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    • 专利摘要:
    Reducer (10) or differential type device for an aircraft turbomachine (1), comprising a central sun (11) and an annular row of satellites (12), each of said satellites being guided in rotation by at least one bearing (17 ) extending around a tubular support (16) of axis Y of said planet carrier, this tubular support comprising an internal cavity (16a) for receiving oil and substantially radial orifices (44) passing through oil from an internal annular surface (16c) of said tubular support up to at least one bearing, characterized in that an organ (60) for conveying oil is mounted in said cavity and comprises at least one oil line (68, 70) which is intended to be connected to oil supply means (78) and which is connected to a ring (66) which extends around the Y axis and which delimits with said internal annular surface (16c) an annular space (84) for circulation of oil, the oil being intended ined to flow from said at least one pipe, into said space to form an oil film in contact with said tubular support, then to pass through said orifices.
    公开号:FR3084429A1
    申请号:FR1856981
    申请日:2018-07-26
    公开日:2020-01-31
    发明作者:Louis Simon Adrien；Michel Pierre Di Giovanni Jean-Charles；Pierre Marcel Morelli Boris；Florian Rappaport
    申请人:Safran Transmission Systems SAS；
    IPC主号:
    专利说明:

    REDUCING OR DIFFERENTIAL TYPE DEVICE FOR A
    AIRCRAFT TURBOMACHINE
    Field of the invention
    The present invention relates to the field of speed reducers or mechanical differentials for a turbomachine in particular of an aircraft.
    State of the art
    The state of the art includes in particular the documents WO-A1-2010 / 092263, FR-A1 -2 987 416 and FR-A1 -3 041 054.
    Current turbomachinery, in particular turbomachinery comprising one or more propellers blowing a secondary flow, comprises a transmission system, called a reduction gear, to drive this or these propellers at the right speed of rotation from the shaft of the power turbine of the primary body of the engine.
    The operation of the reducers, in particular on turbomachines with a fan propeller with a high dilution rate, requires a particularly high oil flow rate, of the order of 6000 to 7000 liters per hour on takeoff, to ensure lubrication and cooling. of their gables and bearings.
    Among the reducers used, there are planetary and (planetary) planetary reducers which have the advantage of offering significant rates of reduction of the speed of rotation in reduced dimensions.
    Such a reducer comprises a planetary or central pinion, called a sun gear, an outer ring and planet gears, called satellites, which are engaged with the sun and with the ring, the support of one of these three components having to be blocked. in rotation for the operation of the gear train as a reducer.
    When the planet carrier is fixed in rotation, the sun and the crown are driving and driven, respectively, or vice versa. The reducer is then of the “planetary” type.
    In the opposite case, the most common of a planetary gearbox, the outer ring is fixed in rotation and the sun and the planet carrier are leading and driven.
    This same structure can be used to make a mechanical differential. In this case, the three components (solar, satellites and crown) are mobile in rotation.
    However, this type of reduction gear or differential has drawbacks linked to its lubrication.
    In the current technique, a satellite is generally guided in rotation by a smooth bearing which extends around a tubular support for the planet carrier, this tubular support comprising an internal oil-receiving cavity and substantially radial through holes. passage of oil from the internal cavity to the plain bearing. Another guidance solution would be the use of rolling element bearings.
    The heat generated by the passage of the moving parts of a bearing must be transferred as efficiently as possible to a heat transfer fluid (here oil). In order to optimize performance (yields), it is preferable to have two different oil temperatures: one for the bearings and the other for the teeth. To date, the only way to get two different oil temperatures is to duplicate the oil circuits.
    The present invention provides an improvement to this technology with a simple, effective and economical solution to this problem.
    Statement of the invention
    The invention relates to a device of the reduction or differential type for an aircraft turbomachine, comprising a central sun of axis X of rotation, a ring extending around the axis X and of the sun, and a satellite support carrier d '' an annular row of satellites arranged between the solar and the crown, and meshed with the solar and the crown, the satellites having axes of rotation Y substantially parallel to said axis X, said solar comprising means for coupling to a shaft of the turbomachine and at least one of the planet carrier and the crown comprising means for connecting to another shaft of the turbomachine, each of said satellites being guided in rotation by at least one bearing extending around a tubular support d axis Y of said planet carrier, this tubular support comprising an internal oil receiving cavity and substantially radial orifices through which oil passes from a surface e internal annular of said tubular support up to at least one bearing, characterized in that an oil conveying member is mounted in said cavity and comprises at least one oil line which is intended to be connected to means supply oil and which is connected to a ring which extends around the axis Y and which defines with said internal annular surface an annular space for circulation of oil, the oil being intended to flow from said at least one pipe, in said space to form an oil film in contact with said tubular support, then through said orifices.
