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    • 专利摘要:
    Blower module (1) with variable pitch blades (5) for a propulsion unit (2) comprising: - a rotor (3) carrying the blades (5), and comprising an internal shaft (10) and a ferrule (11) external device defining between them a space (14); a control device (22) for setting the blades (5); a feathering device (38) for the blades (5); - said rotor (3) being guided in rotation by a bearing (7); said module comprises means for recovering and guiding (81) a bearing liquid lubricant (7), said recovery and guiding means (81) being configured to recover and guide said lubricant from an upstream axial end (13) the shell (11), axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.
    公开号:FR3066558A1
    申请号:FR1754380
    申请日:2017-05-18
    公开日:2018-11-23
    发明作者:Alain Marie Charier Gilles；Morgane Lemarchand Kevin
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    VARIABLE SET BLADES BLOWER MODULE
    TECHNICAL AREA
    The present invention relates to a faired fan module with variable pitch blades for a propulsion unit, and more precisely a blade feathering device adapted to such a fan.
    STATE OF THE ART
    A blower fitted with variable-pitch blades makes it possible to adjust the pitch (and more precisely the wedge angle) of the blades according to the flight parameters, and thus to optimize the operation of the blower, and in general of the propulsion unit in which such a blower is integrated. As a reminder, the pitch angle of a blade corresponds to the angle, in a longitudinal plane perpendicular to the axis of rotation of the blade, between the chord of the blade and the plane of rotation of the fan.
    To be certified, such a blower must include a device for feathering the blades, that is to say a device making it possible to position the blades in a position in which the latter are best erased relative to the direction of advance. . Generally, in flag position, the pitch angle of the blades is 90 °. The blades are for example put in flag position during a failure (or breakdown) of the device for controlling the setting of the blades (for example a failure of a hydraulic actuator) so that the latter offer the least resistance (drag) possible .
    To increase the performance of the blower, engine manufacturers continually seek to reduce the hub ratio of the blower. This hub ratio is the quotient between the diameter of the outer shell of the blade roots at the leading edge of the blades, and the diameter of the circle passing through the outer radial ends of these blades. With an equal fan diameter, the decrease in the hub ratio, that is to say the diameter of the external casing, implies an increase in the suction section of the blower, that is to say an increase in the flow rate. treated, and therefore an improvement in its propulsive efficiency.
    Traditionally, the blade feathering device is placed, in an enclosure, radially between the device for controlling the setting of the blades and the blade pivots, the latter being specific to each blade or common to all the blades.
    The blower comprises a rotor movable relative to a fixed casing, the rotor carrying a series of blades with variable pitch. The rotor is guided in rotation relative to the fixed casing via several bearings. Given the operating conditions, i.e. bearings subjected to high speeds and heavily loaded, lubrication of the bearings via a liquid lubricant (generally oil) is necessary.
    However, the lubricant must not adversely affect the functioning of the internal devices (and in particular of the blade feathering device) present in the enclosure, for example by polluting these devices via a deposit of impurities. On the other hand, the lubricant must not remain trapped (or stored) in cavities of the enclosure so as not to create imbalances harmful to the dynamic balance of the blower rotor.
    The objective of the present invention is thus to propose a blower module meeting the aforementioned constraints.
    STATEMENT OF THE INVENTION
    To this end, the invention proposes a fan module with variable pitch blades for a propulsion unit of longitudinal X axis, said module comprising:
    - A rotor carrying the blades, and comprising an internal annular shaft and an external annular ferrule extending around the shaft and of which an upstream axial end is connected to an axial upstream end of the ferrule, the shaft and the ferrule defining between them an annular space;
    a device for controlling the setting of the blades, said device being located in said space and comprising a load transfer bearing;
    - a feathering device for the blades, in particular in the event of failure of said control device, located upstream of the load transfer bearing;
    - Said rotor being guided in rotation relative to the casing by at least a first bearing located in the vicinity of the upstream axial ends, said first bearing having an inside diameter smaller than the inside diameter of the load transfer bearing and being located upstream of the device for feathering of the blades;
    characterized in that said module comprises means for recovering and guiding a liquid lubricant from the bearing, said means for recovering and guiding being configured to recover and guide said lubricant from said axial end upstream of the ferrule, axially of the upstream downstream and radially from the inside to the outside, under the centrifugal effect.
