• 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:
    A transmission assembly comprising a transmission member and an oil delivery system for supplying oil to the transmission member to provide lubrication thereof. According to the invention, the transmission member (30) comprises at least one rotating pivot (34) rotatable about an axis of rotation and a pivoting part (31) pivotable about the rotary pivot ( 34); the oil distribution system (50) is configured to receive pressurized oil from the oil supply (43a) and to transfer it to at least one oil receiving chamber of the revolving pivot (34); said rotating pivot (34) comprises injection orifices in fluid communication with the oil receiving chamber with the gap (36) separating the rotating pivot (34) and the pivoting part (31) so as to form a bearing fluid; and the transmission assembly (3) is adapted to inject oil into said gap (36) at a first injection pressure at an outer portion (36e) of the interstice (36) directed to the opposite the axis of rotation, and at a second injection pressure at an inner portion (36i) of the gap (36) directed towards the axis of rotation, the second injection pressure being different the first injection pressure.
    公开号:FR3018861A1
    申请号:FR1452462
    申请日:2014-03-24
    公开日:2015-09-25
    发明作者:Augustin Curlier；Yassine Krid
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] FIELD OF THE INVENTION The present disclosure relates to a transmission assembly comprising a transmission member and an oil distribution system for supplying oil to the transmission member to provide lubrication thereof. Such a transmission assembly can in particular be used in the aeronautical field, in turbojet engines or helicopter turbine engines to name just these examples.
    [0002] STATE OF THE PRIOR ART The turbojet engines conventionally encountered today in the field of civil aviation are twin-turbojet turbofan engines. However, due to the ever-increasing constraints on operating costs, which are closely linked to the cost of fuel, which is currently very high, new turbojet projects with lower specific fuel consumption have been proposed. A promising option is to equip the turbojet engine with a speed reducer interposed between the low-pressure compressor and the blower: in this way, it is possible to increase the speed of rotation of the low-pressure body, thus increasing the overall efficiency. of the turbojet, while reducing the speed of the blower, which makes it possible to increase the diameter of the blower, and therefore the rate of dilution of the engine (bypass ratio), while maintaining an acceptable peripheral speed at the end of the blade to limit the occurrence of generating aerodynamic disturbances including noise. Such a turbofan engine with a reducer is shown in FIG. 1, in section along a vertical plane passing through its main axis A. It comprises, from upstream to downstream, a fan 2, a gearbox 3, a low-pressure compressor 4 , a high-pressure compressor 5, a combustion chamber 6, a high-pressure turbine 7 and a low-pressure turbine 8. In such a turbojet engine 1, the high-pressure turbine 7 drives the high-pressure compressor 5 with the aid of A high-pressure shaft 9. The low-pressure turbine 8, also known as a high-speed turbine, drives the low-pressure compressor 4, also called a fast compressor, by means of a low-pressure shaft 10. The turbine 301 8 86 1 2 fast 8 also drives the blower 2 through the speed reducer 3. In this way, the blower 2 can be driven at reduced speed, which is aerodynamically favorable, while the compressor 2 4 pressure can be driven at higher speed, which is favorable from a thermodynamic point of view. As shown in FIG. 2A, this gearbox 3 may be an epicyclic gear train provided with a ring gear 31, a sun gear 32, and planet gears 33 (a single planet gear 33 is shown in this figure for purposes simplification). The planet gears 33 are rotatably mounted on rockets 34 of a planet carrier: each planet pinion 33 thus pivots around the pivot axis P of its respective rocket 34. The bearings 36 between the planet gears 33 and their respective fuses 34 may be smooth, that is to say without a rolling mechanism, and then comprise a film of pressurized oil allowing the lubrication and cooling of the bearings 36 An example of an oil distribution system is given in the French patent application filed under number 13 58581. In a conventional configuration, the ring 31 is fixed to the casing 40, the planet carrier 35 is coupled to the fan shaft 2a, driving the fan 2, and the sun gear 32 is coupled to an end 10a of the low pressure shaft 10. During operation of the turbine engine, due to the rotation of the sun gear 33 and the locking of the crown 31, the planet gears 33 are driven in a race superimposing a rotation about the axis of rotation R of the epicyclic gear train and a pivot about the axis P of their respective fuses 34: therefore, the rockets 34 and the entire planet carrier 35 are rotated about the axis of rotation R of the epicyclic gear train. FIG 26 then schematically illustrates the forces exerted on the oil film present in the gap of the bearing 36 of such a pinion gear 33 in a conventional case. On the one hand, the planet pinion 33 exerts a driving force Fe on the oil film which is retransmitted to the rocket 34 and which tends to drive the planet carrier in rotation about the axis of rotation R: in the rotating reference mark [r, o, P] linked to the rocket 34, this driving force Fe is orthoradial. This driving force generates a pinching of the oil film behind the rocket 34 in the orthoradial direction, which causes an overpressure in this pinch zone and leads to the appearance in the oil film of a gradient Ge orthoradial training gear growing backward.
