• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
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    • 专利摘要:
    A non-ducted aircraft turbomachine blower having at least one propeller comprising a hub and an annular array of blades (36) extending substantially radially outwardly from said hub, the hub having an annular row of hoods (46) mounted between the radially inner ends of the blades and adapted to be fixed to an upstream shell (38) and to a downstream shell of the hub, characterized in that at least one cover comprises at a circumferential end (48c) at least one edge of joined joint with a complementary joint edge of an adjacent cap, and in that said at least one cover and at least one of said upstream and downstream ferrules are configured so that the cover can be mounted and disassembled by a displacement including less at its beginning a pivoting about an initial pivot axis (C) circumferentially spaced from said at least one joint edge towards a center of the cover, and so that at said pivot otément said at least one edge of the joint deviates radially from said complementary seal edge by moving inwardly of said hub.
    公开号:FR3032941A1
    申请号:FR1551586
    申请日:2015-02-24
    公开日:2016-08-26
    发明作者:Charles-Henri Michel Marie Derrez；Adrien Jacques Philippe Fabre；Sebastien Marcelino Juste；Pecheur Cyril Roger Yves Le；Michel Rognant
    申请人:Aircelle SA；SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present invention relates to a non-ducted fan, known as the "open rotor" and "unducted fan", of an aircraft turbomachine. STATE OF THE ART A turbomachine of this type is described in WO-A1- 2011/069981. It mainly comprises, along a longitudinal axis and inside a cylindrical nacelle, carried by the structure of the aircraft (such as the rear part of the fuselage of an aircraft), a "gas generator" part and a part "Propulsion" (only the nacelle part covering the gas generator is fixed while the nacelle parts, situated at the level of the propellers, are rotatable). The propulsion portion comprises an unsheathed fan comprising two coaxial and counter-rotating propellers, respectively upstream (forward) and downstream (rear) which are driven, in inverse rotation with each other, by a suitable mechanism driven by a power turbine located at the outlet of the gas generator part.
    [0002] Each helix comprises a hub having an axis of revolution and carrying an annular row of blades extending substantially radially outwardly from the hub, and outside the nacelle. The hub also has hoods that form rotating parts of the nacelle.
    [0003] To allow the optimal operation of the turbomachine according to the different flight phases encountered, the blades of the counter-rotating propellers can rotate in the radial housings of the hub. The blades are rotated about their respective pivot axes, by a suitable orientation system to vary the pitch of the blades during flight, that is to say the pitch of the propellers. For example, the blades can vary according to the system, from + 90 ° to TI ° for the phases of 3032941 2 vol, from + 30 ° to - 30 ° for the phases on the ground and of the reverse, and to have a fast return to 90 ° , in the flag position, in the event of malfunction in flight (engine failure), for which the blades are erased with respect to the direction of advance of the aircraft and offer the least possible drag.
    [0004] Each blade generally comprises a foot which is engaged in a groove of complementary shape of a plate in view of its retention radially outwardly with respect to the axis of revolution or rotation of the helix. The plate generally comprises a cylindrical portion forming a pivot and defining a radial axis of rotation and wedging of the blade.
    [0005] The covers of each helix extend around the hub and are generally intended to be aligned with the radially outer surfaces of the blade support plates. Document FR-A1-2,645,499 describes alternative embodiments of covers according to the prior art. In FIG. 4 of this document, the propeller is equipped with an annular row of covers which each comprise, substantially in their center, an opening for mounting the support plate of a blade. In Figure 8, the propeller is equipped with an annular row of covers which are each mounted between two adjacent blades. Each cap comprises, at each of its circumferential ends, notches for mounting the support plates of the adjacent blades. The covers are not directly contiguous because gaskets are interposed between the circumferential ends of the covers. Thus, each bonnet has at its circumferential ends seal edges which are complementary to gaskets. When the blades are in the flag position (FIG. 8), the radially inner ends of the leading and trailing edges of the blades are situated above and at a short distance from the linings and therefore do not interfere with the removal of the cowls, by radial translation. outwards. It is indeed important to be able to remove the hoods, without disassembling the blades, in order to have access to the annular space extending between the hub and the hoods, in which are located parts of the plates and 3032941 3 equipment such as a telemetry box for maintenance or inspection purposes. However, the above described technology of inter-blade covers has disadvantages. The casing of the propeller hub, formed by the covers and the gaskets, is formed of a large number of parts, which results in a relatively long assembly and disassembly of the cover, and therefore in a longer period of time. relatively high aircraft immobilization. The present invention provides an improvement to this technology which is simple, effective and economical. SUMMARY OF THE INVENTION The invention proposes a non-ducted aircraft turbomachine fan, comprising at least one propeller comprising a hub and an annular row of blades extending substantially radially outwardly from said hub, the hub comprising an annular row of covers mounted between the radially inner ends of the blades and adapted to be fixed to an upstream shell and to a downstream shell of the hub, characterized in that at least one cover comprises at a circumferential end at least one joint edge joined with a joint edge 20 complementary to an adjacent cap, and in that said at least one cover and at least one of said upstream and downstream ferrules are configured so that the cover can be mounted and disassembled by a displacement including less at its beginning a pivoting about an initial pivot axis circumferentially spaced from said at least one joint edge towards a center of the cape ot, and so that, during said pivoting, said at least one edge of the joint radially deviates from said complementary joint edge by moving inwardly of said hub. The helical hub cowl thus does not include gaskets since each cowl has at its circumferential ends complementary gasket edges of adjacent cowl joint edges. Furthermore, according to an essential feature of the invention, the hoods can be mounted and disassembled by rotating them. In contrast to the prior art, in which, although not intended, one could attempt to rotate a hood about a pivot axis extending along the joint edges of one of the circumferential ends. of the cover, the pivot axis of each cover is here circumferentially spaced from the joint edges of the cover, which allows in particular to prevent any blockage between the cover and the radially inner ends of the blades closest to the pivot axis as will be described in more detail in the following.
