• 专利附录
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    • 专利摘要:
    The invention relates to a system (26) for changing blade pitch of at least one turbomachine propeller, comprising: - a control means acting on a connecting mechanism (31) connected to the blades of the propeller and comprising a movable body (29) in translation along a longitudinal axis relative to a fixed body (28), - at least one load transfer bearing (34) mounted on the movable body and cooperating with the connecting mechanism, and - means lubrication device (60) of said bearing (34) comprising at least one lubricant circulation duct (61) extending radially above the fixed and movable bodies, the duct comprising at least first and second telescopic and sliding tubular parts relative to each other coaxially, the first portion being connected to said fixed body and the second portion being connected to the movable body, lubricant spraying means in the bearing mounted on said movable body and at least one lubricant delivery conduit (75) mounted on the movable body for connecting the pipeline to said spraying means.
    公开号:FR3055309A1
    申请号:FR1657974
    申请日:2016-08-26
    公开日:2018-03-02
    发明作者:Eugene Henri Servant Regis；Anthony Lafitte；Keomorakott Souryavongsa Eddy；Emile Philippe Tajan Sebastien；Arnaud Martin
    申请人:Safran Aircraft Engines SAS；
    IPC主号:
    专利说明:

    ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY © Publication number: 3,055,309 (to be used only for reproduction orders) (© National registration number: 16 57974
    COURBEVOIE © IntCI 8
    B 64 C 11/30 (2017.01), F 02 C 7/06
    A1 PATENT APPLICATION
    (§) Date of filing: 08.26.16. © Applicant (s): SAFRAN AIRCRAFT ENGINES - (30) Priority: FR. @ Inventor (s): SERVANT REGIS, EUGENE, HENRI, LAFITTE ANTHONY, SOURYAVONGSA EDDY, (43) Date of public availability of the KEOMORAKOTT, TAJAN SEBASTIEN, EMILE, PHI- request: 02.03.18 Bulletin 18/09. LIPPE and MARTIN ARNAUD. (© List of documents cited in the report of preliminary research: Refer to end of present booklet (© References to other national documents @ Holder (s): SAFRAN AIRCRAFT ENGINES. related: ©) Extension request (s): (© Agent (s): GEVERS & ORES Société anonyme.
    STEP CHANGE SYSTEM PROVIDED WITH MEANS FOR LUBRICATING A LOAD TRANSFER BEARING.
    FR 3 055 309 - A1 (67) The invention relates to a system (26) for changing the pitch of blades of at least one turbomachine propeller, comprising:
    a control means acting on a connection mechanism (31) connected to the propeller blades and comprising a movable body (29) in translation along a longitudinal axis with respect to a fixed body (28),
    - at least one load transfer bearing (34) mounted on the movable body and cooperating with the link mechanism, and
    - lubrication means (60) of said bearing (34) comprising at least one pipe (61) for circulating lubricant and extending radially above the fixed and movable body, the pipe comprising at least first and second tubular parts telescopic and sliding relative to one another coaxially, the first part being connected to said fixed body and the second part being connected to the mobile body, means for spraying lubricant in the bearing mounted on said mobile body and at least one lubricant supply duct (75) mounted on the movable body for connecting the pipeline to said spraying means.

    Pitch change system equipped with means for lubricating a load transfer bearing
    1. Field of the invention
    The present invention relates to the field of aeronautical propulsion. It relates to a system for changing the pitch of blades of a propeller driven by a turbomachine and in particular means for lubricating a load transfer bearing of said pitch change system.
    2. State of the art
    The change of pitch or variable pitch of blades of a turbomachine propeller is one of the ways to improve the performance and efficiency of turbomachines under different flight conditions.
    There are known turbomachines such as turboprop propeller twin propellers, for example contra-rotating, designated in English by "open rotor" and "unducted fan" equipped with these pitch change systems. Turboprop engines are distinguished from turbojets by the use of a propeller outside the nacelle (not faired) instead of a blower. The pitch change system can also be applied to a turboprop to a propeller or even adapt to one or each propeller.