    Such means for recovering and guiding the lubricant, placed in the enclosure, make it possible in particular to prevent the feathering device from being polluted by the lubricant, for example by a deposit of impurities.
    In addition, the lubricant thus flows into the enclosure along a determined path so as to have no undesirable storage areas, causing unbalances harmful to the dynamic balance of the fan rotor.
    Controlling the path of the lubricant also makes it possible to minimize the amount of lubricant necessary for the lubrication of the bearings.
    The blower module according to the invention may include one or more of the following characteristics, taken in isolation from one another or in combination with each other:
    - Said recovery and guide means comprise an internal annular deflector secured to said ferrule and an external annular deflector secured to said control device, said external deflector being able to at least partially envelop said internal deflector;
    - Said external deflector comprises a flange screwed into an external synchronization ring of said control device, and one downstream face of which is in abutment against an external ring of said load transfer bearing and an upstream face is in abutment against axial holding means ;
    - Said downstream face comprises radial notches for passage of said lubricant and an internal circumferential surface of said external synchronization ring opposite said external ring of said load transfer bearing comprises axial notches for passage of said lubricant;
    - Said rotor is guided in rotation relative to the casing by at least a second and a third bearing located downstream of the load transfer bearing, said third bearing having an internal diameter greater than the internal diameter of the load transfer bearing;
    - Said third bearing guides said ferrule relative to the casing, said third bearing is a rolling bearing comprising an outer ring and an inner ring separated by rolling elements, said outer ring of said rolling bearing is mounted in an annular crown attached to said housing and in that said inner ring of said rolling bearing is mounted on an annular platform attached to said ferrule;
    - The platform comprises a plurality of openings for the passage of said lubricant;
    the ferrule comprises a ring comprising bases for supporting the blades, said ferrule comprising between two successive bases an axial path for the passage of said lubricant;
    - at least one of said bearings is lubricated via a nozzle.
    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 non-limiting example and with reference to the accompanying drawings in which:
    - Figure 1 is an axial (or longitudinal) half-section view of a blower module comprising a device for feathering the blades, in a first position, along an axial plane passing through the axis of rotation of a fan blade;
    - Figure 2 is an axial half-sectional view of the blower module of Figure 1 in which the blade feathering device is in a second position, along an axial plane passing outside the axis of rotation of a fan blade;
    - Figure 3 is a detailed perspective view, in axial half-section, of a mechanism of the feathering device of the blades of Figure 1;
    - Figure 4 is a detailed perspective view, in axial half-section, of a mechanism of the feathering device of the blades of Figure 2;
    - Figure 5 is a detailed perspective view of the feathering device of the blades of Figures 1 and 3;
    - Figure 6 is a detailed perspective view of the feathering device of the blades of Figures 2 and 4;
    - Figure 7 is a detailed perspective view of the mechanism of the feathering device of the blades of Figures 1, 3 and 5;
    - Figure 8 is a detailed perspective view of the mechanism of the feathering device of the blades of Figures 2, 4 and 6;
    - Figure 9 is a schematic view in radial (or transverse) section of a mechanism of the blade feathering device, along a plane passing through the axis of rotation of a lever of said mechanism;
    - Figure 10 corresponds to Figure 1 in which are illustrated the recovery and guiding of the lubricant inside an annular space of the blower;
    - Figure 11 corresponds to Figure 2 in which are illustrated the recovery and guiding of the lubricant inside the annular space of the blower;
    - Figure 12 is a perspective view of an alternative embodiment of the feathering device.
    DETAILED DESCRIPTION
    In Figure 1 is shown a fan 1 faired with a propulsion unit 2 of longitudinal X axis. The blower 1 comprises a rotor 3 movable around the axis X relative to a fixed casing 4, the rotor 3 carrying a series of blades 5 with variable pitch. The blower 1 is here placed upstream of the engine part of the propulsion unit 2 which comprises, for example successively from upstream to downstream, a gas generator and a power turbine which drives the rotor 3 of the blower 1 via a reduction gear 6 speed.
    By convention, in the present application, the terms “upstream” and “downstream” are defined with respect to the direction of circulation of the gases in the fan 1 (or propulsion unit 2). Similarly, by convention in the present application, the terms “internal” and “external”, “interior” and “exterior” are defined radially with respect to the longitudinal (or axial) axis X of the propulsion unit 2, which is in particular the axis of rotation of the rotors of the compressors and turbines of the gas generator.
