• 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 present invention relates to an epicyclic reduction device (70) for driving in rotation a first set of blades of a turbomachine, comprising a sun gear (74) centered on a longitudinal axis (12) of the turbomachine and which is connected to a rotor (76) of the turbomachine to be rotated; at least one satellite (78) meshing with the sun gear; a planet carrier (80) rotatably supporting the satellite and connected to a first set of blades (82) for rotating it; and a ring gear (72) meshing with the satellite; the sun gear being connected to the rotor through a first homokinetic ball joint (84).
    公开号:FR3016189A1
    申请号:FR1450080
    申请日:2014-01-07
    公开日:2015-07-10
    发明作者:Augustin Curlier；Julien Michel Patrick Christian Austruy；Tewfik Boudebiza；Gilles Alain Charier
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] BACKGROUND OF THE INVENTION The present invention relates to the general field of geared turbine turbomachines driven in rotation by means of a single turbine. It therefore finds application to both single and double helix airplane propellers comprising a set of blades or two contrarotating sets of unducted blades, and to single or double fan airplane turbojets comprising a set of blades or two counter-rotating sets. of keeled blades. It is more specifically an epicyclic reduction device used between the rotor shaft of the turbine and the one or more rotary drive shafts or sets of blades actuated by the turbine. As is known, a twin-propeller airplane turboprop comprises two counter-rotating sets of unducted blades. In certain twin-propeller turboprop architectures, the two sets of blades are driven directly in rotation by a power turbine with two counter-rotating rotors. In other architectures more particularly concerned by the present invention, the blade assemblies are driven by one and the same rotor of the power turbine. For example, reference may be made to FR2979121, which describes an exemplary embodiment of such an architecture. The counter-rotating propellers of such a turboprop can be rotated directly or indirectly through a mechanical transmission device forming a gear and comprising an epicyclic gear. Generally, this planetary gear train comprises a set of rolling elements with straight teeth including a sun gear which is centered on the longitudinal axis of the turboprop and which is connected upstream to the rotor of the power turbine to be driven by it. . Downstream, this sun gear output its rotational movement, with a different speed and torque, on the crown and the planet carrier, the two sets of blades of the turboprop.
    [0002] Given the mechanical environment in which the turboprop operates, the misalignments between the shafts of the shafts connected to the different rolling elements of the epicyclic reduction gear are reflected directly in their teeth. These teeth acting as a fulcrum so that the misaligned shafts connect coaxially, either undergo premature wear extremely deleterious to the lifetime of the gear as a whole or require increased material thicknesses likely to generate stresses of very penalizing integrations for the development of an embedded device whose mass and size must necessarily be minimized. To significantly reduce the stress concentration in the straight teeth of this epicyclic reduction gear, it is known to create a difference in bending stiffness of the input and output shafts of the gearbox, which has the effect of reducing the effort required. so that the ends of these trees are coaxial. Any misalignments between shafts are thus compensated for by the displacements on the shafts and are then reflected in the level of the contacts between the right teeth of the rolling elements of the epicyclic reduction gear by the relative sliding thereof. However, this solution still has many disadvantages. Apart from the fact that the power density of such an epicyclic gearbox with straight teeth is rather low, it generates a large noise, the transmission of the force being interrupted by jolts which occur during the transition of a tooth to the other and that generates a metallic rattling. In addition, repeated mechanical shocks performed on the teeth reduce their life. There is therefore an unmet need for an epicyclic reducer turbine gear reducer whose power density is significantly increased. OBJECT AND SUMMARY OF THE INVENTION The main object of the present invention is therefore to overcome such drawbacks by proposing to increase the misalignment tolerance of the epicyclic reduction gearbox when the turbomachine undergoes deformations in operation while maintaining the degrees of freedom essential to this operation. An object of the invention is also to ensure a continuous transition