    [0006] The advantages of this invention may for example be: low number of parts and standards; low mass, important criterion for an open rotor; ease of assembly without disassembling the blades, due to the reduction in the number of parts in the absence of the necessary gaskets in the devices of FR-A1-2 645 499; better resistance to centrifugal force; better rigidity; etc. In the present application, ferrule means an annular element such as a ring, which is integral with an annular support structure of the blades. This ferrule may be fixed to the annular support structure (see rings 60, 62 in FR-A1-2 645 499), or may be directly formed by annular end flanks of the structure (see flanks 20- 21 in WO-A1-2011 / 069981). According to the invention, the pivot axis of the hood is said initial because it is likely to move during disassembly of the hood. In other words, the position of the pivot axis of the cover can vary during disassembly.
    [0007] The non-ducted blower according to the invention may comprise one or more of the following characteristics, taken separately from each other or in combination with each other: said initial pivoting axis passes substantially through at least one pivot point of contact between the hood and the upstream ferrule and / or the ferrule downstream of the hub; Each hood comprises at each of its circumferential ends a first gasket edge on the upstream side and a second gasket edge on the downstream side, said first and second gasket edges being connected by a concave curved edge complementary to a gasket plate; support of a blade; The first and second joint edges of each circumferential end of each cover are at least partly aligned; the first and second joint edges of each circumferential end of each cover extend at least in part along two straight lines substantially parallel to each other and are spaced circumferentially from one another; each edge of the joint has a straight shape substantially parallel to an axis of revolution of the helix or has a shape presenting two segments of joined straight lines, one of which is substantially parallel to said axis of revolution; the joint edges of one of the circumferential ends of each cap each comprise a beveled end portion which joins said concave curved edge; each bonnet comprises at one of its circumferential ends at least one lug of reduced thickness ending in said at least one joint edge and configured to be covered by a complementary lug 20 of reduced thickness of the adjacent bonnet, the latter comprising said complementary seal edge; the or each lug includes screw mounting holes for attaching the hood to the adjacent hood; each ferrule comprises a cylindrical flange for supporting and fixing a circumferential edge of each hood, said pivot zone of contact between the hood and at least one of said ferrules being formed on at least one of said cylindrical flanges; - The cylindrical rim of at least one of the ferrules comprises through radial notches configured to allow the pivoting of the covers; - at least one of the circumferential edges of each cover comprises at least one through radial notch configured to allow the pivoting of the cover; at least one of said radial through notches creates an edge forming a said pivot contact zone; the covers are covered by the radially inner ends of the leading and / or trailing edges of at least some of the blades. The present invention also relates to an aircraft turbomachine, characterized in that it comprises at least one non-ducted fan 10 as described above, said fan preferably comprising two coaxial and counter-rotating propellers. The present invention further relates to a method of disassembling a hood of an unducted fan according to one of the preceding claims, characterized in that it comprises the steps of: a) among the two blades adjacent to the hood, putting the blade farthest from the initial pivot axis of the hood in a position in which the radially inner end of the blade has no area covering a circumferential end of the hood, while the blade closest to said pivot axis has a leading and / or trailing edge having a radially inner end covering another circumferential end of the cover, b) pivoting the cover about said initial pivot axis, so that the circumferential end of the cover further away from said axis deviates radially from the hub, and c) removing the hood. Step c) may comprise a substep of moving the hood so that its center is circumferentially closer to the blade farthest from the initial pivot axis, while rotating the hood around a pivot axis coincident with or distinct from the initial pivot axis 30. DESCRIPTION OF THE FIGURES The invention will be better understood and other details, characteristics and advantages of the invention will appear more clearly on reading the following description given by way of nonlimiting example and with reference to the accompanying drawings. in which: FIG. 1 is a partial