    The rotor 3 is guided in rotation relative to the fixed casing 4 by at least a first bearing 7 located upstream and at least a second and a third bearings 8, 9 located downstream. The rotor 3 includes an internal annular shaft 10 centered on the axis X, and an external annular ferrule 11 centered on the axis X and extending around the shaft 10. An axial end 12 upstream of the shaft 10 is flanged at an axial end 13 upstream of the ferrule 11, the shaft 10 and the ferrule 11 defining between them an annular space 14 commonly called “oil enclosure”.
    According to the embodiment illustrated in the figures and in particular Figures 1 and 2, the shaft 10 and the ferrule 11 form a pin, in axial half-section. The shaft 10 of the rotor 3 is driven by the power turbine via the speed reducer 6. The ferrule 11 comprises from upstream to downstream a frustoconical wall 15 widening from upstream to downstream (relative to the axis X) and a ring 16 for supporting the blades 5, this ring 16 being clamped on the wall
    15. The rotor 3 further comprises a cone 17 for inlet of the fan 1, centered on the axis X and flaring upstream from the downstream.
    More specifically, each blade 5 comprises a foot which is for example in the form of a bulbous attachment, this foot being integral with a pivot 18 mounted in a housing 19 of a base 20a projecting from the ring 16 movably in rotation about a substantially radial Y axis via two rolling bearings. Referring to Figure 2, the ring 16 comprises a substantially flat pan 20b between two successive bases 20a.
    The feet of the blades 5 are covered by an outer annular envelope 21 centered on X of substantially circular section, the latter being substantially tangent to the downstream end of the cone 17, to ensure aerodynamic continuity. The pivot 18 of each blade 5 is isolated from the annular space 14 by means of a cover (not shown). The rolling bearings placed in each housing 19 are generally lubricated with grease.
    As a reminder, the diameter of the outer casing 21 at the leading edge of the blades 5 is one of the components which makes it possible to determine the hub ratio.
    The fan 1 comprises a device 22 for controlling the setting of the blades 5 (or not of the blades 5) around their axis Y, and more precisely of the setting angle of the blades 5 which corresponds for a blade 5 to the angle, in a longitudinal plane perpendicular to the axis Y, between the chord of the blade 5 and the plane of rotation of the fan 1. The control device 22 is located in the annular space 14.
    The blades 5 are positioned in the "reverse thrust" position (known by the English designation "reverse") in FIGS. 1, 3, 5, 7 and 10. In the "reverse thrust" position, the setting angle of the blades 5 is negative. This position of the blades 5 makes it possible to generate a counter-thrust, and thus to participate in the slowing down of the aircraft in addition to the brakes so as to reduce its braking distance during landing.
    The blades 5 are positioned in the flag position in FIGS. 2, 4, 6, 8, 11 and 12. In the flag position, the setting angle is positive and generally equal to 90 °. This position of the blades 5 makes it possible to limit the resistance (drag) generated by the latter.
    According to the embodiment illustrated in the figures and in particular Figures 1 and 2, the device 22 for controlling the setting of the blades 5 comprises a linear annular actuator 23, centered on the axis X, common to all the blades 5 and a device transformation 24 of movement specific to each of the blades 5, this transformation device 24 making it possible to transform the linear movement initiated by the actuator 23 into a movement of rotation of the corresponding blade 5.
    More specifically, the linear actuator 23 comprises a fixed body 25 attached to an annular support 26 (centered on X) of the fixed casing 4 and a movable body 27 in translation relative to the fixed body 25 along the axis X. Advantageously , the linear actuator 23 is hydraulic.
    The control device 22 also includes a load transfer bearing 28, better known by the acronym LTB for "Load Transfer Bearing", secured to the movable body 27 and allowing the transmission of the linear movement initiated by the actuator. The load transfer bearing 28 is a rolling bearing (centered on the X axis) comprising an internal ring 29 mounted integrally on an internal synchronizing ring 30 (centered on the X axis) integral with the movable body 27 of the actuator 23, and an external ring 31 housed in an integral manner in an external synchronization ring 32 causing the blades to wedge 5. The internal and external rings 29, 31 define two rolling tracks for rolling elements 33 (here balls 33). The balls 33 are in radial contact with the outer ring 31 and in oblique contact with the inner ring 29.
