• 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 blower comprising: - a blower disc (10) (1), - an inter-blade platform (20) (2) comprising a base (22) and a radial tab (26), a second orifice ( 28) being formed in the tab (26) of the platform (20), and - a lock (30) having a downstream edge (36) configured to bear against the tab (26) of the platform (20), the one of the downstream edge (36) and the yoke (14) of the fan disc (10) (1) comprising a pin (37), the other comprising a first orifice (16), the pin (37) being configured to penetrate into the first orifice (16) and into the second orifice (28) so as to block the platform (20) relative to the fan disc (10) (1).
    公开号:FR3082876A1
    申请号:FR1855479
    申请日:2018-06-21
    公开日:2019-12-27
    发明作者:Jeremy GUIVARC'H；Michel Francois Rene Aubert Fabrice；Martin Michelsen Pierre
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The invention relates to the general field of inter-blade platforms in the blowers of aeronautical turbomachines, in particular when these platforms are made of a composite material comprising a fibrous reinforcement densified by a matrix.
    TECHNOLOGICAL BACKGROUND
    A turbomachine fan includes a rotor disc carrying a plurality of vanes, the feet of which are engaged and retained in substantially axial grooves formed at the periphery of the disc. These blades are associated at their radially inner end with inter-blade platforms, which are arranged in the extension of the inlet cone.
    The platforms make it possible in particular to delimit, on the interior side, the annular air intake passage in the blower, this vein being delimited on the exterior side by a casing. These platforms generally include a base configured to delimit the vein and a box extending radially inward from the base to allow support of the platform on the blower disc. The box is also configured to stiffen the platform to ensure the continuity of the aerodynamic flow in the fan.
    It is known to produce inter-blade platforms for blowers, for example from composite material. The composite material generally comprises a fibrous reinforcement densified by a matrix. Depending on the application envisaged, the preform can be made of glass fibers, carbon or ceramic and the matrix can be made of an organic material (polymer), carbon or ceramic. For parts of relatively complex geometric shape, it is also known to produce a fibrous structure or blank in one piece by three-dimensional or multilayer weaving and to shape the fibrous structure to obtain a fibrous preform having a shape close to that of the part to be manufactured.
    The performance and integration requirements translate into a good control of the sealing of the foot of the fan blade. This tightness is directly controlled by the ability to surround the foot of the dawn by the platforms at all operating points. Up to a certain clearance, it is possible to fill this clearance with the use of a joint. Beyond that, it is no longer possible to provide a seal.
    The performance and integration requirements also translate into an ability to decrease the hub ratio, which corresponds to the ratio between the internal radius and the external radius of the aerodynamic stream, where the internal radius corresponds to the distance between the axis. of revolution of the fan and the surface of the platform which delimits the flow path, at the leading edge of the fan blade, and the external radius corresponds to the distance between the axis of revolution of the fan and the fan casing, at the same level of the blade (ie at the leading edge of the blade, at the intersection with the platform). The lower the hub ratio, the more efficient the blower will be.
    The reduction of this hub ratio very often requires having to reduce the effort passing upstream of the platform and to resume some of this effort elsewhere on the disc. With a disc plane, axis of revolution and aerodynamic stream fixed, the hub ratio will be a function of the distance (height) between the surface of the platform which delimits the flow stream and the radial face of the blower disc. In particular, if this height increases, the hub ratio increases.
    For example, document US 2012/0275921 illustrates a blower disk in which the platform is taken upstream and downstream. However, the upstream attachment is bulky to allow the recovery of centrifugal forces which implies a hub ratio which it may be worthwhile to aim to reduce.
    Document US 2014/0186187 suggests resuming part of the centrifugal forces on an extension projecting from a downstream part of the disc. Such a configuration makes it possible to reduce the size of the fixing in the upstream part, and therefore to reduce the hub ratio. However, this configuration risks degrading the flow of air by the presence of cavities at the level of the screw hole or poor control of the surface appearance.
    It has also been proposed in document FR 3 029 563 in the name of the Applicant to mount the platform on a pin machined from the mass of the disc. However, the larger the fan blade chord, the more pronounced the curvature of the blade and the greater the clearance required for the axial mounting of the fan blade. This configuration therefore requires sufficient clearance, which may prove to be too great to fill depending on the configurations to allow axial mounting of the platform, which results in an opening of the clearances at the extrados trailing edges of the fan blades.