    [0003] On the other hand, due to the rotation of the rocket 34 about the axis of rotation R, the oil film in the gap 36 is subjected to a centrifugal force Fc which is proportional to the square of the rotational speed around the axis of rotation R and directed radially in the rotating reference mark [r, o, P] linked to the rocket 34. The centrifugal volume forces then generate a centrifugal gradient Gc radially increasing towards the oil film within the oil film. outside. Finally, the gravitational force is also exerted on the oil film but its influence is negligible compared to the driving forces Fe and centrifugal Fc during operation of the reducer.
    [0004] In such a conventional case, the driving gradient and the centrifugal gradient are superimposed to give a distribution of the pressure field shown schematically in FIG. 3. On such a graph, for a given angular coordinate, the curve C is further away from the center of the reference, the higher the pressure prevailing in the gap section considered is high. It can thus be seen that the pressure field C is unbalanced with respect to the orthoradial drive direction. Therefore, on the one hand, the transmission of drive forces from the planet pinion 33 to the rocket 34 is degraded; on the other hand, this increases the risk that the pinion gear 33 does not come into contact with its rocket 34 and thus damage the bearing. To remedy this phenomenon, gearboxes have been proposed in which the carrier is the gearbox member which is connected to the gearbox: therefore, no centrifugal force is applied to the oil film of the gears bearing. satellites. However, this configuration in which it is the carrier-satellite rather than the crown of the gearbox which is linked to the crankcase imposes a range of reduction ratios which is not suitable for certain turbine engine models. There is therefore a real need for a transmission assembly which is at least partially free of the drawbacks inherent in the aforementioned known configurations. The present disclosure relates to a transmission assembly comprising a transmission member and an oil distribution system housed in a housing provided with at least one oil supply, wherein the transmission member comprises at least one rotatable pivot, rotatable about an axis of rotation, and a pivotable portion, pivotable about the rotary pivot, wherein the oil distribution system is configured to receive pressurized oil 10 from the oil supply and to transfer it to at least one oil receiving chamber of the revolving pivot, wherein said revolving pivot comprises injection orifices for fluidic communication with the fluid receiving chamber. oil with the gap separating the rotating pivot and the pivoting part so as to form a fluid bearing, and in which the transmission assembly is adapted to inject oil into said interstice at an angle first injection pressure at an outer portion of the gap directed away from the axis of rotation, and at a second injection pressure at an inner portion of the interstice directed towards the axis of rotation, the second injection pressure 20 being different from the first injection pressure. In such a fluid bearing, due to the rotation of the pivot rotating about the axis of rotation, the oil film in the gap is subjected to centrifugal forces that generate a centrifugal pressure gradient in which the pressure of the oil located in the outer portion of the gap, therefore at a greater radial distance from the axis of rotation, is larger than the pressure of the oil located in the inner portion of the gap; a smaller radial distance from the axis of rotation. With the present transmission assembly, for injecting oil at different pressures into the inner and outer portions of the gap, it is possible to introduce an injection pressure differential into the oil film of the fluid bearing to compensate, at least in part, the centrifugal pressure gradient. Each of these pressures, however, remains above atmospheric pressure.