schematic perspective view of a non-ducted fan turbomachine; - Figure 2 is a schematic longitudinal sectional view of the turbomachine of Figure 1; FIG. 3 is a schematic perspective view of a ring of an external propeller hub of the turbomachine of FIG. 1, this ring comprising housings in one of which is mounted a blade support plate; - Figures 4 and 5 are partial schematic perspective views of an external propeller fan according to the invention; Figure 5a is an enlarged view of the detail of Figure 5; - Figure 6 is a partial schematic perspective view of the helix of Figures 4 and 5, and shows a mounting step / disassembly of the propeller; FIG. 6a is an enlarged view of detail 16 of FIG. 6; Figure 7 is an enlarged view of another detail of the helix of Figure 6; - Figures 8 to 10 are partial schematic perspective views of the helix of Figures 4 and 5, and show other stages of assembly / disassembly of the propeller; Figures 11 and 12 are partial schematic perspective views of a hood of the propeller of Figures 4 and 5; - Figures 13 and 14 are partial schematic perspective views of a ferrule of the hub of the propeller of Figures 4 and 5; and FIGS. 15 and 16 are very partial schematic views of alternative embodiments of an external fan propeller according to the invention. DETAILED DESCRIPTION 3032941 8 Reference is first made to FIGS. 1 and 2, which diagrammatically show an aircraft fanless turbomachine 10, referred to as "open rotor" or "unducted fan". This turbomachine 10 usually comprises, upstream 5 downstream in the direction of flow of the gas flow F inside a nacelle 12, a compressor part (s) 14, an annular combustion chamber 16, a part with turbines 18 whose downstream 20 drives, via a gearbox or epicyclic gearbox 22 and contrarotatively, two external propellers 24, 26 aligned coaxially 10 along the longitudinal axis A of the turbomachine and constituting a fan . In the present application, the terms upstream and downstream refer to the flow of the flow F in the turbomachine 10. The propellers, namely the upstream propeller 24 and the downstream propeller 26, are arranged in parallel radial planes, perpendicular to the axis A, and rotate through the downstream turbine 20 and the gearbox 22 in opposite directions of rotation. The upstream propeller 24 comprises a rotary hub 28, rotatably connected to a corresponding portion of the gearbox 22 to rotate in one direction. This hub 28 is supported by bearings on a fixed cylindrical casing of the turbine engine, bearings and fixed housing are not shown. The hub 28 comprises a rotary ring 30 housed in the usual manner in the nacelle 12 and receiving, in cylindrical housings 32, plates 34 for guiding and rotating the blades 36 of the propeller 24 (Figure 3). The blades 36 project externally relative to the nacelle 12.
    [0008] Similarly, the downstream propeller 26 has a rotating hub 28, on one side rotatably connected to another part of the reducer 22, to then rotate in the opposite direction. This hub 28, supported by bearings, comprises a rotary ring 30 receiving, in a manner analogous to that previously, in cylindrical housings 32, the plates 34 for supporting the blades 36 of the propeller 26.
    [0009] In operation, and briefly, the flow of air F entering the turbomachine 10 is compressed, then mixed with fuel and burned in the combustion chamber 16. The combustion gases generated then pass into the turbine part 18 to drive in reverse rotation, via the epicyclic reduction gear 22, the propellers 24, 26 which provide the major part of the thrust. The combustion gases are expelled through a nozzle 40 to thereby increase the thrust of the turbomachine. The blades 36 of the propellers 24, 26 are of the variable-pitch type, that is to say, that they can rotate in their respective recesses 32 around the radial geometric axes B of the plates 34 by means of control systems the pitch of the blades, so that they take, as recalled earlier, an optimal angular position according to the operating conditions of the turbomachine and the flight phases concerned. Each blade 36 may comprise at its radially internal end a foot, of dovetail section for example, which is fitted into a groove of complementary shape of the corresponding plate 34 (Figure 3). Reference will now be made to FIGS. 4 to 14, which show a first embodiment of an unvented fan of a turbomachine, according to the invention. As mentioned above, the helix essentially comprises two parts, namely a rotary hub 28 and an annular row of blades 36. The hub 28 has an axis of revolution coinciding with the axis A, 25 and the blades 36 extend radially outwardly relative to the axis A, their radially inner ends being connected to or fitted into the support plates of the blades 36. The hub 28 comprises a ring 30 of the type of that represented in FIG. 3, two rings 38, 39 respectively mounted upstream and downstream 30 of the ring, and a cowling around the hub.