of the contact between the teeth during the transmission of the effort to suppress the transmission by jerk and the shock phenomena. These objects are achieved by means of an epicyclic reduction device for driving in rotation at least a first set of blades of a turbomachine, comprising a sun gear centered on a longitudinal axis -io of the turbomachine and which is connected to a rotor of the turbomachine to be rotated, at least one satellite meshing with said sun gear, a planet carrier rotatably supporting said at least one satellite and connected to said first set of blades to drive it in rotation, and a crown meshing said at least one satellite, characterized in that said sun gear is connected to said rotor of the turbomachine through a first homokinetic ball joint. The presence at one end of the planet shaft of a constant velocity joint 20 makes it possible to give the shaft a great mechanical flexibility in radial as well as in angular direction so as to enable it to absorb the deformations experienced during operation by the turbomachine. The tolerance to misalignment and the risk of wear of the various elements of the epicyclic reduction gear is thus reinforced. When the turbomachine (turboprop or turbojet) comprises two propellers or counter-rotating blowers, said ring is connected to said second set of blades through a second homokinetic ball joint. Advantageously, said first and second homokinetic ball joint seals are chosen from one of the following: Rzeppa seal, Weiss seal, cross-track seal, double-offset seal. Preferably, said first homokinetic ball joint comprises a first end provided with a flange extending radially outwards, and a second end opposite said first end and provided with an annular portion mounted around said sun gear. by a system of grooves. Said flange of said first homokinetic ball joint can be attached to a flexible drive shaft of said turboprop turbine rotor through a plurality of bolted links. Advantageously, said second homokinetic ball joint comprises a first end provided with a flange extending radially outwards, and a second end opposite said first end and provided with a flange extending radially towards the first end. and secured to a flexible drive shaft of said second set of blades via a plurality of bolted connections.
    [0003] This results in a configuration that further increases the ability to obtain a great flexibility in radial turbine engine turbine shaft of the turbine engine. In a so-called inverted configuration, said flexible drive shaft 20 of said second set of blades is mounted within a steep drive shaft of said first set of blades attached to said planet carrier. In order to cancel the induced axial thrust between the rotating elements 25 of the epicyclic reduction device, said sun gear, said at least one satellite and said ring are split axially and each comprise helical wheels mounted in opposition (so-called double helix). BRIEF DESCRIPTION OF THE DRAWINGS Other features and advantages of the present invention will become more apparent from the description below, made with reference to the accompanying drawings which illustrate an embodiment thereof which is devoid of any limiting character and in which: FIG. 1 is a schematic longitudinal half-sectional view of a twin-propeller turboprop equipped with an epicyclic reduction device according to the invention; FIG. 2 is a detailed view showing the epicyclic reduction device according to the invention; and FIG. 3 is a view illustrating a second embodiment of an epicyclic reduction device according to the invention applied to a single helical turbojet engine. DETAILED DESCRIPTION OF THE INVENTION FIG. 1 very schematically represents an exemplary embodiment of an aircraft propeller turboprop propeller (open rotor pusher) to which the epicyclic reduction device of the invention can be integrated. Such a turboprop engine is well known and will not be described in detail. The turboprop 10 comprises in particular a longitudinal axis 12 and an annular nacelle 14 disposed coaxially around this longitudinal axis. The turboprop 10 further includes, from upstream to downstream, a low-pressure compressor 16, a high-pressure compressor 18, a combustion chamber 20, a high-pressure turbine 22 and an intermediate pressure turbine 24. Downstream of the intermediate pressure turbine 24 is a counter-rotating propeller system, namely a first assembly (upstream or forward) 25a and a second assembly (downstream or rear) 25b of adjustable-pitch blades, driven in rotation by means of a turbine low pressure 26 disposed downstream of the intermediate pressure turbine 24. This low-pressure turbine comprises in particular a rotor 28 which rotates the two sets 25a, 25b of blades via an epicyclic reduction device 30.