    SUMMARY OF THE INVENTION
    An object of the invention is therefore to provide a blower having the lowest possible hub ratio, in which the inter-blade platforms can be easily attached to the blower disc without degrading the flow stream, whatever the shape. of the flow path they define, while limiting the clearances necessary for mounting the fan blades.
    For this, the invention proposes a turbomachine fan having an axis of revolution and comprising:
    - a fan disc having an upstream face, a radial face configured to receive a series of fan blades and a yoke extending radially with respect to the axis of revolution from the radial face,
    - an inter-blade platform, said platform comprising
    - a base having a first surface configured to delimit a flow vein in the blower and a second surface opposite to the first surface,
    - a lug, extending radially with respect to the axis of revolution on the side of the second surface, and
    - A lock having a downstream edge configured to bear against the tab of the platform, one of the downstream edge of the lock and an upstream face of the yoke of the fan disc comprising a pin, a first orifice being formed in the another among the downstream edge of the bolt and the upstream face of the yoke of the fan disc, and a second orifice being formed in the tab of the platform, the pin being configured to penetrate into the first orifice and into the second orifice so as to block the platform in relation to the blower disc.
    Some preferred but non-limiting characteristics of the blower described above are the following, taken individually or in combination:
    - the pin extends from the downstream edge of the bolt, the first orifice being formed in the upstream face of the yoke.
    - the tab extends between the downstream edge of the bolt and the upstream face of the yoke.
    - the base and the leg are formed integrally and in one piece.
    - The base and the tab are made of a composite material comprising a fibrous reinforcement densified by a polymer matrix.
    - the lock is metallic, preferably titanium, steel or Inconel.
    - The first orifice and the second orifice are through.
    - The base of the platform has an upstream end in which a through passage is formed and the lock comprises an upstream edge configured to penetrate the passage when the downstream edge bears against the tab of the platform.
    - at the upstream face of the disc, the upstream edge of the latch extends in line with the radial face.
    - At least one groove is formed in the radial face of the disc, said groove opening onto the upstream face of the disc and the upstream edge of the lock being bent so as to match the shape of the groove
    - the blower also comprises an added locking ferrule fixed on the one hand to the upstream end of the base of the platform and on the other hand to the upstream face of the blower disc
    - the blower further comprises an attached inlet cone and fixed on the locking ferrule.
    BRIEF DESCRIPTION OF THE DRAWINGS
    Other characteristics, objects and advantages of the present invention will appear better on reading the detailed description which follows, and with regard to the appended drawings given by way of nonlimiting examples and in which:
    Figure 1 is a perspective view of a blower section according to one embodiment.
    Figure 2 is a detailed view of the upstream portion of the blower of Figure 1 when the lock is pressed against the radial face of the blower disc.
    Figure 3 is a sectional view of Figure 1 when the latch pin is engaged in the yoke.
    FIG. 4 is a schematic view in partial section of an exemplary embodiment of a blower on which two forms of platform have been illustrated.
    Figure 5 is a schematic view of an example of a three-dimensional woven fibrous blank according to an embodiment of the invention.
    DETAILED DESCRIPTION OF AN EMBODIMENT
    In the present application, the upstream and downstream are defined with respect to the normal direction of flow of the gas in the fan 1 through the turbomachine. Furthermore, the axis of revolution of the fan 1 turbomachine is called the axis X of radial symmetry of the fan 1. The axial direction corresponds to the direction of the axis X of the fan 1, and a radial direction is a direction perpendicular to and passing through this axis. Likewise, an axial plane is a plane containing the axis X of the fan 1 and a radial plane is a plane perpendicular to this axis X and passing through it. Unless otherwise specified, internal and external will be used, respectively, are used with reference to a radial direction so that the part or the internal face (ie radially internal) of an element is closer to the X axis than the part or the external face (ie radially external) of the same element.
    A turbomachine fan 1 comprises a fan disk 1 carrying a plurality of fan blades 2, associated with inter-blade platforms 2.