    The LTB ensures the transmission of the movement initiated by the linear actuator 23 (linked to the casing 4, fixed mark) to the rotary mark (linked to the rotor 3). Having a linear actuator in a fixed frame makes it easier to supply oil and reduce the masses in rotation.
    The device 24 for transforming the linear movement into a rotational movement comprises, for each blade 5, a spherical joint 34 (commonly called a ball joint) with radial contact and a crank 35. The spherical joint 34 is mounted integrally in a fork 36 of the external synchronization ring 32. The spherical joint 34 comprises a sphere having a radial hole, this sphere being enclosed in a housing formed by two facing hemispheres defined respectively in two half-rings. The crank 35 comprises at each end a finger 37 projecting in opposite directions, one of the fingers 37 being mounted in free rotation and in translation in the hole of the corresponding sphere along an axis B (substantially radial) and l the other being coupled in rotation with the pivot 18 of corresponding blade 5 (via for example a connection by splines). The axis B is offset with respect to the axis Y of rotation of the blade 5. The crank 35 makes it possible to increase the effort necessary to adjust the setting of the corresponding blade 5.
    The linear movement of the movable body 27 of the actuator 23 allows the timing of all the blades 5 to be adjusted synchronously via in particular the outer ring 31 of the load transfer bearing 28.
    The fan 1 also includes a feathering device 38 for the blades 5, in particular in the event of failure (or failure) of the control device 22, and for example a failure in the hydraulic supply of the linear actuator 23. As a reminder, the flag position corresponds to a positive setting generally equal to 90 °.
    The feathering device 38 comprises at least one mechanism 39 comprising at least one lever 40 articulated around an axis A fixed relative to the rotor 3. The lever 40 has a first end 41 situéeο located outside of the space 14 and a second end 42 located inside the space 14, a counterweight 43 being integral with the first end 41 and the second end 42 being coupled to the load transfer bearing 28. The counterweight 43 is capable, under the centrifugal effect, of being moved into a position (FIGS. 2, 4, 6, 8, 11 and 12) in which the load transfer bearing 28 imposes a flag position on the blades 5.
    According to the embodiment illustrated in FIGS. 5 and 6, the feathering device 38 comprises five mechanisms 39 angularly distributed regularly around the axis X.
    According to the embodiment illustrated in the figures and more specifically Figures 7 to 9, for each mechanism 39, the lever 40 has an L or V shape in axial section (Figures 1 to 4). The lever 40 comprises two synchronized parallel arms 44 located outside the space 14 and a connecting rod 45 located inside the space 14. The arms 44 and the connecting rod 45 are linked in rotation and articulated around the axis A relative to a cap of the ferrule 11, by means of an axis 47 centered on the axis A. The axis A is here rectilinear and perpendicular to the axis X. The length of an arm 44 is greater than the length of the connecting rod 45, approximately twice greater in the present case. This length ratio makes it possible to multiply the effort provided by each flyweight 43, and in other words to minimize their mass, and more generally, the mass of all the flyweights 43.
    More precisely, as illustrated in FIG. 9, the axis 47 crosses (transversely) right through the cap 46 and is guided in rotation relative to the bearing surfaces 48 of the latter via means for guiding in rotation 49. The rotating guide means 49 are for example bearings and / or rolling bearings, etc. The arms 44 laterally border the cap 46, each of them being linked in rotation to the axis 47 by first rotational connection means 50. The connecting rod 45 is interposed between the bearing surfaces 48 of the cap 46 and is linked in rotation to the axis by second rotational connection means 51. The first and second rotational connection means 50, 51 are for example pins and / or keys and / or splines, etc. To guarantee the tightness of the articulation between the lever 40 and the cap 46, sealing means 52 are placed between the bearing surfaces 48 of the cap 46 and the axis 47. The axis 47 is stopped axially at one from its ends by a shoulder 53 and by a nut 54 at its opposite end.
    The cap 46 is curved and attached to a boss 55 of the ferrule 11, the boss 55 projecting radially outward. The cap 46 is fixed to the boss 55 by means of three upstream screws 56 and three downstream screws 56 (Figures 7 and 8). The boss 55 and the corresponding cap 46 define internally therebetween, within the space 14, a cavity 57 (FIGS. 1 to 4). Sealing means (not shown) are interposed between the cap 46 and the boss 55, to guarantee sealing between the latter.