    In an open rotor type turbine engine, a gas generator part and a propulsion part are aligned and arranged in a fixed cylindrical nacelle carried by the structure of the aircraft. The gas generator part can be arranged in front of or behind the propellant part. The propellant part comprises a doublet of coaxial and counter-rotating propellers, respectively upstream and downstream, which are driven in reverse rotation from one another by a turbine, in particular low pressure, of the gas generating part via a reducer, for example, with planetary gears. The propellers extend substantially radially with respect to the longitudinal axis transmission shaft outside the nacelle. In general, each propeller comprises a substantially cylindrical rotary casing carrying a hub with an outer polygonal ring received rotatably around the longitudinal axis in the fixed nacelle. The hub has radial cylindrical housings distributed around its periphery around the longitudinal axis. Shafts of radial axes, perpendicular to the longitudinal axis of the turbomachine, integral with the feet of the blades are received in the housings of the polygonal rings and also pass through radial passages of the cylindrical casing. Rotational guide bearings housed in these radial passages hold the radial shafts in their passages.
    An example of a pitch change system for each propeller is known from document WO2013 / 050704. In FIG. 2, this pitch change system 23A is installed at the heart of the rotating or mobile parts with, for example, an annular actuator 25A for driving the feet of the blades in rotation. The annular cylinder 25A comprises a cylinder 27A mounted on a fixed casing 13A and a movable piston 29A connected to a connection mechanism 26A which is connected to each shaft 47A of radial axis. A cylindrical rotary casing 11A rotates around the fixed casing. For this, at least one bearing 12A is disposed between the fixed casing 13A and the rotary casing 11 A. The system also includes a load transfer bearing 34A whose inner ring is integral with the movable piston 29A and the outer ring connected to the mechanism 26A connection and lubrication means of said bearing 34A. Thanks to a linear displacement of the piston as a result of the fluid control of the annular jack, the system 23A ensures a desired angular pivoting of the blades by the link mechanism 26A and the bearing 34A for load transfer by varying their pitch.
    However, such an architecture consisting in transforming a power arriving from the fixed part into a movement on the rotating part of the turbomachine presents many difficulties. One of the difficulties lies in the dimensioning and the integration of the different elements in this rotating part. This applies in particular to the integration of the lubrication means of the load transfer bearing which is subjected to significant thermal and mechanical stresses. Indeed, this load transfer bearing which is intended for the recovery of the thrust forces of the turbomachine moves in translation and in rotation which makes the lubrication of this bearing complex. The small space around the cylinder is constraining for the integration of the lubrication means which must connect a power source located in the fixed part and the load transfer bearing mounted on the movable piston. On the other hand, the jack is subjected to significant radial forces from the rotating part which involve deformations of the jack as well as sealing problems which inevitably have repercussions on the lubrication means of said bearing. These efforts are multiplied when the cylinder is such that it participates in a structural role.
    3. Object of the invention
    The object of the present invention is in particular to propose means for lubricating the load transfer bearing, in particular, a system for changing the pitch of blades of a turbomachine propeller taking into account the difficulties of integration in a congested environment. and displacements of the control means.
    4. Statement of the invention
    These objectives are achieved, in accordance with the invention thanks to a blade pitch change system of at least one turbomachine propeller provided with a plurality of blades, the system comprising:
    - a control means acting on a connection mechanism connected to the blades of the propeller, said control means comprising a fixed body and a body movable in translation along a longitudinal axis relative to said fixed body,
    a load transfer module arranged between the link mechanism and the control means, the load transfer module comprising at least one load transfer bearing mounted on the movable body and cooperating with the link mechanism, and
    means of lubricating said bearing, the means of lubrication comprising:
    - At least one lubricant circulation line configured to be connected to a lubricant supply source, the line extending radially outside the movable body relative to the longitudinal axis and comprising at least first and second tubular parts slidably mounted telescopically to each other along an axis parallel to the longitudinal axis, the first part being connected by a first upstream end to said fixed body and the second part being connected by a first downstream end the moving body,
    - Lubricant spraying means in at least one bearing which are mounted on said movable body; and
    - at least one lubricant supply pipe mounted on the movable part and configured so as to transfer the lubricant from the circulation pipe to said spraying means.
    Thus, this solution achieves the above-mentioned objective. The lubrication means supply the load transfer bearing whatever the position of the movable body on which the load transfer bearing is mounted. Indeed, the first and second telescopic parts make it possible to accompany and resume the movement of the mobile body of the control means in translation and thus allows the circulation of the lubricant from the fixed parts of the turbomachine to the mobile parts, and in particular to the bearing. Furthermore, these lubrication means allow integration into this congested environment without making assembly more complex. Added to this is the fact that these lubrication means are independent, which facilitates their integration into the pitch change system and onto the control means.
    According to another advantageous, but not limiting, characteristic, the first part slides inside the second part.