    The blades 2 are engaged in axial grooves formed in a radial face 11 of the blower disc 10, corresponding to the outer circumferential face of the disc 10. The blower disc 10 further comprises a yoke 14 extending radially from the radial face 11. The yoke 14 is formed integrally and in one piece with the blower disk 10, for example by machining.
    In a first embodiment, a first orifice 16 is formed in the yoke 14. The first orifice 16 is axial and has an axis of revolution X substantially parallel to the axis of revolution X of the fan 1. The first orifice 16 opens out at least in the upstream face 15 of the yoke 14. Optionally, the first orifice 16 is through.
    Each blade 2 has a foot, engaged in one of the grooves, a head (or top), a leading edge 3 and a trailing edge. The leading edge 3 is configured to extend opposite the flow of gases entering the turbomachine. It corresponds to the front part of an aerodynamic profile which faces the air flow and which divides the air flow into a lower surface flow and into an upper surface flow. The trailing edge corresponds to the rear part of the aerodynamic profile, where the intrados and extrados flows meet.
    The blades 2 are associated at their radially inner end with inter-blade platforms 2, which are arranged in the extension of an inlet cone 50.
    Each platform 20 has a base 22 and a tab 26.
    The base 22 has a first surface 22a configured to delimit radially inside the flow stream in the blower 1 and a second surface 22b opposite the first surface 22a.
    The tab 26 extends radially with respect to the axis of revolution X on the side of the second surface 22b of the base 22. A second orifice 28, one axis of revolution X of which is substantially parallel to the axis of revolution X of the fan 1 is formed in the tab 26.
    The tab 26 is configured to come into contact with the cap when the platform 20 is fixed to the fan disc 10 of the fan 1, so that the second opening 28 of the tab 26 is located opposite the first opening 16 of the yoke 14. The second orifice 28 is through.
    The fan 1 further comprises, for each platform 20, a latch 30 having a downstream edge 36 configured to bear against the tab 26 of the platform 20 and an upstream edge 32 configured to cooperate with the base 22 of the platform 20. In the first embodiment, the downstream edge 36 of the lock 30 is provided with a pin 37 configured to penetrate into the first orifice 16 and into the second orifice 28 so as to axially and radially block the platform 20 relative to the disc 10 of blower 1. For this, the downstream edge 36 of the latch 30 is formed of a radially extending wall having a downstream radial face from which the pin 37 projects. The pin 37 is, in the embodiment illustrated in the figures, formed integrally and in one piece with the downstream edge 36 of the latch 30. As a variant, the pin 37 can be attached to the downstream edge 36.
    It will of course be understood that, in an equivalent manner, the invention also covers a second embodiment (not illustrated in the figures) in which the pin 37 extends axially upstream of the yoke 14 of the fan 10 disc 1 , the first orifice 16 then being formed in the downstream edge 36 of the latch 30. Apart from this inverted configuration for mounting the pin, the other parts of the fan 1 are unchanged.
    The combination of the latch 30, the yoke 14 and the lug 26 makes it possible to axially and radially simply, efficiently and quickly fix the platform 20 on the fan 10 disc 1, while allowing a low ratio to be obtained hub. In addition, the axial position of the tab 26 can be determined and fixed with precision, independently of the material constituting the platform 20, since it is pressed axially against the downstream edge 36 of the latch and against the yoke 14 of the disc 10, which can both be precision machined.
    In one embodiment, the pin 37 can be pre-assembled on the platform 20 and then locked after the platform 20 has been placed on the disc 10.
    The platform 20 has an upstream end 23 configured to cooperate with the upstream edge 32 of the lock 30 and a downstream end 29 configured to come opposite a part extending downstream of the blower 1. Generally, the part downstream of the fan 1 comprises an internal ferrule of an IGV (English acronym for Inlet Guide Vane, that is to say the first stator stage of the booster in the primary body of a turbomachine) or, as a variant, a rotating spacer which is formed an annular flange extending between the fan 1 and the internal shroud of the IGV and which rotates at the same speed as the fan disc 10. The downstream end 29 of the base 22 of the platform 20 and this part (whether it is the internal ferrule of the IGV or the rotating spacer) are then shaped so as to extend in the extension of one another so as to limit the inlet cavities of the primary body of the turbomachine e likely to disturb the primary flow.