    [0010] As described above, the ring 30 comprises an annular row of housing 32 for mounting the plates 34 for supporting the blades 36. The document WO-A1-2011 / 069981 describes this type of ring. The rings 38, 39, one of which is shown in Figures 13 and 14, 5 are coaxial with the ring 30. They each comprise a radial annular wall 38a, 39a connected at its outer periphery to a cylindrical rim 38b, 39b. Alternatively, they could be formed by simple annular elements which could be formed or not in one piece with the ring 30.
    [0011] The wall 38a, 39a of each shell 38, 39 comprises at its inner periphery an annular flange for attachment to the ring 30, by means of the screw-nut type. The upstream collar 38 is fixed on the upstream circumferential edge of the ring so that its flange 38b is oriented downstream, and the downstream collar 39 is fixed on the downstream circumferential edge of the ring so as to its rim 39b is oriented upstream. The rings 38, 39 define between them and around the ring 30 an annular space 40, which can be seen in FIGS. 9 and 10. In this space 40, parts of the plates 34 can be extended and mounted on the equipment, such as a telemetry case. The flanges 38b, 39b further include orifices 44 for fixing the cowling by means of the screw-nut type. These flanges 38b, 39b each comprise an annular row of radial notches 42 through. Each of the flanges 38b, 38b is thus of the sectorized type and each flange sector comprises at each of its circumferential ends an edge 42a extending substantially parallel to the axis A. The cowling comprises an annular row of hoods 46 which are each mounted between the radially inner ends and the plates 34 of two adjacent blades 36.
    [0012] Figures 11 and 12 show a hood 46 according to the invention. Such a cover is for example made of injection-molded composite material. In the example shown, the cover 46 has a rounded shape (around the axis A), although this is not limiting. It comprises an upstream circumferential edge 48a and a downstream circumferential edge 48b, as well as lateral or circumferential ends 48c, 48d of the hood. The circumferential end 48c comprises two longitudinal edges 50a, 50b, respectively upstream and downstream, which are separated from each other by the peripheral edge 52a of a central notch 52 of the cover. The other circumferential end 48d comprises two other longitudinal edges, 51a, 51b, respectively upstream and downstream, which are separated from each other by the peripheral edge 52a of another median notch 52 of the cover. These two other longitudinal edges 51a, 51b are formed on lugs 59, in this example lugs of reduced thickness which form shoulders on the internal face of the hood at their junction with the main part of the hood, which has a greater thickness. Each notch 52 has a concave curved shape that extends at an angle close to 180 °. It has a shape complementary to that of the plate 34 so that the cover 46 can be mounted leaving a minimum gap between its edge 52a and the plate 34. The longitudinal edges 50a, 50b, 51a, 51b of each end circumferential hood are here substantially straight and parallel to the axis A. They extend substantially in the same radial plane passing through the axis A.
    [0013] The edges 50a, 50b form gasket edges intended to be contiguous with the edges 51a, 51b of the nearest cowling. An edge 52a is for its part almost joined with the nearest plate, a minimum spacing being preserved so that the rotation of the plate is done without friction against the edge 52a. In the same way, the edges 51a, 51b form joint edges intended to be contiguous with the edges 50a, 50b of the nearest hood. The edges 50a, 50b, 51a, 51b of a cover thus have a shape complementary to that of the corresponding edges 51a, 51b, 50a, 50b of the two adjacent covers, as can be seen in the drawings. It is thus understood that the rollover of the helix is devoid of inter-cowl linings and that the circumferential extent of each cowl 5 is equal to or greater than 360 ° / n, where n is the number of cowls (which is equal to the number of rolls). blades or plates, and is for example twelve). A circumferential extent greater than 360 ° / n corresponds to the case where the circumferential ends 48c and 48d of the covers overlap at tabs 58 and 59.
    [0014] The longitudinal edges 51a, 51b of the lateral edge 48d are chamfered at their longitudinal ends connected to the edge 52a (chamfers 54). The longitudinal edges 50a, 50b of the lateral edge 48c each comprise, at their longitudinal ends connected to the edge 52a, a pointed portion 56 of shape complementary to that of the corresponding chamfer 54 of the adjacent cap. The cover 46 comprises at each of the longitudinal edges 50a, 50b of its lateral edge 48c, a tab 58 configured to extend circumferentially under a tab 59 of the lateral end of an adjacent cap 20 and thus be covered by this adjacent hood tab. Each tab 58 in this example has a reduced thickness which forms a shoulder on the outer face of the cover at the junction of the tab with the main part of the cover, and extends over substantially the entire longitudinal dimension of the longitudinal edge 50a, 50b corresponding 25. Its radially outer surface is offset radially inwards relative to that of the remainder of the cover, by a radial distance at least equal to the radial thickness of the circumferential end 48d and the edges 50a, 50b of this end of the cover so that in the mounting position the outer surfaces of the hoods may be circumferentially aligned with each other, particularly at their circumferential ends 48c, 48d.