    The device can thus be a planetary or planetary type reducer or a mechanical differential. The invention proposes to heat the oil before lubrication of the bearing. For this, it is proposed to circulate the "cold" oil in contact with the tubular support and inside it. The oil is thus intended to form a film of oil which heats up in contact with the tubular support and therefore arrives "hot" at the bearing, at a predetermined temperature for optimal performance while having removed the heat from the bearing. The invention thus proposes to use only one oil circuit instead of the two currently recommended using the losses at the bearing to heat the oil before it reaches the bearing.
    The device according to the invention may include one or more of the following characteristics, taken in isolation from one another, or in combination with one another:
    - Said member comprises a first axial pipe extending along the Y axis and at least a second radial pipe extending between the first pipe and said ring; the organ is therefore of simple design,
    - Said first pipe is formed in a cylindrical portion of the member and said at least one second pipe is formed in a connecting disc of said cylindrical portion at the inner periphery of the ring, and preferably substantially in the middle of this ring; the pipes can be made by machining or any other suitable technique,
    - Said cylindrical portion is connected by an axial end to said disc and by an axial end opposite to another disc, the external periphery of which bears radially on an internal cylindrical surface of said tubular support; this makes it possible to guarantee precise positioning of the member in the support, and to limit the risks of relative displacement of these parts in operation,
    - Said opposite axial end comprises a port for connection to said supply means; the port can cooperate by male-female fitting with the oil supply means,
    - Said ring is cylindrical and said space has a substantially constant thickness over its entire length; it is thus understood that the oil film has a substantially constant thickness, this thickness being for example determined as a function of the viscosity of the oil so as to absorb a certain amount of heat from the bearing in operation,
    - Said ring has in axial section a biconical shape and comprises two frustoconical parts connected together and to said at least one pipe by their ends of smaller diameter, the biconical shape of the ring makes it possible to facilitate the flow and the guiding of the oil in operation,
    said frustoconical parts have a predetermined angle cc 0 with respect to said internal annular surface, and the ring is configured so that said oil film has a predetermined thickness eo,
    - at least one seal is mounted between each axial end of the ring and the internal annular surface of said tubular support; the seal is for example O-ring and provides an oil seal between the ring and the support,
    - Said member is formed in one piece; this facilitates the assembly of the organ,
    - Said bearings are of the roller type, and preferably comprise at least two annular rows of bearings arranged one next to the other; alternatively, there could be three or more landings arranged next to each other,
    - The support comprises radially external annular ribs which define therebetween in particular external annular grooves for receiving the rows of bearings, at least some of said orifices extending into the ribs and / or opening at the bottom of said grooves; it is thus understood that the inner rings of the bearings are formed in one piece with the annular support, which is advantageous and simplifies assembly.
    The present invention further relates to an aircraft turbomachine, characterized in that it comprises at least one device as described above.
    Brief description of the figures
    Other characteristics and advantages will emerge from the following description of a non-limiting embodiment of the invention with reference to the accompanying drawings in which:
    FIG. 1 is a schematic view in axial section of a turbomachine using the invention,
    - Figure 2 is an axial sectional view of a speed reducer,
    FIG. 3 is a cutaway perspective view of the reduction gear,
    FIG. 4 is a sectional view of a device of the reduction or differential type, the guide bearings of the satellites of which are with bearings,
    - Figure 5 is a sectional perspective view of part of the device of Figure 4;
    FIG. 6 is a sectional view of a device of the reducing or differential type, equipped with an oil conveying member according to an embodiment of the invention, and
    - Figure 7 is a sectional view of a reduction or differential type device, equipped with an oil delivery member according to an alternative embodiment of the invention.
    Detailed description of an embodiment of the invention
    FIG. 1 shows a turbomachine 1 which conventionally comprises a fan propeller S, a low pressure compressor 1a, a high pressure compressor 1b, an annular combustion chamber 1c, a high pressure turbine 1d, a low pressure turbine 1e and an exhaust nozzle 1h. The high pressure compressor 1b and the high pressure turbine 1d are connected by a high pressure shaft 2 and form with it a high pressure body (HP). The low pressure compressor 1a and the low pressure turbine 1e are connected by a low pressure shaft 3 and form with it a low pressure body (BP).