    A through passage 21 is formed in the upstream end 23 of the base 22 of the platform 20 and is configured to receive the upstream edge 32 of the latch 30, when its downstream edge 36 is in abutment against the tab 26 of the platform 20 and the plate against the upstream face 15 of the yoke 14. In operation, the upstream edge 32 therefore enters the passage 21. If necessary, the upstream edge 32 of the latch 30 can pass right through the passage 21 and protrude from the upstream end 23 of the base 22.L
    In one embodiment, the upstream edge 32 of the latch 30 extends in the extension of the radial face 11 of the disc 10, or at least of the portion of the disc 10 which opens onto the upstream face 12. Where appropriate, a through hole can be formed in the upstream edge 32 of the latch to allow the passage of a disassembly tool to axially slide the latch upstream side.
    This configuration of the lock 30, and in particular the configuration of its upstream edge 32, makes it possible to make the lock 30 "versatile" in the sense that it adapts to many forms of platforms 20. We can in particular refer to the figure 4, which illustrates very schematically two examples of platform 20, one having a "slope" (inclination relative to the axis of revolution) gentle while the other has a strong "slope" and forms a vein d more aggressive flow. As can be seen in this figure, in these two configurations, the base 22 of the platform 20 passes through the same radius at the plane P of the fan. However, this plane P of the fan corresponds here to the plane normal to the axis of revolution X of the fan which passes through the foot of the fan blades 2 at their leading edge 3. It is therefore the plane at which the hub ratio is measured. We deduce that these two platform configurations have the same hub ratio.
    Furthermore, the axial travel of the mounting of the platform 20 on the disc 10 can be reduced to a minimum and correspond substantially to the distance between the upstream face 12 of the disc 10 and the upstream face 15 of the yoke 14 ..
    The upstream end 23 of the base 22 of the platform 20 is bent and has a first portion 24 which extends radially inwards from the side of the second surface of the base 22 so as to extend along the upstream face 12 of the disc 10, and a second portion 25 which extends axially from the first portion 24 and which is configured to cooperate with a locking ferrule 40. The passage 21 is formed in the first portion 24 of the upstream end 23 from base 22.
    The upstream end 23 of the base 22 of the platform 20 therefore extends upstream relative to the upstream face 12 of the fan 10 disc 1 and radially inside with respect to the radial face 11 of the disc 10. The if necessary, the platform 20 can be brought into abutment against the upstream face 12 of the disc 10, which improves the rigidity of the platform
    20.
    The combination of the upstream edge 35 of the latch 30 extending in the extension of the radial face 11 of the disc 10 and the upstream end 23 of the base 22 which extends along the upstream face 12 of the disc 10 allows '' obtain a blower 1 with a low hub ratio without degrading the clearance at the trailing edge or the quality of the flow stream.
    Optionally, the hub ratio can be further reduced by forming a groove 13 in the radial face 11 of the disc 10, which opens at its upstream face 12, and by shaping the upstream edge 35 of the latch 30 so that it follows the shape of the radial face 11 of the disc 10 at its upstream part. For example, the upstream edge 35 of the latch 30 can be bent so as to match the shape of the groove 13 (FIG. 3). This particular shape of the upstream edge 35 of the latch 30, which is allowed by the formation of the groove 13 in the disc 10, thus makes it possible to offset radially inwards the upstream end 23 of the base 22 of the platform 20, and therefore further reduce the hub ratio of the blower 1. The height between the first surface 22a of the base 22 of the platform 20, which delimits the flow stream, and the radial face 11 of the disc 10 of blower 1 can effect to be weak (of the order of a few millimeters). In particular, the deeper the groove 13 formed in the disc 10, the more this height can be reduced and therefore the lower the hub ratio.
    The groove 13 may be annular. As a variant, several grooves 13 can be formed in the radial face 12 of the disc 10. If necessary, the disc 10 can have as many grooves 13 as there are platforms 20 (see FIGS. 1 and 2) or the same groove 13 can be shared by several platforms 20.
    The fan 1 further comprises the locking ferrule 40 and the inlet cone 50.