    [0005] Thus, thanks to this transmission assembly, it is possible to adjust, at least in part, the distribution of the pressure field in the oil film to better control the position of the pivoting portion around the pivot pivot. First of all, this makes it possible to reduce the risk of contact between the pivoting part and the rotating pivot and thus to reduce the wear of the transmission member. In addition, this may make it possible to improve the symmetry of the pressure field around the driving direction in which the driving force exerted by the pivoting part on the rotary pivot is applied, or vice versa, thus improving the energy transfer efficiency between these two bodies and therefore the general performance of the transmission member.
    [0006] In the present description, the terms "axial", "radial", "tangential", "interior", "exterior" and their derivatives are defined with respect to the main axis of the transmission assembly; the term "orthoradial" is defined with respect to such a radial axis. The term "inner portion of the gap" is understood to mean a portion of the gap, the angular amplitude of which is between 10 and 1800, preferably between 10 and 90 °, which extends symmetrically from one side to the other. other of the radial plane passing through the axis of rotation and the axis of the rotating pivot and which is located in the inner half-space defined by the orthoradial plane perpendicular to said radial plane and passing through the axis of the rotating pivot. "Outer portion of the gap" means the portion of the corresponding gap in the outer half-space defined by this orthoradial plane. In some embodiments, the second injection pressure is greater than the first injection pressure. A centripetal injection pressure differential is thus introduced to compensate, at least in part, the centrifugal pressure gradient generated by the centrifugal force forces. In some embodiments, the transmission assembly includes a first oil flow opening through at least a first injection port at the outer portion of the gap, and a second oil flow, separate from the first flow of oil, opening through at least a second injection port at the inner portion of the gap. Due to the independence of the first and second oil flows, it is possible to independently adjust the injection parameters, and in particular the injection pressure, of the oil in the outer portion of the gap of an oil. part, and in the inner portion of the gap on the other hand. In some embodiments, the transmission device further comprises a computer configured to adjust the pressure of the first and / or the second fluid flow as a function of the rotation speed of the pivot rotating about the axis of rotation. The centrifugal force acting on the oil film, and therefore the amplitude of the centrifugal pressure gradient, increases with the speed of rotation of the pivot rotating about the axis of rotation: such a calculator makes it possible to compensate for this increase. also increasing the injection pressure differential. This difference in injection pressure can therefore be zero when the rotational speed of the revolving pivot is zero and increase when this speed increases. In some embodiments, the transmission assembly includes a device for measuring the rotational speed of the pivot rotating about the axis of rotation. In some embodiments, this measuring device comprises a voice wheel. In some embodiments, the computer is configured to follow a control law in which the pressure difference between the first and second injection pressures compensates for at least 70% of the pressure difference of the oil between the inner portions. and outer of the gap caused by the centrifugal force forces during the rotation of the rotating pivot. In this way, the distribution of the pressure field of the ideal situation in which the pressure field is symmetrical with respect to the driving direction is substantially brought closer together. The performance of the transmission member is thus greatly improved. In some embodiments, the computer is configured to follow a control law in which the pressure difference between the first and second pressures makes it possible to guarantee an oil film thickness at least 1.5 times greater than the equivalent roughness. quadratic (in the sense of the mean) of the bearing bodies. In some embodiments, the assembly includes a first oil supply, pressurized by a first pump and supplying the first oil flow, and a second oil supply, pressurized. by a second pump and feeding the second circulation of oil. With these independent power supplies, it is possible to adjust the parameters specific to each upstream oil flow, thus simplifying the configuration of the distribution system. The two pumps can in particular independently adjust the pressure of each of the oil flows. In some embodiments, the oil delivery system includes a rotating portion having a first oil transfer chamber provided with at least a first feed port configured to receive oil from the first feed. oil, and a second oil transfer chamber provided with at least a second feed port configured to receive oil from the second oil supply. In some embodiments, the swivel pivot comprises a first oil receiving chamber, in fluid communication with the outer portion of the gap by said at least one first injection port, and a second oil receiving chamber. in fluid communication with the inner portion of the gap by said at least one second injection port.
    [0007] In some embodiments, the assembly further comprises a first connecting conduit putting in fluid communication the first oil transfer chamber and the first oil receiving chamber, and a second connecting conduit putting in fluid communication with the first second oil transfer chamber and the second oil receiving chamber. In some embodiments, the first and second link conduits are independent. In other embodiments, the first and second connecting ducts are part of the same room provided with two channels.