    For each mechanism 39, the counterweight 43 is cylindrical with a circular section or another suitable shape, located between the arms 44 and fixed at the ends opposite the axis A by means of screws 59 (FIGS. 7 and 8). The flyweight 43 is able to move in a longitudinal plane P (FIG. 1) perpendicular to the axis A between the shell 11 of the rotor 3, and the cone 17 and the casing 21 of the rotor 3.
    As illustrated in FIGS. 7 and 8, the second end 42 of the lever 40 is coupled to the load transfer bearing 28, and more precisely to the external synchronization ring 32 by means of a link 60. A upstream axial end of the rod 60 is articulated in a yoke 61 of the rod 45 around an axis C and an downstream axial end of the rod 60 is articulated in a yoke 62 of the external synchronization ring 32 around a axis D.
    When the propulsion unit 2 operates normally (no failure), the feathering device 38 is subordinate to the control device 22 for setting the blades 5, and more precisely to the linear actuator 23. Note that when the blades 5 are in the "reverse thrust" position, the flyweights 43 of the mechanisms 39 of the feathering device 38 of the blades 5 are close to and / or in contact with the shell 11 of the rotor 3 (FIGS. 1 , 3, 5, 7).
    In the event of a failure (need to position the blades 5 in flag position), for example a failure in the hydraulic supply of the linear actuator 23, the device 22 for controlling the setting of the blades 5 then becomes subordinate to the setting device. flag 38, and more precisely weights 43 which under the centrifugal effect is found near and / or in contact with the cone 17 (FIGS. 2 and 4), to impose a flag position on the blades 5.
    The rotor 3 is guided in rotation relative to the fixed casing 4 by at least a first bearing 7 located upstream and at least a second and a third bearings 8, 9 located downstream. The first, second and third bearings 7, 8, 9 have an outside diameter greater than the inside diameter of the support 26 under the linear actuator 23. The second and third bearings 8, 9 have an outside diameter greater than the outside diameter of the first upstream bearing 7.
    Such an arrangement and such a dimensioning of the bearings 7, 8, 9 makes it possible to have a more compact annular space (or oil chamber) radially, and thus to minimize the hub ratio, without however degrading the mechanical characteristics of the fan 1. On the other hand, this architecture makes it possible to significantly improve the dynamic balance of the rotor 3. This improvement is explained in particular by the arrangement of the bearings 7, 8, 9 with respect to the resulting force including in particular the forces generated by masses in rotational movement around the axis X (and in particular mass of the control device 22 of the blades 5, mass of the feathering device 38 of the blades 5, mass of the pivots 18 of the blades 5).
    According to the embodiment illustrated in the figures and in particular Figures 1 and 2, the annular support 26 is centered on X and comprises, from upstream to downstream, an upstream section 63 and a downstream section 64 flanged one to the other. The upstream section 63 is substantially frustoconical, the latter widening from downstream to upstream. The downstream section 64 comprises, from upstream to downstream, a cylindrical portion 65 with circular section and a substantially frustoconical portion 66 flaring from upstream to downstream.
    The first and second bearings 7, 8 more precisely make it possible to guide the shaft 10 of the rotor 3 in rotation relative to the fixed casing 4.
    The first bearing 7 is located near the axial ends 12, 13 upstream of the ferrule 11 and the shaft 10, and in other words the first bearing 7 is upstream of the linear actuator 23, of the load transfer bearing 28 and mechanisms 39 of the feathering device 38 of the blades 5. The inside diameter of the first bearing 7 is greater than the outside diameter of the shaft 10 under the linear actuator 23. The first bearing 7 has an internal diameter smaller than the internal diameter of the load transfer bearing 28. The first bearing 7 is a rolling bearing (centered on the X axis) comprising an internal ring 67 mounted on an annular base 68 (centered on the X axis) attached to the shaft 10, and an external ring 69 housed in the upstream section 63 of the support 26. The internal and external rings 67, 69 define a raceway for rolling elements 70 (here cylindrical rollers 70). The first bearing 7 is thus able to essentially support radial loads.
