b) are spaced from each other in a circumferential direction (91) of the casing, and in that a connecting piece (125a, 125b) traversed by a connecting duct (142a, 142b) is of a part partially housed in the blade root (34) so as to communicate the connecting duct (142a, 142b) with the lubricant passage orifice (124a, 124b) of the blade root, and on the other hand partially housed in a bit holder device (108a) or in the lubricant passage nozzle (88a, 88b), so as to make the connection conduit (142a, 142b) communicate with the lubricant passage (98a, 98b) from the mouthpiece.
    [2" id="c-fr-0002]
    2. Intermediate casing according to claim 1, characterized in that said connecting piece (125a, 125b) adopts a generally elongated shape, oriented substantially in the circumferential direction (91) of the casing.
    [3" id="c-fr-0003]
    3. Intermediate casing according to any one of the preceding claims, characterized in that said connecting piece (125a, 125b) is secured to the blade root (34), or on the hub (26) of the intermediate casing, or else on the lubricant line (55a, 55b), and preferably on an ear (166a, 166b) of a complementary tip (92a, 92b) provided on the lubricant line (55a, 55b), the complementary tip cooperating with the lubricant passage nozzle (88a, 88b).
    [4" id="c-fr-0004]
    4. Intermediate casing according to any one of the preceding claims, characterized in that the passage axis (134a, 134b) and the orifice axis (140a, 140b) are substantially parallel to each other, and orthogonal to an axis of conduit (144a) of said connecting conduit (142a, 142b).
    [5" id="c-fr-0005]
    5. Intermediate casing according to any one of the preceding claims, characterized in that the tip-holder device (108a) comprises a main body (160) fixed on the lubricant line (55a, 55b), as well as a cowling ( 162) fixed on the main body (160), and in that the connecting piece (125a, 125b) is housed in a housing (164a, 164b) formed jointly by the main body (160) and the cowling (162).
    [6" id="c-fr-0006]
    6. Intermediate casing according to claim 5, characterized in that the main body (160) and the end piece (88a, 88b) are made in one piece, or secured to one another by a welded connection or screwed.
    [7" id="c-fr-0007]
    7. Intermediate casing according to any one of the preceding claims, characterized in that it comprises, associated with said blade (24), at least one platform (40a, 40b) for reconstitution of secondary vein, said platform being fixed on the hub (26) and arranged radially outward relative to the blade root (34) and to the bit holder device (108a).
    [8" id="c-fr-0008]
    8. Intermediate casing according to any one of the preceding claims, characterized in that the tip-holder device (108a) is arranged between two blades (24) directly consecutive from said casing, the tip-holder device (108a) carrying a first and a second lubricant passage nozzle (88a, 88b), the two nozzles:
    - Being associated respectively with one and the other of the two directly consecutive vanes (24) via a first (125a) and a second connecting piece (125b); and
    - cooperating respectively with a first (55a) and a second lubricant line (55b).
    [9" id="c-fr-0009]
    9. A method of assembling an intermediate casing (25) according to any one of claims 5 to 8, comprising the following steps:
    - mounting the main body (160) of the tip-holder device on the pipe (s) (55a, 55b), so that each end piece (88a, 88b) cooperates with its associated pipe;
    - Installation of each connecting piece (125a, 125b) on the main body (160) and in the blade root (34), then fixing of this connecting piece on its associated pipe; and
    - Attaching the cover (162) to the main body (160) so as to enclose each connecting piece (125a, 125b) between the main body (160) and the cover (162) of the bit holder device (108a).
    [10" id="c-fr-0010]
    10. Turbomachine of an aircraft with double flow (1) comprising an intermediate casing (25) according to any one of claims 1 to 8, arranged downstream of a fan (15) of this turbomachine.
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    同族专利:
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    US10669872B2|2020-06-02|
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    引用文献:
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    FR2989110B1|2012-04-05|2016-09-09|Snecma|DAWN OF STATOR FORMED BY A SET OF DAWN PARTS|
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    US10196932B2|2015-12-08|2019-02-05|General Electric Company|OGV heat exchangers networked in parallel and serial flow|
    US11125160B2|2015-12-28|2021-09-21|General Electric Company|Method and system for combination heat exchanger|
    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|GB201616969D0|2016-10-06|2016-11-23|Rolls Royce Plc|Stator assembly for a gas turbine engine|
    FR3059353B1|2016-11-29|2019-05-17|Safran Aircraft Engines|AIRBOARD TURBOMACHINE EXIT OUTPUT AUDE COMPRISING A LUBRICANT-BENDED ZONE HAVING AN IMPROVED DESIGN|
    FR3075256B1|2017-12-19|2020-01-10|Safran Aircraft Engines|OUTPUT DIRECTIVE VANE FOR AIRCRAFT TURBOMACHINE, INCLUDING A LUBRICANT COOLING PASS EQUIPPED WITH FLOW DISTURBORING PADS|
    FR3081027B1|2018-05-09|2020-10-02|Safran Aircraft Engines|TURBOMACHINE INCLUDING AN AIR TAKE-OFF CIRCUIT|
    DE102019135339A1|2019-12-19|2021-06-24|Rolls-Royce Deutschland Ltd & Co Kg|Aircraft gas turbine engine|
    GB2591298A|2020-01-27|2021-07-28|Gkn Aerospace Sweden Ab|Outlet guide vane cooler|
    CN112059553B|2020-09-08|2021-11-05|中国航发沈阳黎明航空发动机有限责任公司|Multiple cross machining method for intermediary case|
    法律状态:
    2018-02-19| PLFP| Fee payment|Year of fee payment: 2 |
    2018-10-05| PLSC| Publication of the preliminary search report|Effective date: 20181005 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 5 |
    2022-02-21| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1752791|2017-03-31|
    FR1752791A|FR3064682B1|2017-03-31|2017-03-31|INTERMEDIATE CASE FOR AIRCRAFT TURBOMACHINE COMPRISING A LUBRICANT PASSING BIT CONNECTED TO A CARTER BOLT BY A CONNECTING PART|FR1752791A| FR3064682B1|2017-03-31|2017-03-31|INTERMEDIATE CASE FOR AIRCRAFT TURBOMACHINE COMPRISING A LUBRICANT PASSING BIT CONNECTED TO A CARTER BOLT BY A CONNECTING PART|
    US15/936,657| US10669872B2|2017-03-31|2018-03-27|Intermediate case for an aircraft turbomachine comprising a lubricant passage end-piece connected to a case vane by a connection piece|
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