    [0004] According to the invention, this epicyclic reduction device 30 comprises a sun gear 32 which is in the form of an externally toothed gear, centered on the longitudinal axis 12 of the turboprop and fixed upstream of the rotor 28 of the low pressure turbine 26. It also comprises at least one satellite 34, and preferably several (for example between three and six), each satellite having the shape of a toothed wheel externally and meshing with the sun gear 32. Each satellite 34 has an axis which is eccentric with respect to the longitudinal axis 12 and is rotatably carried by a planet carrier 36 centered on the longitudinal axis 12, this planet carrier being integral downstream of the upstream assembly 25a of blades so as to be able to directly driving in rotation about the longitudinal axis 12. The epicyclic reduction device 30 also comprises a ring gear 38 centered on the longitudinal axis 12 and meshing each satellite 34 by its teeth. the inner ring, this ring being integral downstream of the downstream assembly 25b of blades so as to drive it directly in rotation about the longitudinal axis 12. This epicyclic reduction gear is said to be inverted because the drive shaft 40 of the downstream propeller at the crown outlet is inside the drive shaft 42 of the upstream propeller at the output of the planet carrier. The advantage of such an inversion is to have a lower torque on the downstream propeller than on the upstream propeller in order to reduce the size of the hub of the downstream propeller and therefore its weight. With this configuration, the upstream propeller rotates against the turbine and the downstream propeller in the same direction as the blower. It is of course possible to have a direct reduction train, the choice of the configuration, direct or inverse (which in turn will influence the choice of flexible or rigid shafts), depending on the desired torque available for each element and the spring of the skilled person. Thus, the rotor 28 of the low-pressure turbine rotates the sun gear 32 of the epicyclic reduction device which itself retransmits this rotational movement, via the planet carrier 36 (via the satellites 34) and the crown 38, both to the upstream assembly 25a and the downstream assembly 25b of blades for rotating them in a contra-rotating manner.
    [0005] As shown in more detail in FIG. 2, the sun gear 32 is flexibly connected to the rotor (flexible in bending) through a first ball transmission joint 44 and the ring gear 38 is connected to the second helix (the second downstream assembly 25b of blades) also flexibly through a second ball transmission joint 46, the planet carrier 36 being for its part connected in a stiff manner to the first propeller (the first assembly 3016 189 7 upstream 25a of blades). More specifically, this first ball transmission joint 44 comprises at a first end, opposite a second end consisting of an annular portion 44a mounted by a spline system 48 on the sun gear 32, a flange 50 extending radially to the outside and which is fixed on a radial flange of a flexible drive shaft 28a integral with the rotor 28 of the low-pressure turbine through a plurality of bolted connections 52. As for the second transmission joint 10 46, its first end is fixed to the ring gear 38 via a plurality of bolted connections 54 and its second end is fixed, also via a plurality of bolted connections 56, to the shaft flexible drive 40 secured to the second set of blades 25b. Likewise, a plurality of bolted connections 58 provide attachment between the planet carrier 36 and the stiff drive shaft 42 integral with the first set of blades 25a. Thus, by coupling the sun gear and the ring gear with their respective shaft thanks to constant velocity ball joint seals enabling the stress concentration in the toothings of the rolling elements to be limited in the event of angular or radial misalignment, the necessity of the degree is eliminated. axial freedom at the level of the teeth (axial offset) essential in the planetary gear trains with straight teeth of the prior art. Note also the flexibility provided by the flexible shafts and the two ball transmission joints. By the use of these homokinetic joints, it is possible to eliminate a degree of freedom in translation and thus to resort to helicoidal teeth instead of straight teeth and, because of the continuity in the transmission of the force, the density is increased. of power of the epicyclic reduction device. In practice, the epicyclic gear train is double, with helical wheels mounted opposite (double helix). In this way, the axial displacement between the rolling elements of the gearbox is zero.