    The second bearing 8 is located downstream of the linear actuator 23 and upstream of the reduction gear 6. The inside diameter of the second bearing 8 is greater than the outside diameter of the first bearing 7. The second bearing 8 is a rolling bearing (centered on the X axis) comprising an inner ring 71 mounted on an annular seat 72 (centered on the X axis) attached to the shaft 10, and an outer ring 73 housed in an annular clip 74 (centered on the X axis) clamped to the fixed casing 4. The internal and external rings 71, 73 define a raceway for rolling elements 75 (here balls 75). The balls are in radial contact with the inner and outer rings 71, 73. The second bearing 8 is thus able to support radial and axial loads.
    The third bearing 9 more precisely makes it possible to guide the ferrule 11 of the rotor 3 in rotation relative to the fixed casing 4.
    The third bearing 9 is located downstream of the control device 22 of the setting of the blades 5 and upstream of the reduction gear 6. The inside and outside diameters of the third bearing 9 are greater than the outside diameter of the second bearing 8. The third bearing 9 has a inner diameter greater than the inner diameter of the load transfer bearing 28. The third bearing 9 is a rolling bearing (centered on the X axis) comprising an internal ring 76 mounted on an annular platform 77 (centered on the X axis) flanged on the ring 16 for supporting the blades 5, and an outer ring 78 housed in a crown 79 (centered on the axis X) flanged to the fixed casing 4. The inner and outer rings 76, 78 define a raceway for rolling elements 80 (here rollers 80). In the same way as the first bearing 7, the third bearing 8 is able to support essentially radial loads.
    It is noted that each of the bearing rings (first bearing 7, second bearing 8 and third bearing 9) is stopped axially at one of its ends by a shoulder and at its opposite end by removable axial retaining means such as a retaining rings.
    According to the embodiment illustrated in the figures, the bearings (first bearing 7, second bearing 8, third bearing 9 and bearing 28 for load transfer) are lubricated using a liquid lubricant such as oil. Advantageously, each of the rolling bearings 7, 8, 9, 28 mentioned above is lubricated via a nozzle.
    For reasons of clarity, the nozzles and the supply ducts are not shown in the figures. The first bearing 7 is for example lubricated via a nozzle placed downstream of the first bearing 7 and fixed to the upstream section 63. The second bearing 8 is for example lubricated via a nozzle placed upstream of the second bearing 8 and fixed to the clip 74 The third bearing 9 is for example lubricated via a nozzle placed downstream of the third bearing 9 and fixed to the crown 79. The load transfer bearing 28 is for example lubricated via a nozzle placed upstream of the movable body 27 and fixed to the internal synchronization ring 30, the lubricant being conveyed to the load transfer bearing 28 via recovery and guide means 81. It is also noted that for the load transfer bearing 28, the nozzle supply duct is telescopic and placed between the movable body 27 of the actuator 23 and the internal synchronization ring 30.
    According to the embodiment illustrated in the figures, the fan 1 comprises means for recovering and guiding 81 of the lubricant from the bearings 7, 8, 9, 28, the means for recovering and guiding 81 being configured to recover and guide the lubricant from the upstream axial end 13 of the shell 11, axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.
    The discharge of the lubricant injected into space 14 (oil chamber) via the different nozzles is common, so as to minimize the components of the hydraulic circuit (in particular the pumps). The lubricant is evacuated via evacuation means 93, schematically represented in FIGS. 10 and 11. Recovery is generally carried out at six o'clock by analogy with the dial of a watch.
    The recovery and guide means 81 comprise an internal annular deflector 82 (centered on the X axis) flanged on the ferrule 11 and an external annular deflector 83 (centered on the X axis) secured to the control device 22 of the blades 5 , the external deflector 83 being capable of more or less enveloping the internal deflector 82 (partly or entirely overlapping), depending on the position of the movable body 27 of the actuator 23.
    More specifically, the external deflector 83 comprises an annular flange 84 threaded externally screwed into the external ring 32 for synchronizing the control device 22 so as to fix the external ring 31. The flange 84 comprises a downstream face 94 bearing against the ring external 31 of the load transfer bearing 28 and an upstream face 95 in abutment against axial holding means 85 (for example a stop ring in rotation of the flange in the present case).