    [0015] The cover 46 also comprises orifices 60 for the passage of fastening means of the screw-nut type. These orifices are distributed along the circumferential edges 48a, 48b and longitudinal edges 50a, 50b, 51a, 51b. Ports are located on the legs 58 of each cover and are intended to be traversed by screws mounted in the orifices of the circumferential end 48d of an adjacent cover. The covers 46 are supported on the flanges 38b, 39b of the rings 38, 39 and the screws mounted in the orifices of the edges 48a, 48b of the covers pass through the orifices 44 of the flanges 38b, 39b.
    [0016] Referring now to Figures 4 to 10 which show steps of a method according to the invention for mounting or dismounting the covers 46 of the outer propeller. Figures 4 and 5 show a portion or a sector of a helix of which one of the covers 46, the central cover, is transparent, so as to view the space 40 above. The blades 36 of the helix are here partially represented and in the flag position, in which they are substantially parallel to the axis A. Each blade 36 comprises a leading edge 36a and an air leakage edge 36b. flowing around the nacelle of the turbomachine in operation. As can be seen in FIGS. 4, 5a and 6, the blades 36 have a longitudinal dimension or chord greater than the longitudinal dimension or the diameter of the plate 34, and the downstream ends of the blades comprising the trailing edges 36b thus extend. downstream beyond platen 34.
    [0017] The covers 46 are configured to extend below the downstream ends of the blades 36 (FIG. 5a) and at a short distance therefrom. It is also noted that the edges 52a, 50a, 50b, 51a, 51b of the cowlings marry, with slight play, the shapes of the plate 34 and the edges 51a, 51b, 50a, 50b of the adjacent cowls. We also see the tab 58 of a cover which is covered by the tab 59 of the adjacent cover (Figure 5a).
    [0018] It can be seen that the orifices 60 of the hoods 46 are aligned with orifices of the adjacent hoods and orifices 44 of the flanges 38b, 39b of the ferrules 38, 39. It can also be seen, in particular in FIG. 4, that the notches 42 of FIGS. The flanges 38b, 39b are located at the corners of the hoods, in the circumferential edge connection areas 48a, 48 at the longitudinal edges 50a, 50b, 51a, 51b. In other words, the covers do not rest, at their corners, on the flanges 38b, 39b of the rings 38, 39. After unscrewing and removal of the fixing screws of the covers 46 (Figures 4, 5 and 5a), a step of Disassembly method consists in pivoting a cover 46 (here the transparent central cover) around an initial pivot axis C. The initial pivoting axis C preferably passes substantially through the edge 42a of at least one of the ferrules 38, 39 (which is a contact edge between the cap and the ferrule or ferrules) and is circumferentially spaced from the seal edges 50a, 50b, 51a, 51b of the circumferential ends 48c, 48d of the cap. In the example shown, the initial pivoting axis C of each cover 46 is situated in the vicinity of the lateral end 48c (comprising the tabs 58) and is at a circumferential distance from the edges 50a, 50b of this end. It passes through the edges 42 of two notches 42 facing the edges 38b, 39b. When pivoting the cover 46, the circumferential end 48c comprising the tabs 58 pivots about the axis C, radially inwards, until it penetrates into the aforesaid space 40 through the corresponding notches 42 of the flanges 38b , 39b ferrules 38, 39 (Figures 6a and 7). The opposite circumferential end 48d of the cover rotates about the axis C, radially outward, and rises away from the flanges 38b, 39b of the rings 38, 39. This allows the hood to extract from the plate 34 located on the side of the circumferential end 48d of the cover. The pivoting of the cover can take place initially at a relatively low angle, for example of the order of 10-20 ° C. (FIG. 6). This angle may vary from one operator to another. This displacement is performed on a relatively small angle for several reasons. First, the blades 36 adjacent to the hood may comprise portions covering the hood. This is particularly the case of the blade located on the side of the circumferential end 48c of the cover, the radially inner end of the trailing edge and / or the leading edge partially covers this circumferential end. An initial pivoting of the cover 46 to an excessive angle could cause contact between the cover and the radially inner end of the trailing edge of the blade. Furthermore, the upstream circumferential edge 48a of the cover may have a particular conformation visible in FIG. 12. When the cover is pivoted, this edge 48a, which covers the outer periphery of the upstream collar 38a, could come into contact with this periphery and prevent further pivoting of the hood around the initial pivot axis C.