    [0008] In some embodiments, the oil distribution system is integrally rotated with the rotating pivot of the transmission member. In the present description, the term "oil distribution system is rotatably driven in rotation with the rotating pivot of the transmission member" the fact that the oil distribution system rotates about the axis of rotation substantially at the same speed, and in any case on average at the same speed, as the rotating pivot of the transmission member with a phase shift remaining substantially zero, and in any case no one on average such that a given point in the oil distribution system always substantially faces the same area of the rotating pivot of the transmission member. This definition therefore tolerates small transient speed differences or small transient phase shifts due to parasitic vibrations or in case of acceleration or deceleration of the rotating pivot of the transmission member for example. In some embodiments, at least one oil transfer chamber of the oil distribution system extends over an angular sector strictly less than 360 °. In this way, the oil transfer chamber is not continuous on the complete turn of the oil distribution system, which prevents the oil from rotating within the oil transfer chamber and thus limits the impact of oil movements on the overall dynamics of the oil distribution system. In this way, the oil is in the same frame as the distribution system. In some embodiments, the oil delivery system 20 is connected to the rotating pivot of the transmission member by means of at least one rotational driving device comprising a damper. This rotary drive device provided with this damper makes it possible to drive the oil distribution system in rotation by limiting the transmission of parasitic movements of the transmission member 25 to the oil distribution system. Embodiments of such drive devices are described in French Patent Application Laid-open No. 13,558,581. In some embodiments, the revolving pivot comprises a plurality of first injection ports symmetrically disposed on both sides. the other plane passing through the axis of the rotating pivot and the axis of rotation of the rotating pivot. In certain embodiments, the pivoting pivot comprises a plurality of second injection orifices arranged symmetrically on either side of the plane passing through the axis of the rotary pivot and by the axis of rotation of the rotary pivot. In this way, the injection distribution is symmetrical with respect to the radial direction of the rotating marker, which is better adapted to compensate for the centrifugal gradient, also symmetrical with respect to this radial direction. In some embodiments, the rotating pivot comprises an even number of first injection ports.
    [0009] In some embodiments, the pivot pivot comprises an even number of second injection ports. It is preferable indeed not to inject oil on the radial direction of the rotating mark, either towards the axis of rotation or its opposite. In certain embodiments, the rotary pivot comprises at least one group of two first injection ports separated by an angle of between 100 and 160 °, preferably between 60 ° and 120 °, more preferably equal to 90 ° ± 5 ° _with respect to the axis of the rotating pivot. In some embodiments, the rotating pivot comprises at least one group of two second injection ports separated by an angle of between 10 ° and 160 °, preferably between 60 ° and 120 °, more preferably equal to 90 °. ° ± 5 ° to the axis of the rotating pivot. In some embodiments, the rotating pivot comprises a plurality of groups of first injection ports, preferably two groups. In some embodiments, the swivel comprises a plurality of groups of second injection ports, preferably two groups. In some embodiments, the first injection ports are provided symmetrically with respect to the second injection ports. In some embodiments, the rotating pivot comprises injection ports having different passage sections. This makes it possible to generate different pressure drops during the injection and thus to adjust different injection pressures. It is an alternative or complementary means for generating the injection pressure differential in the interstitial oil film. In particular, in such a case, it is possible to provide a single flow of oil supplying injection orifices having sections of larger passages at the inner portion of the gap rather than at the level of its interior. outer portion. In some embodiments, the bearing between the pivoting portion and the rotating pivot is devoid of a rolling device. In some embodiments, the transmission member is a speed reducer. In some embodiments, the transmission member is of the epicyclic gear type having a carrier. In some embodiments, the planet carrier has a plurality of rotatable pivot pins, each carrying a pivoting satellite pinion. The centrifugal pressure gradient can thus be compensated, at least in part, in the bearings of each of the planet gears of the epicyclic gear train. The present disclosure also relates to a turbomachine comprising a transmission assembly according to any one of the preceding embodiments.