    To allow the lubricant to flow into the space 14, as illustrated in FIG. 10, the downstream face 94 of the collar 84 includes radial notches 86 for the passage of said lubricant. An internal circumferential surface of the external synchronization ring 32 opposite the external ring 31 of the load transfer bearing 28 comprises axial notches 87 for passage of the lubricant. At the downstream end of the external ring 31 of the load transfer bearing 28, the external synchronization ring 32 includes orifices 88 for the passage of the lubricant. The orifices 88 are placed downstream of a lip 89 for guiding the lubricant, this lip 89 projecting from the external synchronization ring 32 towards the outside. The platform 77 includes a plurality of openings 90 for passage of the lubricant. Annular sealing wipers 91 (centered on X) are clamped on the blade support ring 16 5, these wipers 91 surrounding the crown 79 of the fixed casing 4. The wipers 91 are placed opposite abradable coatings so as to form seals of the labyrinth type. Such seals significantly limit the leakage of lubricant and are traditionally used to guarantee the seal between a rotor part and a stator part of an oil enclosure.
    As illustrated in FIGS. 10 and 11, under the centrifugal effect, the lubricant (represented by the dotted arrow) is projected towards the outside, the latter flowing from the upstream axial end 13 of the ferrule 11 , axially from upstream to downstream and radially from the inside to the outside. The lubricant flowing at least successively over (or into) the internal deflector 82, the external deflector 83, the radial cuts 86, the axial cuts 87, the orifices 88, the lip 89, the flaps 20 b or the openings 90, and wipers 91.
    Referring to FIG. 11, it should however be noted that the lubricant flows mainly under the centrifugal effect on the sides 20b of the ring
    16. The ferrule 11 then comprises between two successive bases 20a of the ring 16 a main axial path (flats 20b) for the passage of the lubricant.
    To prevent lubricant from being trapped (or stored) in the cavities 57 and creating unbalances harmful to the dynamic balance of the rotor 3 of the fan 1, for each mechanism 39 of the feathered device 38 of the blades 5, a drain 92 collects the lubricant present in the corresponding cavity 57 and then discharges it into a downstream part of the space 14. Each drain 92 is here of circular section and inclined from the inside to the outside in order to facilitate the flow of the lubricant. Each drain 92 discharges the lubricant into the space 14 downstream of the blade support ring 16 5.
    An alternative embodiment is shown in FIG. 12, the feathering device 38 for the blades 5 comprises ten mechanisms 39 distributed angularly in a regular manner around the axis X.
    It is noted that the example illustrated in the figures is in no way limiting, the feathering device 38 of the blades 5 according to the invention could for example be incorporated into the rotor of a propeller of a turboprop engine or even into the rotor of each of the two propellers of a turbomachine comprising two counter-rotating propellers, better known by the English designation "Open Rotor". In the definition of the invention, the term "fan" also covers the propeller or propellers of such turbomachinery.
    Such a feathering device 38 applies more generally to any turbomachine comprising a device for controlling the setting of the blades for which a feathering device is necessary.
    权利要求:
    Claims (9)
    [1" id="c-fr-0001]
    1. Blower module (1) with blades (5) with variable setting for a propulsion unit (2) of longitudinal axis (X), said module comprising:
    - A rotor (3) carrying the blades (5), and comprising an internal annular shaft (10) and an external annular ferrule (11) extending around the shaft (10) and one end (12) of which is axial upstream is connected to an axial end (13) upstream of the ferrule (11), the shaft (10) and the ferrule (11) defining between them an annular space (14);
    - a control device (22) for setting the blades (5), said device (22) being located in said space (14) and comprising a load transfer bearing (28);
    - a feathering device (38) of the blades (5), in particular in the event of failure of said control device (22), located upstream of the load transfer bearing (28);
    - Said rotor (3) being guided in rotation relative to the casing (4) by at least a first bearing (7) located in the vicinity of the upstream axial ends (12, 13), said first bearing (7) having a smaller internal diameter the inside diameter of the load transfer bearing (28) and being located upstream of the feathering device (38) of the blades (5);
    characterized in that said module comprises means for recovering and guiding (81) a liquid lubricant from the bearing (7), said means for recovering and guiding (81) being configured to recover and guide said lubricant from said end ( 13) axial upstream of the shell (11), axially from upstream to downstream and radially from the inside to the outside, under the centrifugal effect.
    [2" id="c-fr-0002]
    2. Blower module (1) according to claim 1, characterized in that said recovery and guide means (81) comprise an internal annular deflector (82) integral with said ferrule (11) and an external annular deflector (83) integral with said control device (22), said external deflector (83) being capable of at least partially enveloping said internal deflector (82).