    [0019] The cover 46 must then be displaced laterally as well as radially outward in order to partially extract its circumferential end 48c from the space 40 (FIGS. 6a and 7), by pulling it in a direction substantially parallel to the hood and facing the blade located on the side of the end 48d of the hood. This translation makes it possible to move the center of the hood away from the radially inner ends of the trailing edge and the leading edge of the aforementioned blade, while increasing the spacing between the outer surface of the hood and these ends. radially internal of the blade. By increasing the above-mentioned gap, a second pivoting of the cover can then take place on a larger angle, for example of the order of 30-50 ° (FIG. does not abut against the radially inner end of the trailing edge or the leading edge of the aforementioned blade. Pivoting takes place around a final pivot axis C, which corresponds to a displacement of the initial pivot axis C. In the example shown, the final pivot axis C is parallel to the initial axis C and extends perpendicularly to the upstream circumferential edge 48a of the hood. The pivot axis C can move on the ferrules as the hood is removed. On the side of the circumferential end 48d of the cover, chamfers 54 of the cover may be necessary and dimensioned to allow this new pivoting by allowing a passage of the cover closer to the blade located on the side of this end 48d of the cover without bumping against this blade. The invention is however not limited to the presence of such chamfers. The blade on the side of the circumferential end 48d of the cover may be dimensioned so as to allow the passage of the cover even in the absence of chamfers. The cover 16 can then be removed to inspect the space 40 and perform a maintenance operation for example (Figures 9 and 10). If necessary, other covers 46 of the propeller are disassembled in the same way. To assemble one or more covers, the aforementioned steps can be repeated in the reverse order. Figures 15 and 16 show schematically alternative embodiments of the invention. In these figures, the elements already described in the above are designated by the same references. In Figure 15, the hub ring is similar to that described in the foregoing. The upstream ferrule 38 of the hub is also similar to that described above. On the other hand, the downstream collar 39 is different because its rim 39b here is devoid of notches 42. The plates 34 and the blades 36 are similar to those described in the foregoing. The two visible blades are not wedged in the same position. The left blade on the drawing is in the flag position while the right one is inclined relative to the axis A, so as to be able to disassemble the cover 46 mounted between these blades 36. The covers 46 here have a peripheral shape contour different from that of the previous embodiment.
    [0020] Each cap 46 has a rounded shape about the axis A and comprises an upstream circumferential edge 48a and a downstream circumferential edge 48b, which are interconnected at the lateral or circumferential ends 48c, 48d of the cap. Each circumferential end 48a, 48d comprises two edges 50a, 50b, 51a, 51b, respectively upstream and downstream, which are interconnected by the peripheral edge 52a of a central notch 52 of the cover. Each notch 52 has a concave curved shape that extends at an angle close to 180 °. It has a shape complementary to that of the plate 34 so that the cover 46 can be mounted in an adjusted manner, by its edge 52a, on the plate 34.
    [0021] The edges 50a, 50b, 51a, 51b of each circumferential end of the cover form joint edges as described in the foregoing, and here have a substantially V-shaped shape and comprise a first edge portion 50aa, 50ba, 51aa, 51ba which is rectilinear and substantially parallel to the axis A, and a second edge portion 50ab, 50bb, 51ab, 51bb which is straight and inclined with respect to the axis A. The edges 50aa, 50ba of each circumferential end of the hood are circumferentially offset from each other. Furthermore, the edge 50ba of the end 48c of each cover is either aligned with the pivot axis C of the cover is circumferentially offset from the axis C to the end 48d of the cover. It is thus understood that, during the pivoting of the cover around this axis C, the entire downstream circumferential edge 48b of the cover will lift and move away from the rim 39b and that it is therefore not necessary to provide notches 42 on this rim to allow the hood to pivot. During this pivoting, it is the portion of the end 48c of the cover having the edge 50a, and which is located at the right edge of the blade 36 of the left, which will enter the space 40. The opposite end 48d of the hood is not obstructed by the right blade because of its inclination, and therefore does not risk coming into contact with the blade during pivoting. Disassembly of the cover can be carried out as follows.