    The blower propeller S is driven by a blower shaft 4 which is coupled to the LP shaft 3 by means of a planetary or differential reduction gear 10 with planetary gear, shown here diagrammatically.
    The reduction gear 10 is positioned in the front part of the turbomachine. A fixed structure schematically comprising, here, an upstream part 5a and a downstream part 5b is arranged so as to form an enclosure E1 surrounding the reducer 10. This enclosure E1 is here closed upstream by seals at a level allowing the crossing of the fan shaft 4, and downstream by seals at the crossing of the LP shaft 3.
    With reference to FIG. 2, the reduction gear 10 comprises a ring 14 which is fixed by means of a ring holder (not shown) to the fixed structure 5a, 5b with flexible means arranged to enable it to follow the movements fans of the fan shaft 4, in certain cases of degraded operation for example. In a planetary architecture, the crown carrier is composed of a more or less flexible part which drives the crown and of a part held by bearings or bearings and on which the fan is mounted. These fixing means are known to those skilled in the art and are not detailed here. A brief description can be found for example in FR-A1 -2987416.
    The reduction gear 10 is connected to the BP shaft 3 via splines 7 which drive a planetary or solar gear pinion 11, and on the other hand to the fan shaft 4 which is attached to a satellite carrier 13. Conventionally, the sun 11, whose axis of rotation X coincides with that of the turbomachine, drives a series of pinions of satellites or satellites 12, which are distributed regularly over the circumference of the reduction gear 10. The number of satellites 12 is generally defined between three and seven. The satellites 12 also rotate around the axis X of the turbomachine except in the case of a planet wheel where they rotate only around their axes of revolution Y, meshing on an internal toothing chevron of the crown 14, which is fixed to a stator of the turbomachine by means of flanges 20 in the case of an epicycloidal or fixed to a rotor of the turbomachine in the case of a sun gear. Each of the satellites 12 rotates freely around an axis Y defined by a tubular support 16 carried by the planet carrier 13, using a bearing 17 which is generally smooth in the current technique.
    The rotation of the satellites 12 around the axis Y, due to the cooperation of their teeth with the teeth of the crown 14, causes the rotation of the planet carrier 13 around the axis X, and consequently that of the fan shaft 4 which is linked to it, at a speed of rotation which is lower than that of the LP shaft 3.
    Figure 2 shows, with Figure 3, the routing of oil to the reducer 10 and its path inside thereof. Arrows show in FIG. 2 the path followed by the oil from, in this example, a buffer tank 31 linked to the fixed structure of the turbomachine, up to the pinions and the bearings 17 to be lubricated.
    The lubrication device schematically comprises three parts which will be described below successively, a first part linked to the fixed structure and delivering the oil to the rotating parts of the reduction gear 10, a spinning wheel rotating with the planet carrier 13 receiving this oil , and oil distribution circuits supplied with oil by the impeller to convey it to the places to be lubricated. The first part comprises at least one injector 32, the calibrated end of which is tightened to form a nozzle 33. The oil is brought to the injector by a conveying pipe 30, coming from the engine tank (not shown). A buffer tank 31 can be interposed next to the reducer 10 on the pipe, preferably in the upper part so that the oil can flow towards the center of the reducer by gravity. The nozzle 33 ejects the oil in the form of a jet 34, which is formed under the pressure produced jointly by the feed pump (not shown) and by the weight of the oil column located above it . The nozzle 33 is positioned here radially inside the planet carrier 13 with respect to the axis X and the jet 34 is oriented with a radial component directed towards the outside of the reduction gear 10. With reference to FIG. 3, the oil receiving impeller linked to the planet carrier 13 essentially comprises a cylindrical cup, here in U-shaped section, whose U-shaped opening is oriented in the direction of the axis of rotation X. The impeller is arranged on the door -satellites 13 so that the bottom of the U of the cup 35 collects the jet of oil 34 ejected by the nozzle 33.