    [3" id="c-fr-0003]
    3. Blower module (1) according to claim 2, characterized in that said external deflector (83) comprises a flange (84) screwed into a ring (32) external synchronization of said control device (22), and one of which downstream face (94) bears against an external ring (31) of said load transfer bearing (28) and an upstream face (95) bears against axial holding means (85).
    [4" id="c-fr-0004]
    4. Blower module (1) according to claim 3, characterized in that said downstream face (94) comprises radial notches (86) for the passage of said lubricant and an internal circumferential surface of said external synchronization ring (32) opposite said outer ring (31) of said load transfer bearing (28) comprises axial notches (87) for passage of said lubricant.
    [5" id="c-fr-0005]
    5. Blower module (1) according to one of the preceding claims, characterized in that said rotor (3) is guided in rotation relative to the casing (4) by at least a second and a third bearing (8, 9) located downstream of the load transfer bearing (28), said third bearing (9) having an internal diameter greater than the internal diameter of the load transfer bearing (28).
    [6" id="c-fr-0006]
    6. Blower module (1) according to claim 5, characterized in that said third bearing (9) guides said ferrule (11) relative to the casing (4), said third bearing (9) is a rolling bearing comprising a outer ring (78) and an inner ring (76) separated by rolling elements (80), said outer ring (78) of said rolling bearing is mounted in an annular ring (79) attached to said casing (4) and in that that said inner ring (76) of said rolling bearing is mounted on an annular platform (77) attached to said ferrule (11).
    [7" id="c-fr-0007]
    7. Blower module (1) according to claim 6, characterized in that the platform (77) comprises a plurality of openings (90) for the passage of said lubricant.
    [8" id="c-fr-0008]
    8. Blower module (1) according to one of the preceding claims, characterized in that the ferrule (11) comprises a ring (16)
    10 comprising bases (20a) for supporting the blades (5), said ferrule (11) comprising between two successive bases (20a) an axial path for the passage of said lubricant.
    [9" id="c-fr-0009]
    9. Blower module (1) according to one of the preceding claims, characterized in that at least one of said bearings (7, 9, 28) is lubricated via a nozzle.
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    同族专利:
    公开号 | 公开日
    GB2564754A|2019-01-23|
    FR3066558B1|2019-07-19|
    US10533573B2|2020-01-14|
    GB2564754B|2021-06-23|
    GB201808040D0|2018-07-04|
    US20180335046A1|2018-11-22|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5272868A|1993-04-05|1993-12-28|General Electric Company|Gas turbine engine lubrication system|
    FR2918120A1|2007-06-28|2009-01-02|Snecma Sa|DOUBLE BLOWER TURBOMACHINE|
    FR2977636A1|2011-07-06|2013-01-11|Snecma|Device for lubricating rolling bearing of double helix turbopropeller of airplane, has flow channel opening to downstream level of downstream roller bearing, and lubricating oil jet opening longitudinally at upstream end of channel|
    WO2014013201A1|2012-07-20|2014-01-23|Snecma|Device for the transfer of heat between a lubrication pipe and a turbomachine blade pitch actuator control hydraulic pipe|
    US20140205457A1|2013-01-18|2014-07-24|Snecma|System for changing the pitch of the blades of a propeller|
    US10508598B2|2014-01-15|2019-12-17|United Technologies Corporation|Cooling systems for gas turbine engines|
    FR3066559B1|2017-05-18|2019-06-07|Safran Aircraft Engines|BLOWER MODULE WITH VARIABLE SHAFT BLADES|
    FR3086341B1|2018-09-24|2020-11-27|Safran Aircraft Engines|TURBOMACHINE WITH REDUCER FOR AN AIRCRAFT|
    法律状态:
    2018-04-23| PLFP| Fee payment|Year of fee payment: 2 |
    2018-11-23| PLSC| Search report ready|Effective date: 20181123 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 3 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 4 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 5 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1754380A|FR3066558B1|2017-05-18|2017-05-18|BLOWER MODULE WITH VARIABLE SHAFT BLADES|
    FR1754380|2017-05-18|FR1754380A| FR3066558B1|2017-05-18|2017-05-18|BLOWER MODULE WITH VARIABLE SHAFT BLADES|
    US15/982,866| US10533573B2|2017-05-18|2018-05-17|Fan module with variable pitch blades|
    GB1808040.8A| GB2564754B|2017-05-18|2018-05-17|Fan module with variable pitch blades|
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