    [0006] The constant velocity ball joints are preferably Rzeppa joints which will be assembled to the rolling elements (planet or crown) depending on the availability that allows integration into the turbomachine. The elements of the ball transmission joint (nuts 44a, 46a, bowl 44b, 46b, cage 44c, 46c and balls 44d, 46d) can be integrated directly to the rolling elements and to the shafts or mounted separately by means of splines 48 to the sun gear 32 or the bolted flange 54 for the ring gear 38 as illustrated in FIG. 2. For low power applications not illustrated, it could also be envisaged to lock the elements of the transmission joint via a circlip and to carry out the training by a simple groove, keeping in contact between tracks and rolling elements can then be provided by a single spring. It should be noted that such constant velocity ball joints are sensitive to the relative axial movements of these different components. Indeed, an axial movement of the nut relative to the bowl may have the effect of loss of contact between the balls of the seal and their bearings. It is therefore necessary to know the possible axial differences between operating shafts and to pre-constrain the seal in order to keep track / ball contact in all cases of loadings encountered. It will be noted that the balls which are held in the same plane by means of a cage, necessary to prevent the balls from escaping during a relative axial distance between the two elements coupled by the seal, can not penetrate into the tracks, so that a compression of the transmission joint does not pose any particular problem. Particular attention will be paid to the radial positioning of the two transmission joints 44, 46 with respect to the bearings 60, 62 carrying the drive shafts of the two propellers. Indeed, if we reason in terms of purely angular misalignment between the rigid drive shaft 42 (connected to the planet carrier) and one of the flexible drive shafts 28a, 40 (connected to the sun gear and the crown) it can be seen that if the center of the bearing surfaces of the transmission joints coincides with the center of rotation of the misaligned shaft, then the rotation is free and no bending stress is induced in the shafts and in the teeth of the rolling elements. The position of this center being unknown and varying according to the loads applied to the engine, it is possible to approximate an "average" position so as to maximize the action of the transmission joints and to reduce the stresses in the shafts. drive and in the teeth, while making flexural flexibilities of flexible drive shafts of the crown and the sun gear. These flexibility makes it possible to resume a possible radial misalignment between two of its drive shafts which it must necessarily reflect some of the constraints related to the bending of these trees in the teeth. Indeed, it appears that during the angular or radial misalignment of the turbine shaft relative to the drive shaft of the first propeller, the geometric configuration of the integral transmission joint of the sun gear will have an influence on the distribution constraints. It is interesting to notice that in case of radial misalignment between the steer shaft of the first propeller and one of the flexible shafts, the device will tend to reduce to a configuration where the two shafts are only misaligned angularly , the only necessary constraints in the teeth being those necessary for bending the flexible shaft to reduce to this configuration. It is therefore particularly interesting to make flexible shafts as flexible as possible. If the foregoing description has been made with respect to Rzeppa joints, it is of course possible to use another type of homokinetic ball joint, such as a Weiss joint, a double offset joint (double offset plunging joint). or a plunging joint. The double-offset and cross-track joints are particularly interesting because they have straight tracks giving an additional degree of freedom (axial) and therefore eliminate the need to add a prestress which could allow some of the thrust forces to pass through. the epicyclic train instead of being communicated to the structure via the bearings of the drive shafts, as mentioned above. In comparison, the allowable angular deflection is less important than for a Rzeppa joint but can reach twenty degrees, which in general is largely sufficient.
    [0007] More particularly, for the cross-track seal VL, the tracks generated by secant curves are straight lines arranged as the edges of a hyperboloid to a web, inclined alternately to the right and to the left. , six in number. They are made in the form of grooves, external in the nut and inside the bowl, matched by balls. Because of the crossed geometry of the tracks, it is essential that the cage, which holds the balls between them, provides an ortho-radial freedom to allow these balls to follow the tracks in case of relative axial movement of the two coupled elements. . Thus, the invention makes it possible to reduce the level of stress in the teeth by introducing an architecture that completely absorbs axial misalignments between driving shafts and therefore between elements constituting the epicyclic reduction device without generating the constraints of the systems of the art. prior. Of course, if the epicyclic reduction device according to the invention has been described with reference to the turboprop engine of FIG. 1, it should be noted that this same architecture is perfectly applicable to a twin-blower type aircraft turbojet engine (the downstream blades are now arranged upstream). Indeed, in this application, the sun gear 32 centered on the longitudinal axis 12 of the turbojet is then secured downstream of the rotor 28 of the low pressure turbine 26. The satellites 34 25 meshing with the sun gear 32 each have an axis which eccentric with respect to the longitudinal axis 12 and are rotatably carried by a planet carrier 36 centered on this longitudinal axis, the planet carrier being secured upstream of the first blade assembly 25a of the fan so as to be able to directly resulting in rotation about the longitudinal axis 12. Finally, the ring gear 38 centered on the longitudinal axis 12 and meshing with each satellite 34 is secured upstream of the second set 25b of blades so as to be able to drive the fan directly into position. rotation about the longitudinal axis 12.