    [0022] Of the two blades adjacent to the hood, the blade farthest from the initial pivot axis C of the hood is placed in a position in which the radially inner end of the blade has no area covering the circumferential end. 48d of the hood, while the blade closest to the pivot axis C has a leading edge having a radially inner end covering another circumferential end 48c of the cover, then the cover 46 is rotated around the initial pivoting axis C, so that the circumferential end 48d of the cover furthest from this axis C radially deviates from the hub 28. Finally, the cover is removed this step may include a substep consisting of moving the hood so that its center is circumferentially closer to the blade farthest from the initial pivot axis C, while rotating the hood about a pivot axis c The ring of the hub is similar to that described in the foregoing. On the other hand, the two rings 38, 39 are different because their edges 38b, 39b are both devoid of notches 42. The covers 46 are similar to those of FIG. 15 except that they each comprise here in addition to a notch 62 at the upstream end of its circumferential end 48c. This notch 62 has a function similar to that of the notches 42 mentioned above since it is intended to allow the hood 46 to pivot about the pivot axis C. In other words, instead of providing a notch for pivoting each cover on at least one of the flanges 38b, 39b of the rings 38, 39, this notch is provided on each cover. The notch 62 of each cover 46 defines an edge 62a which extends substantially parallel to the axis A and 25 through which is intended to pass the pivot axis C of the cover. It is understood that the notch 62 must extend over a circumferential distance, along the edge 48a, sufficient for pivoting. It may for example extend from the end 48c to substantially the axis C. The notch 62 must also have a longitudinal dimension, along the axis A, at least equal to that of the rim 38b corresponding for 3032941 19 that the portion of the end 48c of the cover, having the edge 50a, can enter the space 40 above when pivoting the cover. To improve the aesthetics of the assembly and especially optimize the aerodynamics of the cowling avoiding turbulence in the air flow around the cowling, a plug 64 is attached and fixed on the rim 38b of the ferrule to fill the volume of vacuum generated by each notch 62. The cap 64 of each cover has its radially outer surface which is aligned with that of the adjacent covers so as not to generate a loss of charge during operation. Alternatively, plugs 64 for all hoods 46 of the helix could be integrally formed with flange 38b which could for example comprise an annular row of protruding external radial protuberances which would form these plugs. .
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. A non-ducted aircraft turbomachine blower comprising at least one propeller (24, 26) comprising a hub (28) and an annular row of blades (36) extending substantially radially outwardly from said hub, the hub comprising an annular row of covers (46) mounted between the radially inner ends of the blades and adapted to be fixed to an upstream shell (38) and to a downstream shell (39) of the hub, characterized in that at least one cover comprises a circumferential end (48c) at least one joint edge (50a, 50b) joined with a complementary joint edge (51a, 51b) of an adjacent cover, and in that said at least one cover and at least one said upstream and downstream ferrules (38, 39) are configured so that the hood can be mounted and disassembled by a displacement including at least at its beginning a pivoting about an initial pivot axis (C) circumferentially spaced from said at least one edge seal (50a, 50b) towards a center of the hood, and so that, during said pivoting, said at least one joint edge (50a, 50b) radially deviates radially from said complementary joint edge (51a, 51b) while moving inwardly said hub.
    [0002]
    2. Unsheathed blower according to claim 1, wherein said initial pivot axis (C) substantially passes through at least one pivot contact zone (42a, 62a) between the cap and the upstream shell (38) and / or the ferrule downstream (39) of the hub.
    [0003]
    3. Unsheathed blower according to claim 1 or 2, wherein each cover (46) comprises at each of its circumferential ends a first sealing edge (50a, 51a) on the upstream side and a second sealing edge (50b, 51b). the downstream side, said first and second joint edges being connected by a concave curved edge (52a) complementary to a plate (34) for supporting a blade (36).
    [0004]
    A non-ducted blower according to claim 3, wherein: the first and second seal edges (50a, 50b, 51a, 51b) of each circumferential end of each cap (46) are at least partially aligned, or the first and second joint edges (50aa, 50ba, 51aa, 51ba) of each circumferential end of each cap extend at least in part along two straight lines substantially parallel to one another and are circumferentially spaced apart; one of the other.
    [0005]
    5. Unsheathed blower according to one of the preceding claims, wherein each joint edge (50a, 50b, 51a, 51b) has a straight shape 10 substantially parallel to an axis of revolution (A) of the propeller or has a shape having two segments of joined straight lines, one of which is substantially parallel to said axis of revolution (A).
    [0006]
    A non-ducted blower according to claim 3 or 4, wherein the joint edges (51a, 51b) of one of the circumferential ends of each cap each comprise a beveled end portion (54) which joins said curved edge concave (52a).
    [0007]
    7. Unsheathed blower according to one of the preceding claims, wherein each cover (46) comprises at one of its circumferential ends at least one lug (58) of reduced thickness ending in said at least one edge of seal (50a, 50b) and configured to be covered by a complementary lug (59) of reduced thickness of the adjacent cap, the latter including said complementary seal edge (51a, 51b).
    [0008]
    A non-ducted blower according to claim 7, wherein the or each tab (58, 59) includes screw mounting holes (60) for attachment of the hood to the adjacent hood.
    [0009]
    9. Unsheathed blower according to one of the preceding claims, wherein each ferrule (38, 39) comprises a cylindrical flange (38b, 39b) for supporting and fixing a circumferential edge (48a, 48b) of each 30 cover (46), said pivoting contact zone (42a, 62a) between the cover and at least one of said shrouds (38, 39) being formed on at least one of said cylindrical rims (38b, 39b).
    [0010]
    10. Unsheathed blower according to claim 9, in which: the cylindrical flange (38b, 39b) of at least one of the ferrules comprises through radial notches (42) configured to allow the hoods (46) to pivot, or - At least one of the circumferential edges (48a, 48b) of each cover comprises at least one notch (62) through radial configured to allow the pivoting of the cover. 10
    [0011]
    11. Unsheathed blower according to claim 10, wherein at least one of said through radial notches (42, 62) creates an edge forming a said pivot contact zone (42a, 62a).