    There are two types of oil distribution circuits here. A first series of oil distribution circuits corresponds to first pipes 43, which are distributed regularly over the circumference of the reduction gear 10 and in a number equal to that of the satellites 12. These pipes 43 start radially from the cup 35 and enter the internal cavity 16a of each support 16 (FIG. 3), which is closed by the planet carrier
    13. The oil which circulates in the first pipes 43 penetrates into the internal cavity 16a then passes, due to the centrifugal force, into orifices 44 which pass through each support 16 while being oriented radially. These orifices 44 open at the periphery of the supports 16, at the level of the bearings supporting the pinions of the satellites 12 and thus ensure the lubrication of these bearings. The second series of oil distribution circuits includes second pipes 45 which pass from the cup 35 between the satellites 12 and are divided into several channels 45a, 45b. The channels 45a, 45b convey the oil to the gears formed by the pinions of the satellites 12 and the sun 11, on the one hand, and the pinions of the satellites 12 and the outer ring 14, on the other hand. Each channel 45a extends axially along the pinions of a satellite 12, between these and the sun 11, and forms a lubrication ramp over the entire width of the pinions. The channel 45b, which feeds the gear between the crown 14 and the pinions of the satellites 12, projects its oil into the center of the cylinder formed by each satellite 12. As shown, each satellite 12 is produced in the form of two parallel pinions which mesh respectively with two half-crowns of the crown 14 (Figure 3). The propellers of the teeth of each satellite are oriented diagonally to the axis Y of rotation of the satellite 12, so as to give them a function of grooves in which the oil is entrained, from the middle of the cylinder to its periphery, to lubricate the gear over its entire width.
    Although the foregoing description relates to a planetary or planetary type reducer, it applies to a mechanical differential in which the three components, which are the planet carrier 13, the crown 14 and the sun 11, are movable in rotation, the speed of rotation of one of these components depending on the speed difference of the two other components in particular.
    FIG. 4 shows the case where the satellites 12 of a device of the reducing or differential type are centered and guided in rotation on the tubular supports 16 of the planet carrier 13, by a bearing with one or more rows of rolling elements 17a, 17b. The rows of rolling elements 17a, 17b are called "bearings" in the following.
    In the examples of Figures 4 and 5, each support 16 is surrounded by the two bearings 17a, 17b which are roller in the example shown. In our example, each bearing 17a, 17b is associated with a propeller 12a, 12b of the chevron toothing of the satellite 12 which is itself meshed with two half-rings 14a, 14b, as mentioned in the foregoing. In other words, the bearings 17a, 17b are coaxial and arranged one next to the other, each bearing being situated in a median plane P1, P2 passing substantially through the median plane of each propeller 12a, 12b of the satellite pinion 12 and by the median plane of the propeller of a half-crown 14a or 14b. The planes P1 and P2 are mutually parallel and perpendicular to the Y axis. The number of bearings 17a, 17b may be different from the example presented. It does not necessarily depend on the number of propellers 12a, 12b, 14a, 14b of a chevron toothing.
    Each bearing 17a, 17b comprises an annular row of bearings 50 (rollers) arranged in a cage 52 which is formed by a cylindrical ring comprising an annular row of through holes 52a for receiving the bearings. The cages 52 are independent and axially spaced from one another. In the case illustrated in the drawings, the rings or internal and external tracks of each bearing are formed in one piece with the support 16, on the one hand, and the satellite 12, on the other hand.
    As can be seen in FIG. 4, the bearings 17a, 17b are at an axial distance from each other. This is also the case for the propellers 12a, 12b of the satellite pinion 12 and the propellers of the half-rings 14a, 14b. The propellers 12a, 12b are connected by a cylindrical web of material which includes an annular row of radial holes 19 necessary for the flow of the oil in operation so as not to have a hole in the chevron teeth.
    Each half-crown 14a, 14b comprises an annular body of generally cylindrical shape and connected to an annular flange 14ab, 14bb extending radially outwards. Each body includes an internal propeller. Although this is not visible in the drawings, the propellers of the half-crowns, are complementary to the propellers 12a, 12b of the satellite, which are they of the type shown in FIG. 3. The propellers of the two half-crowns 14a, 14b are thus in a chevron.
    The body of each half-crown is connected by one of its longitudinal ends to the corresponding flange 14ab, 14bb by means of an annular flange 14ab1, 14bb1.
    Each flange 14ab, 14bb extends substantially in the radial direction and is supported on the other flange in a substantially radial joint plane. The flanges 14ab1, 14bb1 have here a generally frustoconical shape and here converge towards each other radially outwards.
    The flanges 14ab, 14bb are used to fix the half-crowns 14a, 14b therebetween, as well as to a crown carrier 15 and to an oil recovery unit 22 in the example shown.
    For this, the flanges 14ab, 14bb each comprise an annular row of through axial holes for passage of fastening means 21 of the screw-nut type or the like. The orifices of the flanges are aligned and receive the fixing means 21.