    [0010] In some embodiments, the turbomachine further comprises a low pressure turbine and a blower, and the epicyclic train further comprises a sun gear and a ring gear. In certain embodiments, the ring gear is fixed to the casing, preferably by means of a flexible connection, the sun gear is coupled with the low pressure turbine, preferably by means of a flexible connection, and the The carrier is coupled with the fan, preferably with a stiff connection. The term "flexible connection" means a more flexible connection in flexion than the so-called "stiff" connection. The above-mentioned characteristics and advantages, as well as others, will appear on reading the following detailed description of embodiments of the device and the method proposed. This detailed description refers to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS The accompanying drawings are schematic and are intended primarily to illustrate the principles of the invention. In these drawings, from one figure (FIG) to the other, identical elements (or element parts) are identified by the same reference signs.
    [0011] FIG 1 is an axial sectional view of an example of a turbomachine gearbox.
    [0012] FIG 2A is a diagram of the race of the satellite gear; FIG 2B is a diagram illustrating the forces exerted on the bearing of the satellite gear. FIG 3 is a graph schematically illustrating the distribution 5 of the pressure field in the bearing in the absence of compensation. FIG 4 is a graph schematically illustrating the ideal distribution of the pressure field in the bearing. FIG 5 is a block diagram of the transmission assembly. FIG 6 is a sectional view of the oil distribution system. FIG. 7 is a cross-sectional view of a rocket. DETAILED DESCRIPTION OF THE EMBODIMENT (S) In order to make the invention more concrete, an exemplary transmission assembly is described in detail hereinafter with reference to the accompanying drawings. It is recalled that the invention is not limited to this example. FIG. 1 represents a turbofan engine with a gearbox as described in an introductory manner, comprising a transmission unit 3 according to the invention. This transmission assembly 3 comprises an epicyclic gear train 30 similar to that which has been described by way of introduction with reference to FIG. 2A. The transmission assembly 3 according to the invention is also shown in FIG. 5. It should be noted in particular that, in this example, the ring 31 is fixed to the casing 40 by flexible rings 41, the planet carrier 35 is coupled to the fan shaft 2a, driving the fan 2, by a stiff connection, and that the sun gear 32 is flexibly coupled to a splined end 10a of the low pressure shaft 10. In this example according to the invention, the rockets 34 of the planet gears 33 each comprise a first oil receiving chamber 37a and a second oil receiving chamber 37b fluidly connected to the outer portion 36e of the gap 36 forming the bearing, respectively to the inner portion 36i of the gap 36 of the bearing, by channels passing through the rocket 34 and opening through first injection ports 38a, respectively second injection ports 38b.
    [0013] According to an example of distribution of the injection orifices 38a, 38b around the rocket 34, better visible in FIGS. 6 and 7, the rocket 34 comprises a first series of first injection orifices 38a located in a first axial plane and a second series of first injection orifices 38a located in a second axial plane. In addition, each series of first orifices 38a comprises two first orifices 38a, provided symmetrically on either side of the radial plane and spaced apart by an angle α of about 900. In this example of distribution of the injection orifices, the second injection ports 38b are provided in a similar configuration but symmetrical to the first orifices 38a with respect to the orthoradial plane. The transmission assembly 3 further comprises an oil distribution system 50 for dispensing lubricating oil from a first oil supply 43a, provided by a first pump 44a, and a second oil supply 43b, supplied by a second pump 44b, to the bearings 36 of the planet gears 33. These two power supplies 43a, 43b and their pumps 44a, 44b are provided on the stator of the reduction unit 3. The distribution system 50 will be described in more detail This oil dispensing system 50 firstly comprises a generally annular rotating part 51 provided with a cylindrical outer wall 52 and a front wall 53. The rotating part comprises a first oil transfer chamber 54a extending in an arc of a circle, on an angular sector less than 360 °, inside and along the front portion of the outer wall 52 and along most of the The rotating portion 51 further comprises a second oil transfer chamber 54b whose cross-sectional profile forms an L surrounding the first transfer chamber 54a: it is thus contiguous with the rear portion of the outer wall 52 and the inner portion of the front wall 53. The second transfer chamber 54b also extends over