    The locking ferrule 40 is attached and fixed on the one hand to the upstream end 23 of the base 22 of the platform 20 and on the other hand to the upstream face 12 of the fan 10 disc 1 in order to block the latch 30 against the upstream face 12 of the fan disc 10. The locking ferrule 40 therefore makes it possible to maintain the position and a radial centering of the platform 20, by blocking the axial movements of the latch 30. The locking ferrule 40 may for example comprise a clamp 42 configured to come to bear on the face radially external to the upstream end 23 of the base 22 and a lug 44 configured to be inserted in a corresponding housing formed in the upstream face 12 of the fan 10 disc 1 and locked in this position by locking means such as a screws and a bolt.
    As for the inlet cone 50, it is attached and fixed to the locking ferrule 40, so as to extend in the extension of the base 22 of the platform 20 by limiting the cavities liable to disturb the flow at the inlet of the fan 1. In the embodiment illustrated in the figures, the inlet cone 50 covers the upstream end 23 of the base 22 and the locking ferrule 40. As a variant, the locking ferrule 40 could comprise a part covering the upstream end 23 of the base 22 and extending in the extension of the radially external surface of the base 22. In this case, the inlet cone 50 extends in the extension of the locking ferrule 40, without covering it.
    The tab 26 and the base 22 of each platform 20 are formed integrally and in one piece.
    In one embodiment, the tab 26 and the base 22 can be made of a composite material comprising a fibrous reinforcement densified by a polymer matrix.
    The fibrous reinforcement can be formed from a fibrous preform obtained by three-dimensional weaving with progressive thickness. It can in particular comprise fibers of carbon, glass, aramid and / or ceramic. As for the matrix, it is typically a polymer matrix, for example epoxide, bismaleimide or polyimide. The blade 1 is then formed by molding by means of a resin injection process of the RTM type (for "Resin Transfer Molding"), or even VARTM (for Vacuum Resin Transfer Molding).
    In order to produce in one piece the base 22 and the tab 26, an open unbinding can be formed so as to allow, from the same three-dimensional preform, to produce these two parts of the platform 20. We can in particular refer in FIG. 5, which schematically represents a chain plan of a three-dimensional woven fibrous blank from which a fibrous platform preform 20 can be shaped, before injection of resin or densification by a matrix and possible machining, in order to 'Obtain a blower platform 1 of composite material such as that illustrated in Figures 1 to 4. By three-dimensional weaving, it will be understood that the warp threads Ci-Cs follow winding paths in order to link weft threads T belonging to layers of different weft threads with the exception of unbinding 106, it being noted that three-dimensional weaving, in particular with interlock weave, can i Include 2D weaves on the surface. Different three-dimensional weaving weaves can be used, such as interlock, multi-satin or multi-veil weaves, for example, as described in particular in document WO 2006/136755. In FIG. 5, the fibrous blank has two opposite surfaces 100a, 100b and comprises a first part 102 and a second part 104. These two parts 102, 104 respectively form a first and a second part of the thickness of the blank fibrous between its opposite surfaces 100a, 100b.
    Each part 102, 104 of the fibrous blank comprises a plurality of superposed layers of weft threads T, four in the example illustrated, the number of weft threads T being able to be any desired number at least equal to two depending on the 'desired thickness. In addition, the numbers of weft son layers in parts 102 and 104 may be different from each other. The weft threads T are arranged in columns each comprising the weft threads T of the first and second parts 102, 104 of the fiber blank. On a portion of the dimension of the fibrous blank in chain direction C, the first part 102 and the second part 104 of the fibrous blank are completely separated from each other by an open debinding 106 which extends to from an upstream limit 106a to a downstream edge 100c of the fibrous blank. By open unbinding 106 is meant here a zone closed at one end and open at an opposite end which is not crossed by warp threads Ci-Cs connecting together weft threads T of layers belonging respectively to two of the layers , in the example here the second part 104 and the second part 104 of the fiber blank.
    With the exception of the open unbinding 108, the layers of weft threads T are linked together by warp threads of a plurality of layers of warp threads Ci to Cs. In the example more precisely illustrated in FIG. 5, the same first warp yarn C4 links together layers of weft yarns T of the first part 102 of the fibrous blank adjacent to the unbinding 106 and layers of yarns of frame T of the second part 102 of the fibrous blank beyond the unbinding 106, that is to say in front of the upstream limit 106a. Of course, this connection could be achieved by several first warp son.