    The crown holder 15 also comprises an annular flange 15a for fixing to the flanges 14ab, 14bb. The flange 15a is applied axially to one of the flanges 14ab, 14bb, namely here the flange 14ab in the example shown. The flange 14ab is thus interposed axially between the flange 15a and the flange 14bb. The reverse is also possible.
    The flange 15a comprises orifices aligned with the orifices of the flanges 14ab, 14bb and which also receive the fixing means 21, heads of which can be applied axially on the upstream face of the flange 15a and nuts can be applied axially on the face downstream of the flange 14bb or vice versa. In the example shown, a flange 22a of the annular oil recuperator 22 is in axial support on the flange 14bb and receives on its downstream face the heads of the nuts. The flange 22a comprises orifices aligned with the orifices of the flanges 14ab, 14bb, 15a and which also receive the fixing means 21.
    The flanges 14ab1, 14bb1 delimit an annular space E which here has a generally triangular section, the point of which is oriented radially outwards.
    Due to the shape of the flanges 14ab1, 14bb1 and their connection to the longitudinal ends, respectively downstream and upstream, of the bodies of the half-rings, these bodies are separated axially from each other by a predetermined distance.
    The axial distance between helices 12a, 12b may be due to a manufacturing constraint. Each satellite has an internal rolling track. To reduce the precise surface to be machined to the exact need, this internal cylindrical surface is divided into several tracks of reduced axial width, the number of which is equal to the number of bearings 17a, 17b. This makes it possible to obtain an annular groove 12c for recovering oil between the tracks, to reduce the mass because the satellite undergoes fewer stresses at this location and to reduce the difficulty of production on elements requiring very high precision because several tracks are produced independently of each other and the total surface of great precision is smaller with the grooves between each track. The holes 19 are formed at the bottom of this groove 12c.
    The lubricating oil is intended to flow in operation through the inter-body space E. Substantially radial passages are provided between the flanges 14ab, 14bb in order to allow the evacuation of the oil radially towards the outside of the crown 14.
    The oil passages are here formed on the one hand by substantially radial lunules 25 formed in the facing surfaces of the flanges 14ab, 14bb. Each flange 14ab, 14bb comprises an annular row of lunules 25 axially aligned with lunules 25 on the other of the flanges. The lunules are produced at a distance from the orifices for passage of the fixing means 21. Each lunula has, for example in section, a semicircular (semi-oblong) or rectangular shape.
    The lunules 25 are in fluid communication, at their radially internal ends, with the space E, and at their axially external ends with oil outlet notches 27 provided on cylindrical flanges situated at the external periphery of the flanges 15a, 22a (figure 4).
    Oil passages are further formed by substantially radial lunules 28 formed in the bearing surfaces of the flanges 22a, 15a (Figure 4). Each flange 22a, 15a comprises an annular row of lunules 28. The lunules 28 are produced at a distance from the orifices for passage of the fixing means 21 and communicate with through orifices 29 provided at the bottom of the lunules 25 for the flanges 14ab, 14bb. Each lunula has for example in section a semi-circular (semi-oblong) or rectangular shape.
    The oil which passes through the orifices 44 of the support 16 (arrows f1) lubricates the bearings 17a, 17b and must then flow radially outside of them. The lubrication will be used to cool the rolling elements as well as the cage 52. Once the elements have cooled, the lubrication is found on one of the three possible paths:
    - Path N ° 1 - arrows f2
    The lubricating oil is ejected from the front side of the reduction gear (or from the left end of the bearing in the drawing), and rises in the crown carrier 15 to the rings 28; it is then transferred via the orifices 29 between the flanges 14ab, 14bb of the half-crowns to find themselves ejected by the notches 27;
    - Path N ° 2 - arrows f3 and f4
    The lubricating oil is trapped between the bearings 17a, 17b; using centrifugal effects, gravity and ventilation, the lubricating oil is found in the circular groove 12c located between the two inner taxiing tracks (arrows f3) then leaves the satellite 12 via the holes 19 for arrive in space E formed by the two assembled half-crowns (arrows f4); at the end of this cavity are the lunules 25 and the notches 27 for the ejection of the oil from the reducer by the centrifugal effect of the rotating crown;
    - Path N ° 3 - arrows f5
    The lubricating oil is ejected from the rear side of the reduction gear (or from the right end of the bearing in the drawing), and rises in the oil catch tank 22 to the rings 28; it is then transferred via the orifices 29 of the flange of the rear half-crown to find itself ejected by the central channel formed by the notches 27 of the two assembled half-crowns.