an angular sector less than 360 °, preferably on the same angular sector as the first chamber transfer 54a. An annular ring 55 is attached around the outer wall 52 between a shoulder 56 and a nut 57. The hoop 55 comprises a first series of intake passages 58a, respectively a second series of intake passages 58b, provided in a with respect to intake orifices 59a, 59b respectively, formed in the outer wall 52 and opening into the first transfer chamber 54a, respectively into the second transfer chamber 54b. This oil distribution system 50 then comprises a fixed portion 60, generally annular, mounted against the housing 40 between a shoulder 45 and a nut 46. The fixed portion 60 comprises a first annular cavity 61a and a second annular cavity 61b, all two open on their inner radial sides in the direction of the hoop 55 of the part portion 51. The first cavity 61a, respectively the second cavity 61b, comprises on its outer radial side an orifice 62a, respectively 62b, which is provided vis-à-vis -vis a supply port 47a, respectively 47b, the first oil supply 43a, respectively the second oil supply 43b. The rotating portion 51 of the oil distribution system 50 is mounted on the planet carrier 35 through a plurality of rotational drives (not shown) which may include a damper. Examples of embodiments of such drive devices are described in the French patent application filed under number 13 58581. The rotating part 51 is also mounted in the housing 40 by engaging its hoop 55 in the fixed part 60 of the distribution system of oil, thus closing the first and second cavities 61a, 61b. Annular joints 63 are provided between the rotating part 51 and the hoop 55 in front of the first cavity 61a, between the first and second cavities 61a, 61b, and behind the second cavity 61b in order to ensure the tightness of these cavities 61a and 61b. These seals 63 are preferably composite and include an inner member of the elastomer preload O-ring type and a ring-type outer member comprising PTFE. An example of a seal of this type is the Turcon Glyd Ring seal. In order to transfer the oil from a transfer chamber 54a, 54b to the corresponding oil receiving chambers 37a, 37b of the rockets 34, the front wall 57 of the rotating part 51 of the oil distribution system 50 comprises first and second recesses 71a, 71b provided at locations facing the oil receiving chambers 37a, 37b of the rockets 34 of the planet carrier 35. These recesses 71a, 71b each fluidly communicate with the corresponding oil transfer chamber 54a , 54b using orifices 72a, 72b. Each fuse 34 of the planet carrier 35 comprises, in turn, first and second recesses 73a, 73b that communicate fluidly with the oil-receiving chamber 37. For each fuse 34, a first connecting pipe 70a, respectively a second connecting pipe 70b, is mounted floating, on the one hand, between the side walls of the first recess 73a, respectively of the second recess 73b, of the spindle 34 and, on the other hand, between the side walls of the first recess 71a, respectively of the second recess 71b, of the rotating part 51 of the oil distribution system 50 situated opposite, thereby making it possible to fluidly connect the oil receiving chambers 37a, 37b of this fuse 34 to their oil distribution chamber respectively 54a, 54b. Thus, the reducing assembly 3 is provided with two separate oil circulations 20a and 20b. In the first oil circulation 20a, the oil is fed by the first pump 44a and enters through the orifices 47a and 62a in the first annular cavity 61a of the fixed part 60 of the oil distribution system 50 in which it is located. spreads 360 °; the oil then passes through the passages 58a, 59a to fill in turn the first oil transfer chamber 54a; the oil can then be distributed via the first connecting pipes 70a to the first oil receiving chambers 37a of the rockets 34 from which it will be conveyed to the outer portion 36e of the bearings 36 via the first orifices injection 38a. Similarly, in the second oil circulation 20b, the oil is fed by the second pump 44b and enters through the orifices 47b and 62b into the second annular cavity 61b of the fixed portion 60 of the oil distribution system 50 in which it spreads 360 degrees; the oil then passes through the passages 58b, 59b to fill in turn the second oil transfer chamber 54b; the oil can then be distributed via the second connecting ducts 70b to the second oil receiving chambers 37b of the rockets 34 from which it will be conveyed to the inner portion of the bearings 36 via the second orifices of FIG. injection 38b. The reduction assembly 3 further comprises a computer 80 which controls the first and second pumps 44a and 44b to adjust the oil pressure in the first and second oil passages 20a, 20b. The reduction assembly 3 further comprises a device 81 for measuring the speed of rotation of the planet carrier 35: this measuring device comprises an inductive sensor and a voice wheel mounted on the fan shaft 2a, coupled to the