    [0008] Similarly, if the invention has been applied in the two previous embodiments to a gearbox acting differentially on two sets of counter-rotating blades, it is clear that it can be applied just as well. as illustrated in FIG. 3, to a gearbox acting on a single propeller or blower and in which one of the elements of the gearbox is blocked (the problem of the constraints in the teeth being the same).
    [0009] Indeed, in such a turbomachine gearbox (propeller turboprop or turbojet blower), the reducer 70 is interposed between the low pressure compressor which can be driven at high speed and the blower which can instead be driven at reduced speed. This reducer 70 conventionally comprises a fixed ring gear 72, a sun gear 74 driven by the low pressure shaft 76 of the rotor of the low pressure compressor and the satellites 78 driving, via their planet carrier 80, the fan shaft 82 of the fan .
    [0010] In contrast to the previous embodiment, the epicyclic gear train used is a conventional and non-differential gear with an input, the low-pressure shaft 76, and an output, the fan shaft 82. According to the invention, the gear shaft With the blower being stiff, the flexibility is obtained at the level of the low-pressure shaft which is connected to the sun gear by a homokinetic ball joint 84. More precisely, this homokinetic ball-bearing joint 84 comprises at an opposite upstream end. at a downstream end consisting of an annular portion 84a mounted by a spline system 86 on the sun gear 74, a flange 88 extending radially outward and which is fixed to a radial flange of the low pressure shaft 76 through a plurality of bolted connections 90. When the gearbox is plain bearings, the homokinetic ball joint is advantageously a Rzeppa or W joint. eiss not to have an axial degree of freedom. The assembly thus obtained is then isostatic. On the other hand, if the gearbox comprises barrel bearings, the homokinetic ball-bearing joint is advantageously a double-offset or cross-track seal, a splined sliding connection between the ring gear and the casing (not shown) then to be provided for remove the additional degree of freedom conferred by the seal.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. An epicyclic reduction device (30, 70) for driving in rotation at least a first set of blades of a turbomachine, comprising: a sun gear (32, 74) centered on a longitudinal axis (12) of the turbomachine and which is connected to a rotor (28, 76) of the turbomachine to be rotated; at least one satellite (34, 78) meshing with said sun gear; a planet carrier (36, 80) rotatably supporting said at least one satellite and connected to said at least one first set of blades (25a, 82) to rotate it; and a ring gear (38, 72) meshing said at least one satellite; characterized in that said sun gear is connected to said rotor of the turbomachine through a first homokinetic ball joint (44, 84).
    [0002]
    2. Device according to claim 1, wherein said first homokinetic ball joint is chosen from one of the following: Rzeppa seal, Weiss seal, cross-track seal, double-offset seal.
    [0003]
    Apparatus according to any one of claims 1 and 2, wherein said first constant velocity ball joint comprises a first end provided with a radially outwardly extending flange (50, 88), and a second end opposite said first end and provided with an annular portion (44a, 84a) mounted around said sun gear by a spline system (48, 86).
    [0004]
    4. Device according to claim 3, wherein said flange of said first homokinetic ball joint is fixed on a flexible drive shaft (28a, 76) of said rotor of the turbomachine via a plurality of bolted connections. (52, 90).