    In the case shown in FIG. 4, the flow of oil from the orifices 44 to the space E is not optimized. Road oil No. 2 may stagnate and reduce the lubrication and cooling efficiency of the bearings 17a, 17b. The cages 52 of the bearings 17a, 17b include facing peripheral edges which are identical and at an axial distance from each other, and which are not suitable for guiding the oil in operation.
    Figures 6 and 7 illustrate two embodiments of the invention. This invention applies to a reducer or differential as described in the above.
    In these embodiments, the device is equipped with a body 60 for conveying oil which is mounted in the cavity 16a of each tubular support 16.
    The member 60 essentially comprises three parts, namely a cylindrical portion 62, a disc 64 and a ring 66. The member 60 is here formed in one piece although this characteristic is not limiting.
    The portion 62 extends along the Y axis and has an external diameter D1. It comprises an internal pipe 68, called the first pipe, which extends along the axis Y over almost the entire length of the portion 62 in the example shown.
    The portion 62 has an axial end 62a connected to the center of the disc 64 whose external periphery is connected to the ring 66. The disc 64 extends in a plane substantially perpendicular to the axis Y and comprises an internal pipe 70, called the second pipe, which extends radially and the radially internal end of which is connected to the axial end of the pipe 68 located at the end 62a, and the radially external end of which opens onto an external annular surface 64a of the disc .
    The disc 64 is connected substantially in the middle of the ring 66 (along the Y axis) so that the pipe 70 opens substantially in the middle of the ring 66. The disc 64 could include several radial pipes 70 regularly spaced around the 'Y axis.
    The portion 62 has an opposite axial end 62b connected to the center of another disc 72, the external periphery of which bears radially on an internal cylindrical surface 74 of the support 16, which is here located at an axial end of the latter. The portion 62 extends axially beyond the disc 72 to form a port 76 for connection of the pipe 68 to supply means 78.
    The supply means 78 comprise for example an annular ramp 80 connected to a source of lubricating oil and comprising an annular row of fittings 82 fitted on the ports 76 of the members 60 mounted in the various supports 16. The ramp 80 s here extends around the X axis. O-ring seals can be provided between the ports 76 and the fittings 82 of the ramp 80.
    The ring 66 extends around the axis Y and delimits with an internal annular surface 16c of the support 16 an annular space 84 for oil circulation.
    As mentioned in the foregoing, these orifices 44 pass radially through the tubular wall of the support 16. In the example shown, the support 16 comprises radially external annular ribs 16b which define between them external annular grooves 86 for receiving the bearings 50. The ribs 16b thus serve as axial stops for the rolling elements of the bearings 17a, 17b. At least some of the holes 44 extend to the free radially outer ends of the ribs
    16b. Others extend as far as the grooves 86. The radially internal ends of the orifices 44 open onto the surface 16c.
    The length of the ring 66 is determined so that all the orifices 44 open into the space 84. In the example shown, it has a length which represents 50 to 80% of that of the support 16, measured along the Y axis.
    The ring 66 of Figure 6 has a generally cylindrical shape and extends at a predetermined radial distance from the surface 16c. This distance makes it possible to define a thickness e 0 of an oil film intended to be formed between the ring 66 and the support 16. The thickness e 0 is substantially constant over the length of the film.
    The ring has an internal diameter D2 significantly greater than D1 and an external diameter D3 which is substantially equal to the internal diameter of the surface 16c or slightly smaller than the latter.
    The ring 66 comprises an annular flange 88 radially external to each of its axial ends. Each rim 88 comprises an annular groove 90 opening radially outwards and in which is intended to be housed an annular seal intended to cooperate with the surface 16c.
    The arrows in FIG. 6 show the routing of the oil from the supply means to the bearings 17a, 17b. The oil leaves the ramp 80 and enters line 68 via port 76. It flows through lines 68, 70 and then enters space 84 to form the oil film. The oil flows along the surface 16c and heats up in contact with the support 16 due to the heat generated by the bearings 17a, 17b in operation. The oil thus heated then passes through the orifices 44 to join the bearings 17a, 17b for their lubrication.
    The member 60 ’of the embodiment of FIG. 7 differs from the member 60 described in the foregoing essentially in that its ring 66’ has a different shape.
    The ring 66 ’has a biconical shape in axial section and comprises two frustoconical parts 92, 94 connected together and to the disc 64 by their ends of smaller diameter. The ring has a plane of symmetry passing through the disc 64 and perpendicular to the axis Y.