    [0012]
    12. Unsheathed blower according to one of the preceding claims, wherein the covers (46) are covered by the radially inner ends of the leading edges (36a) and / or trailing (36b) of at least some of the blades (36).
    [0013]
    13. A method of disassembling a hood (46) of an unducted fan according to one of the preceding claims, characterized in that it comprises the steps of: a) among the two blades (36) adjacent to the bonnet, put the blade farthest from the initial pivot axis (C) of the hood in a position in which the radially inner end of the blade has no area covering a circumferential end (48d) of the hood, while the The blade closest to said pivot axis (C) has a leading edge (36a) and / or trailing edge (36b) having a radially inner end covering another circumferential end (48c) of the hood, b) pivoting the cover (46) about said initial pivot axis (C), so that the circumferential end (48d) of the hood furthest from said axis (C) radially deviates from the hub (28), and c) remove the hood. 3032941 23
    [0014]
    The method of claim 13, wherein step c) comprises a substep of moving the hood so that its center is circumferentially closer to the blade farthest from the initial pivot axis (C ), while rotating the hood about a pivot axis coincident with or distinct from the initial pivot axis (C). 10
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    同族专利:
    公开号 | 公开日
    US10118710B2|2018-11-06|
    US20160244175A1|2016-08-25|
    GB2536796A|2016-09-28|
    GB201603038D0|2016-04-06|
    FR3032941B1|2017-03-10|
    GB2536796B|2020-07-15|
    引用文献:
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    FR2645499A1|1989-04-11|1990-10-12|Gen Electric|AIRCRAFT PROPULSION DEVICE WITH ROTOR COVER|
    DE4017586A1|1989-06-05|1990-12-06|Gen Electric|CONNECTING DEVICE FOR AIRPLANE PROPELLER BLADES|
    WO2011015475A1|2009-08-05|2011-02-10|Snecma|Hub for a propeller having variable pitch blades|
    WO2011069981A1|2009-12-07|2011-06-16|Snecma|Propeller hub having a reinforced polygonal ring and turbine engine provided with such a hub|
    US4044973A|1975-12-29|1977-08-30|The Boeing Company|Nacelle assembly and mounting structures for a turbofan jet propulsion engine|
    US5224831A|1990-10-04|1993-07-06|General Electric Company|Fan blade protection system|
    US8057187B2|2008-09-08|2011-11-15|General Electric Company|Steam turbine rotating blade for a low pressure section of a steam turbine engine|
    FR2996592B1|2012-10-10|2014-12-19|Snecma|PROPELLER COMPRISING A DYNAMIC MOBILE ECOPE|
    FR3050719B1|2016-04-28|2018-04-13|Airbus Operations|AIRCRAFT TURBOMACHINE PROPELLER COMPRISING MEANS OF FLAME-RELIEVING BACK-UP MEANS|FR3021295B1|2014-05-21|2016-05-13|Snecma|RAIDI HUB FOR NON-CAREED PROPELLER WITH BLADES WITH VARIABLE TURBOMACHINE ADJUSTMENT.|
    FR3050719B1|2016-04-28|2018-04-13|Airbus Operations|AIRCRAFT TURBOMACHINE PROPELLER COMPRISING MEANS OF FLAME-RELIEVING BACK-UP MEANS|
    US10633067B2|2016-10-17|2020-04-28|General Electric Company|Method and system for improving flow characteristics in marine propellers|
    法律状态:
    2016-02-08| PLFP| Fee payment|Year of fee payment: 2 |
    2016-08-26| PLSC| Publication of the preliminary search report|Effective date: 20160826 |
    2017-02-01| PLFP| Fee payment|Year of fee payment: 3 |
    2018-01-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 Owner name: AIRCELLE, FR Effective date: 20170719 |
    2019-01-23| PLFP| Fee payment|Year of fee payment: 5 |
    2020-01-22| PLFP| Fee payment|Year of fee payment: 6 |
    2021-01-20| PLFP| Fee payment|Year of fee payment: 7 |
    2022-01-19| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1551586A|FR3032941B1|2015-02-24|2015-02-24|NON-CARRIED TANK FOR AIRCRAFT TURBOMACHINE|FR1551586A| FR3032941B1|2015-02-24|2015-02-24|NON-CARRIED TANK FOR AIRCRAFT TURBOMACHINE|
    GB1603038.9A| GB2536796B|2015-02-24|2016-02-22|Unducted fan for an aircraft turbine engine|
    US15/050,637| US10118710B2|2015-02-24|2016-02-23|Unducted fan for an aircraft turbine engine|
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