carrier. satellite 35. Each passage of one of the teeth of the voice wheel in front of the inductive sensor induces an electromotive force in the inductive sensor which, by analyzing the output signal of the sensor, makes it possible to measure the speed of rotation of the shaft 2a and Thus, the planet carrier 35. In order to compensate for the centrifugal pressure gradient Gc normally present in the oil film of the bearing 36 when the planet carrier 35 is rotating, the computer 80 adjusts the pressures of the first and second oil passages 20a. and 20b so as to introduce a differential injection pressure between the first injection ports 38a and the second injection ports 38b, that is to say between the outer portion 36e and the porti 36i of the bearing 36. The calculator 80 sets this injection pressure differential as a function of the speed of rotation measured by the measuring device by applying a suitable control law based on a calibration table or a mathematical model. . The control also relies on a feedback loop based on the pressure measurements in the first and second flows 20a, 20b performed by pressure sensors 82a, 82b and / or flow. Thus, the injection pressure differential will be zero or almost zero when the reducer is stopped and will be all the more important that the carrier rotates faster. Thanks to such a transmission assembly and to such a control law, it is possible to substantially compensate the centrifugal pressure gradient Gc, which makes it possible to obtain a distribution of the pressure field close to the ideal case represented in FIG. wherein the distribution of the pressure field C 'is symmetrical with respect to the orthoradial plane, that is to say with respect to the driving direction.
    [0014] The modes or examples of embodiment described in the present description are given for illustrative and not limiting, a person skilled in the art can easily, in view of this presentation, modify these modes or embodiments, or consider others, while remaining within the scope of the invention. In addition, the various features of these modes or embodiments can be used alone or be combined with each other. When combined, these features may be as described above or differently, the invention not being limited to the specific combinations described herein. In particular, unless otherwise specified, a characteristic described in connection with a mode or example of embodiment may be applied in a similar manner to another embodiment or embodiment.
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. Transmission assembly comprising a transmission member (30) and an oil distribution system (50) housed in a housing (40) provided with at least one oil supply (43a), wherein the transmission member (40) 30) comprises at least one rotatable pivot (34), rotatable about an axis of rotation (R), and a pivotable portion (33), pivotable about the revolving pivot (34), wherein the rotation system (34) oil distribution (50) is configured to receive oil under pressure from the oil supply (43a) and to transfer it to at least one oil receiving chamber (37a) of the revolving pivot (34), wherein said rotational pivot (34) comprises injection ports (38a, 38b) fluidly communicating the oil receiving chamber (37a) with the gap (36) separating the rotating pivot (34) and the portion pivoting (33) so as to form a fluid bearing, wherein the transmission assembly (3) is adapted to inject oil into said gap (36) at a first injection pressure at an outer portion (36e) of the gap (36) facing away from the axis of rotation (R), and at a second pressure of injection at an inner portion (36i) of the gap (36) directed towards the axis of rotation (R), the second injection pressure being different from the first injection pressure.
    [0002]
    2. The assembly of claim 1, wherein the second injection pressure is greater than the first injection pressure.
    [0003]
    3. The assembly of claim 1 or 2, comprising a first oil flow (20a) opening through at least a first injection port (38a) at the outer portion of the gap (36e), and a second oil circulation (20b), distinct from the first oil circulation (20a), opening through at least one second injection orifice (38b) at the inner portion of the gap (36i).
    [0004]
    An assembly according to claim 3, further comprising a computer (80) configured to adjust the pressure of the first and / or second fluid circulation (20a, 20b) as a function of rotational speed of the revolving pivot (34). ) around the axis of rotation (R).
    [0005]
    5. The assembly of claim 4, wherein the computer (80) is configured to follow a control law according to which the pressure difference between the first and second injection pressures compensates for at least 70% of the pressure difference between the first and second injection pressures. oil between the inner and outer portions of the gap (361, 36e) caused by the centrifugal force forces during rotation of the revolving pivot (34).