    Each frustoconical part 92, 94 is inclined by a predetermined angle cc 0 with respect to the surface 16c, this angle being measured in an axial plane such as the cutting plane of FIG. 7.
    The member 60 ′ of the embodiment of FIG. 7 further differs from the member 60 in that the ring 66 ′ bears axially via one of its axial ends against an internal annular shoulder 96 of the support 16. Although the port 76 for connecting the member 60 'to the oil supply means is not shown, the member 60' does indeed include such a port.
    The arrows in FIG. 7 show the routing of the oil from the supply means to the bearings 17a, 17b. The oil flows through lines 68, 70 and then enters space 84 'to form the oil film of medium thickness eo. The oil flows along the surface 16c and heats up in contact with the support 16 due to the heat generated by the bearings 17a, 17b in operation. The oil thus heated then passes through the orifices 44 to join the bearings 17a, 17b for their lubrication.
    As an example, a first dimensioning under the lubrication conditions and with the current bearing loss estimates gives a potential increase in oil temperature between 10 ° C and 60 ° C by playing on the oil film by its average thickness eo and its angle a 0 . The yield calculations estimate that a lubrication temperature of the bearings 40 ° C higher than that of the teeth would be beneficial.
    The invention makes it possible in particular to use only a single oil circuit. Since the teeth require an oil that is less hot than the bearings, it is now possible to reheat it before it is injected under the bearings, while cooling the tubular support forming the inner ring of the bearing. This represents an economy of an oil circuit and therefore gains in mass and efficiency at the engine level. The invention also makes it possible to limit the mass of the device, the only structural part being the tubular support, and to homogenize the stresses in the tubular support by absence of tightening and shrinking.
    权利要求:
    Claims (10)
    [1" id="c-fr-0001]
    1. A device of the reducing (10) or differential type for an aircraft turbomachine (1), comprising a central sun (11) of axis X of rotation, a ring (14) extending around the axis X and solar, and a planet carrier (13) for supporting an annular row of satellites (12) disposed between the solar and the crown, and meshed with the solar and the crown, the satellites having axes of rotation Y which are substantially parallel to said X axis, said solar unit comprising means (7) for coupling to a shaft (3) of the turbomachine and at least one of the planet carrier and the crown comprising means for connection to another shaft (4) of the turbomachine, each of said satellites being guided in rotation by at least one bearing (17) extending around a tubular support (16) of Y axis of said planet carrier, this tubular support comprising an internal cavity (16a) for receiving oil and substantially radial through holes (44) s for the passage of oil from an internal annular surface (16c) of said tubular support to at least one bearing, characterized in that a member (60, 60 ') for conveying oil is mounted in said cavity and comprises at least one oil line (68, 70) which is intended to be connected to oil supply means (78) and which is connected to a ring (66, 66 ') which extends around the 'Y axis and which defines with said internal annular surface (16c) an annular space (84, 84') for circulation of oil, the oil being intended to flow from said at least one pipe, into said space to form an oil film in contact with said tubular support, then through said orifices.
    [2" id="c-fr-0002]
    2. Device according to the preceding claim, wherein said member (60, 60 ') comprises a first axial pipe (68) extending along the Y axis and at least a second radial pipe (70) extending between the first pipe and said ring (66, 66 ').
    [3" id="c-fr-0003]
    3. Device according to the preceding claim, wherein said first pipe (68) is formed in a cylindrical portion (62) of the member (60, 60 ') and said at least one second pipe (70) is formed in a disc. (64) connecting said cylindrical portion to the internal periphery of the ring (66, 66 '), and preferably substantially in the middle of this ring.
    [4" id="c-fr-0004]
    4. Device according to the preceding claim, wherein said cylindrical portion (62) is connected by an axial end to said disc (64) and by an axial end opposite to another disc (72) whose external periphery is in radial support on a internal cylindrical surface (74) of said tubular support (16).
    [5" id="c-fr-0005]
    5. Device according to the preceding claim, wherein said opposite axial end comprises a port (76) for connection to said supply means (78).
    [6" id="c-fr-0006]
    6. Device according to one of the preceding claims, wherein said ring (66) is cylindrical and said space (84) has a thickness (e 0 ) substantially constant over its entire length.
    [7" id="c-fr-0007]
    7. Device according to one of claims 1 to 5, wherein said ring (66 ') has in axial section a biconical shape and comprises two frustoconical parts (92, 94) connected together and to said at least one pipe (68, 70) by their ends of smaller diameter.