    Conversely, the same second warp yarn C5 binds together layers of weft threads T of the second part 104 of the fiber blank adjacent to the open unbinding 106 and layers of weft threads T of the first part 102 of the fibrous blank beyond the closed unbinding. Of course, this connection could be achieved by several second warp threads. Thus, the path of the warp thread Cs and that of the warp thread Ce intersect at the upstream limit 106a of the open unbinding 106.
    The fibrous preform 10 therefore comprises, in the direction of the warp threads C, a first portion 24 in which the first part 102 and the second part 104 are fixed together so as to form, after injection of the matrix, the downstream part of the platform 20, and a second portion 25 extending between the upstream limit 106a of the unbinding 106 and the downstream edge 100c of the preform, intended to form the upstream part of the base 22 and the tab 26. For this, it suffices, after weaving, to separate the two parts 102 and 104 and to give them the desired shape (and more particularly to form an angle between the isolated portion of the first part 102 of the preform intended to form the base 22 and the isolated portion of the second part 104 of the preform intended to form the tab 26), then placing the preform in the desired configuration in a suitable mold in order to inject the matrix therein under vacuum, in accordance with the usual methods t used (for example by a process of the RTM or VARTM type.
    The second orifice 28 can then be produced by machining in the tab 26. In a variant not shown, this orifice could come from an insert co-molded with the tab 26.
    The thickness of the upstream part of the base 22 and of the tab 26 of the platform 20 can be determined by choosing the number of layers in the first part 102 and the second part 104, respectively, as well as the number and the diameter ( tex) strands in the warp and weft threads in each of these parts. The thickness of the upstream part can therefore be different from that of the downstream part.
    The lock 30 is metallic, preferably titanium, steel or Inconel (such as Inconel 425) in order to guarantee precise machining of the part and a low mass.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Turbomachine fan (1) having an axis of revolution (X) and comprising:
    - a fan disc (10) (1) having an upstream face (12), a radial face (11) configured to receive a series of fan blades (2) (1) and a yoke (14) extending radially with respect to the axis of revolution (X) from the radial face,
    - an inter-blade platform (20) (2), said platform (20) comprising
    - a base (22) having a first surface (22a) configured to delimit a flow vein in the blower (1) and a second surface (22b) opposite the first surface (22a),
    - a tab (26), extending radially with respect to the axis of revolution (X) on the side of the second surface (22b), and
    - a lock (30) having a downstream edge (36) configured to bear against the tab (26) of the platform (20), one of the downstream edge (36) of the lock (30) and an upstream face ( 15) of the yoke (14) of the fan disc (10) (1) comprising a pin (37), a first orifice (16) being formed in the other among the downstream edge (36) of the latch (30) and the upstream face (15) of the yoke (14) of the fan disc (10) (1), and a second orifice (28) being formed in the tab (26) of the platform (20), the pin (37) being configured to enter the first port (16) and the second port (28) so as to block the platform (20) relative to the fan disc (10) (1).
    [2" id="c-fr-0002]
    2. Blower (1) according to claim 1, wherein the pin (37) extends from the downstream edge (36) of the latch (30), the first orifice (16) being formed in the upstream face (15) of the yoke (14).
    [3" id="c-fr-0003]
    3. Blower (1) according to one of claims 1 or 2, wherein the tab (26) extends between the downstream edge (36) of the latch (30) and the upstream face (15) of the yoke (14 ).
    [4" id="c-fr-0004]
    4. Blower (1) according to one of claims 1 to 3, wherein the base (22) and the tab (26) are formed integrally and in one piece.
    [5" id="c-fr-0005]
    5. Blower (1) according to one of claims 1 to 4, wherein the base (22) and the tab (26) are made of a composite material comprising a fibrous reinforcement densified by a polymer matrix.
    [6" id="c-fr-0006]
    6. Blower (1) according to one of claims 1 to 5, wherein the latch (30) is metallic, preferably titanium, steel or Inconel.