    [0005]
    5. Device according to claim 1 or claim 2, wherein said ring is connected to a second set of blades (25b) through a second homokinetic ball joint (46).
    [0006]
    6. Device according to claim 5, wherein said second homokinetic ball joint is chosen from one of the following: Rzeppa seal, Weiss seal, cross-track seal, double-offset seal.
    [0007]
    7. Device according to claim 5 or 6, wherein said second homokinetic ball joint comprises a first end provided with a flange extending radially outwardly and a second end opposite said first end and provided with a flange extending radially inwardly and secured to a flexible drive shaft (40) of said second set of blades via a plurality of bolted connections (56).
    [0008]
    The apparatus of claim 7, wherein said flexible drive shaft of said second set of blades is mounted within a steep drive shaft (42) of said first set of blades attached to said planet carrier.
    [0009]
    9. Device according to any one of claims 1 to 8, wherein said sun gear, said at least one satellite and said ring are each split axially and comprise helical wheels mounted in opposition (so called double helix) so as to cancel the induced axial thrust.
    [0010]
    10. Device according to claim 5, wherein said first or second sets of blades belong to a single or double propeller of a turboprop or a single or double fan of a turbojet engine.
    类似技术:
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    同族专利:
    公开号 | 公开日
    CN105899794B|2018-03-13|
    FR3016189B1|2018-09-28|
    CA2936046A1|2015-07-16|
    JP6526019B2|2019-06-05|
    EP3092396B1|2019-09-18|
    RU2673639C2|2018-11-28|
    EP3092396A1|2016-11-16|
    WO2015104474A1|2015-07-16|
    JP2017503960A|2017-02-02|
    RU2016132494A3|2018-09-28|
    US20160326964A1|2016-11-10|
    CN105899794A|2016-08-24|
    RU2016132494A|2018-02-16|
    US10495005B2|2019-12-03|
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    法律状态:
    2016-01-12| PLFP| Fee payment|Year of fee payment: 3 |
    2017-01-13| PLFP| Fee payment|Year of fee payment: 4 |
    2017-12-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-06-29| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2019-12-19| PLFP| Fee payment|Year of fee payment: 7 |
    2021-10-08| ST| Notification of lapse|Effective date: 20210905 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1450080A|FR3016189B1|2014-01-07|2014-01-07|EPICYCLOIDAL REDUCTION DEVICE FOR THE ROTATIONAL DRIVE OF BLADE ASSEMBLIES OF A REDUCING TURBOMACHINE|
    FR1450080|2014-01-07|FR1450080A| FR3016189B1|2014-01-07|2014-01-07|EPICYCLOIDAL REDUCTION DEVICE FOR THE ROTATIONAL DRIVE OF BLADE ASSEMBLIES OF A REDUCING TURBOMACHINE|
    CN201480072535.8A| CN105899794B|2014-01-07|2014-12-24|Planetary reducer for the rotation driving of the blade group for the turbine that slows down|
    US15/110,001| US10495005B2|2014-01-07|2014-12-24|Epicyclic reduction device for the rotational drive of blade sets of a reduction turbomachine|
    RU2016132494A| RU2673639C2|2014-01-07|2014-12-24|Planetary gear-down mechanism for driving into rotation blade assemblies of turbo mechanism with gear|
    JP2016545300A| JP6526019B2|2014-01-07|2014-12-24|Planetary gear reducer for rotating set of blades of reducer turbomachine|
    EP14831030.3A| EP3092396B1|2014-01-07|2014-12-24|Epicyclic reduction device for the rotational drive of blade sets of a geared turbomachine|
    CA2936046A| CA2936046A1|2014-01-07|2014-12-24|Epicyclic reduction device for the rotational drive of blade sets of a reduction turbomachine|
    PCT/FR2014/053553| WO2015104474A1|2014-01-07|2014-12-24|Epicyclic reduction device for the rotational drive of blade sets of a reduction turbomachine|
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