    [8" id="c-fr-0008]
    8. Device according to the preceding claim, wherein said frustoconical portions (92, 94) have a predetermined angle (oto) relative to said internal annular surface (16c), and the ring (66 ') is configured so that said film of oil has a predetermined thickness (e 0 ).
    [9" id="c-fr-0009]
    9. Device according to one of the preceding claims, in which at least one seal is mounted between each axial end of the ring (66, 66 ’) and the internal annular surface (16c) of said tubular support (16).
    [10" id="c-fr-0010]
    10. Aircraft turbomachine, characterized in that it comprises at least one device according to one of the preceding claims.
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    同族专利:
    公开号 | 公开日
    US20200032893A1|2020-01-30|
    FR3084429B1|2020-11-13|
    EP3599396A1|2020-01-29|
    EP3599396B1|2020-09-30|
    US10975952B2|2021-04-13|
    CN110778692A|2020-02-11|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DD243739A1|1985-10-11|1987-03-11|Fortschritt Veb K|OIL LUBRICATION ON PLANETARY WHEEL BOLTS|
    GB2234035A|1989-07-21|1991-01-23|Rolls Royce Plc|Lubricating a reduction gear assembly in a gas turbine engine|
    EP2333250A2|2009-11-30|2011-06-15|United Technologies Corporation|Journal bearing of an epicyclic gear assembly for a gas turbine engine|
    DE243739C|
    FR2942284B1|2009-02-16|2011-03-04|Snecma|LUBRICATION AND COOLING OF AN EPICYCLOIDAL GEAR TRAIN REDUCER|
    FR2987416B1|2012-02-23|2015-09-04|Snecma|DEVICE FOR LUBRICATING AN EPICYCLOIDAL REDUCER.|
    FR3009594B1|2013-08-08|2016-12-09|Snecma|EPICYCLOIDAL TRAIN REDUCER WITH FLUID TRANSFER PIPES, AND AIRCRAFT TURBOMACHINE FOR AN AIRCRAFT WITH SUCH REDUCER|
    FR3015599B1|2013-12-23|2016-07-22|Skf Aerospace France|MECHANICAL DEVICE COMPRISING A BEARING AND A LUBRICATION SYSTEM, MACHINE AND METHOD FOR IMPLEMENTING SAID METHOD|
    FR3035375B1|2015-04-23|2018-07-27|Safran Aircraft Engines|EPICYCLOIDAL GEAR TRAIN REDUCER FOR A TURBOMACHINE.|
    FR3041054B1|2015-09-15|2017-09-15|Hispano-Suiza|OIL SUPPLY DEVICE FOR AN EPICYCLOIDAL TRAIN REDUCER.|
    FR3047284B1|2016-02-01|2018-06-15|Safran Transmission Systems|SATELLITE BEARING FOR A SATELLITE CARRIER HAVING LUBRICATION MEANS|US11098654B2|2019-03-15|2021-08-24|Hamilton Sundstrand Corporation|Hydraulic unit gear shrouds|
    DE102019214105A1|2019-09-17|2021-03-18|Zf Friedrichshafen Ag|Lubricant feed in a vertically installed gear|
    DE102020122218A1|2020-08-25|2022-03-03|Rolls-Royce Deutschland Ltd & Co Kg|Method and control unit for determining bearing temperatures of plain bearings of planetary gears during operation of a planetary gear|
    法律状态:
    2019-06-20| PLFP| Fee payment|Year of fee payment: 2 |
    2020-01-31| PLSC| Search report ready|Effective date: 20200131 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 3 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 4 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1856981|2018-07-26|
    FR1856981A|FR3084429B1|2018-07-26|2018-07-26|REDUCER OR DIFFERENTIAL TYPE DEVICE FOR AN AIRCRAFT TURBOMACHINE|FR1856981A| FR3084429B1|2018-07-26|2018-07-26|REDUCER OR DIFFERENTIAL TYPE DEVICE FOR AN AIRCRAFT TURBOMACHINE|
    EP19184895.1A| EP3599396B1|2018-07-26|2019-07-08|Reducer or differential type device for a turbine engine of an aircraft|
    CN201910677296.3A| CN110778692A|2018-07-26|2019-07-25|Deceleration or differential device for a turbine engine of an aircraft|
    US16/522,352| US10975952B2|2018-07-26|2019-07-25|Reduction- or differential-type device for a turbine engine of an aircraft|
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