    [7" id="c-fr-0007]
    7. Blower (1) according to one of claims 1 to 6, wherein the first port (16) and the second port (28) are through.
    [8" id="c-fr-0008]
    8. Blower (1) according to one of claims 1 to 7, wherein the base (22) of the platform (20) has an upstream end (23) in which is formed a passage (21) passing through and the latch ( 30) comprises an upstream edge (32) configured to penetrate the passage (21) when the downstream edge (36) bears against the tab (26) of the platform (20).
    [9" id="c-fr-0009]
    9. Blower (1) according to claim 8, wherein, at the upstream face (12) of the disc (10), the upstream edge (32) of the latch (30) extends in the extension of the radial face (11).
    [10" id="c-fr-0010]
    10. Blower (1) according to claim 9, in which at least one groove (13) is formed in the radial face (11) of the disc (10), said groove (13) opening onto the upstream face (12) of the disc. and the upstream edge (32) of the lock (20) being bent so as to follow the shape of the groove (13).
    [11" id="c-fr-0011]
    11. Blower (1) according to one of claims 8 to 10, further comprising a locking ferrule (40) attached and fixed on the one hand on the upstream end (23) of the base (22) of the platform (20) and on the other hand
    5 on the upstream face (12) of the fan disc (10) (1).
    [12" id="c-fr-0012]
    12. Blower (1) according to claim 11, further comprising an inlet cone (50) attached and fixed to the locking ferrule (40).
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    EP3589468B1|2021-03-31|Preform and one-piece vane for turbomachine
    FR3108665A1|2021-10-01|Fan rotor with upstream center of gravity vanes
    FR3015638A1|2015-06-26|TURBOMACHINE INJECTION SYSTEM SLIDING RUNNING SEGMENT SEGMENT
    同族专利:
    公开号 | 公开日
    US20190390559A1|2019-12-26|
    US11143047B2|2021-10-12|
    FR3082876B1|2021-01-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    WO2013160584A1|2012-04-26|2013-10-31|Snecma|Fibrous blank woven in one piece by three-dimensional weaving for producing a platform with a closed box structure for a turbomachine fan made of composite material|
    WO2014092925A1|2012-12-14|2014-06-19|United Technologies Corporation|Gas turbine engine fan blade platform seal|
    EP2837774A1|2013-08-14|2015-02-18|Rolls-Royce plc|Annulus filler and corresponding stage and gas turbine engine|
    FR3021693A1|2014-05-28|2015-12-04|Snecma|PLATFORM FOR AUBAGEE WHEEL|
    FR3038654A1|2015-07-08|2017-01-13|Snecma|ASSEMBLY OF A REPORTED PLATFORM OF BLOWER BLADE ON A BLOWER DISK|WO2021176160A1|2020-03-03|2021-09-10|Safran Aircraft Engines|Method for manufacturing a composite platform for an aircraft turbine engine fan|FR2913734B1|2007-03-16|2009-05-01|Snecma Sa|TURBOMACHINE BLOWER|
    US20120275921A1|2011-04-28|2012-11-01|General Electric Company|Turbine engine and load reduction device thereof|
    US9399922B2|2012-12-31|2016-07-26|General Electric Company|Non-integral fan blade platform|
    FR3029563B1|2014-12-08|2020-01-17|Safran Aircraft Engines|LOW HUB RATIO PLATFORM|FR3048997B1|2016-03-21|2020-03-27|Safran Aircraft Engines|BLADE PLATFORM AND AERONAUTICAL TURBOMACHINE BLOWER DISC|
    法律状态:
    2019-05-21| PLFP| Fee payment|Year of fee payment: 2 |
    2019-12-27| PLSC| Search report ready|Effective date: 20191227 |
    2020-05-20| PLFP| Fee payment|Year of fee payment: 3 |
    2021-05-19| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1855479A|FR3082876B1|2018-06-21|2018-06-21|BLOWER INCLUDING A PLATFORM AND A LOCK LOCK|
    FR1855479|2018-06-21|FR1855479A| FR3082876B1|2018-06-21|2018-06-21|BLOWER INCLUDING A PLATFORM AND A LOCK LOCK|
    US16/446,669| US11143047B2|2018-06-21|2019-06-20|Fan including a platform and a locking bolt|
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