    [0006]
    6. An assembly according to any one of claims 3 to 5, comprising a first oil supply (43a), pressurized by a first pump (44a) and feeding the first oil circulation (20a), and a second supply in oil (43b), pressurized by a second pump (44b) and feeding the second oil circulation (20b).
    [0007]
    The assembly, wherein the oil distribution system (50) comprises a rotating portion (51) having a first oil transfer chamber (54a) provided with at least a first configured supply port (59a). for receiving oil from the first oil supply (43a), and a second oil transfer chamber (54b) provided with at least a second supply port (59b) confined to receive oil from the second oil supply (43b), wherein the rotating pivot (34) comprises a first oil receiving chamber (37a), in fluid communication with the outer portion of the gap (36e) by said at least a first an injection port (38a), and a second oil receiving chamber (37b), in fluid communication with the interior portion (36i) of the gap by said at least one second injection port (38b), comprising further a first connecting conduit (70a) porting fluidic the first oil transfer chamber (54a) and the first oil receiving chamber (37a), and a second connecting conduit (70b) fluidly communicating with the second oil transfer chamber (54b) and the second oil receiving chamber (37b).
    [0008]
    8. An assembly according to any one of claims 3 to 7, wherein the rotary pivot comprises a plurality of first injection orifices arranged symmetrically on either side of the plane passing through the axis (P) of the rotary pivot ( 34) and by the axis of rotation (R) of the rotary pivot (34).
    [0009]
    An assembly according to any one of claims 1 to 8, wherein the rotary pivot (34) comprises injection ports (38a, 38b) having different passage sections.
    [0010]
    10. An assembly according to any one of claims 1 to 9, wherein the transmission member is an epicyclic gear type speed reducer (30) having a carrier (35), and wherein said carrier (35) has a plurality of rotatable pivot pins (34), each carrying a pivotable satellite gear (33). 20
    [0011]
    11. Turbomachine comprising a transmission assembly (30) according to any one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    RU2016141477A|2018-04-24|
    CN106461058A|2017-02-22|
    RU2681824C2|2019-03-12|
    US20180216489A1|2018-08-02|
    WO2015145029A1|2015-10-01|
    CN106461058B|2019-04-30|
    CA2943732A1|2015-10-01|
    RU2016141477A3|2018-10-04|
    EP3123059B1|2017-12-20|
    CA2943732C|2022-01-18|
    EP3123059A1|2017-02-01|
    US10215055B2|2019-02-26|
    FR3018861B1|2016-04-08|
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    法律状态:
    2015-03-13| PLFP| Fee payment|Year of fee payment: 2 |
    2016-02-24| PLFP| Fee payment|Year of fee payment: 3 |
    2017-03-08| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-02-20| PLFP| Fee payment|Year of fee payment: 5 |
    2020-02-20| PLFP| Fee payment|Year of fee payment: 7 |
    2021-02-19| PLFP| Fee payment|Year of fee payment: 8 |
    2022-02-18| PLFP| Fee payment|Year of fee payment: 9 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1452462A|FR3018861B1|2014-03-24|2014-03-24|TRANSMISSION ASSEMBLY COMPRISING A TRANSMISSION MEMBER AND AN OIL DISTRIBUTION SYSTEM|FR1452462A| FR3018861B1|2014-03-24|2014-03-24|TRANSMISSION ASSEMBLY COMPRISING A TRANSMISSION MEMBER AND AN OIL DISTRIBUTION SYSTEM|
    US15/128,708| US10215055B2|2014-03-24|2015-03-19|Transmission assembly comprising a transmission member and an oil distribution system|
    CN201580022644.3A| CN106461058B|2014-03-24|2015-03-19|Transmission assembly including variator components and oil distribution system|
    RU2016141477A| RU2681824C2|2014-03-24|2015-03-19|Transmission assembly including transmission member and oil distribution system|
    EP15714878.4A| EP3123059B1|2014-03-24|2015-03-19|Transmission assembly including a transmission member and an oil distribution system|
    PCT/FR2015/050669| WO2015145029A1|2014-03-24|2015-03-19|Transmission assembly including a transmission member and an oil distribution system|
    CA2943732A| CA2943732C|2014-03-24|2015-03-19|Transmission assembly including a transmission member and an oil distribution system|
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