    According to another characteristic of the invention, a first end of the first part is fixed to a connection ring of the fixed body, said ring being secured to a fixed casing of the turbomachine. This ring makes it possible to make the junction between the fixed parts and the mobile parts.
    In particular, the control means is mounted in a non-structural manner and separate from the fixed casing, the fixed body being integral with a cylindrical wall of the fixed casing. This arrangement allows on the one hand, a gain in compactness and the passage without risk of leakage of the easements linked to the supply and to the operation of the control means. The control means of this pitch change system is configured so that it no longer supports the rotating parts and is no longer subjected to radial forces. In particular, the control means no longer undergoes bending stress which induces misalignments and leaks harmful to the control means. On the other hand, also thanks to this non-structural arrangement, it is possible to independently manage the integration of the control means and the structure of the fixed and rotary casings.
    According to another characteristic of the invention, the first part is equipped in the vicinity of its second free end with at least a first vent hole with a central axis and a second vent hole with a central axis, said axes being perpendicular to the longitudinal axis and being defined in offset and substantially parallel planes. In this way, the suction phenomena that can occur during the displacement of the first and second parts relative to one another are limited. The offset of the vent holes does not weaken the first tubular part.
    According to another aspect of the invention, the first part is formed of at least first and second tubular portions, the first and second tubular portions aligned substantially along the same axis, the first and second tubular portions being interconnected by an annular connection member configured so as to maintain a seal between the first and second portions in the event of misalignment. Thus, the annular connection member makes it possible to maintain the seal between the two tubular portions while allowing their misalignment during the displacement of the movable part. This radial or tangential misalignment is due to the geometric tolerances of the parts, to the mounting tolerances, as well as to the play-up and the deformation of the parts under the operating loads of the turbomachine.
    Advantageously, but not limited to, a ball joint is interposed at each free end of the first and second portions, and between the walls of said first and second portions and the annular connection member. The ball joint connection is a space-saving solution to solve the problems of misalignment. It also makes it possible to take into account the different positions of the control means as well as questions of tightness at high pressures of the order of 100 bar.
    According to yet another characteristic of the invention, the load transfer module comprises an internal ferrule on which the spraying means are mounted, the internal ferrule being equipped with an orifice of coaxial radial axis with an opening of a ring inside said bearing, the spraying means extending at least partly through the orifice and the opening. This configuration allows spraying directly in the bearing and on the bearings.
    Advantageously, but not limited to, centering means arranged on the internal ferrule of the bearing are configured to center and orient the spraying of the spraying means.
    According to another characteristic of the invention, the load transfer bearing is equipped with a two-row bearing and the spraying means comprise at least two nozzles for each row, the nozzles being distributed in an azimuthal manner around the axis longitudinal.
    According to yet another characteristic of the invention, the conveying conduit comprises a curved tubular body which is arranged at least partly around the movable body and fixed on a rear face of the internal ferrule.
    Advantageously, but not limited to, the conveying duct is fixed to the rear face by means of flexible collars. The flexible collar attachment is necessary due to the presence of adjustment means arranged between the mobile body and the fixed body to adjust the axial position of the mobile body relative to the fixed body. Thus, the movable body can have its entire travel.
    According to yet another characteristic of the invention, the conveying conduit comprises tubes extending along an axis substantially parallel to the longitudinal axis, said tubes are connected by a first end to the body of the conveying conduit and by a second end to the spraying means.
    Advantageously, but not limited to, the control means comprises an actuator whose movable body slides around the cylindrical wall of the fixed casing. In particular, the actuator comprises an annular cylinder.
    The invention could also relate to a system for changing the pitch of blades of at least one turbomachine propeller provided with a plurality of blades, the system comprising:
    - a control means acting on a connection mechanism connected to the blades of the propeller, said control means comprising a fixed body and a body movable in translation along a longitudinal axis relative to said fixed body,
    a load transfer module arranged between the link mechanism and the control means, the load transfer module comprising at least one load transfer bearing mounted on the movable body and cooperating with the link mechanism, and
    - lubrication means of said at least bearing, the lubrication means comprising at least one lubricant circulation pipe configured to be connected to a lubricant supply source, the pipe extending radially outside the movable body by relative to the longitudinal axis and comprising at least first and second tubular parts slidably mounted telescopically relative to one another along an axis parallel to the longitudinal axis, the first part being connected by a first upstream end to said fixed body and the second part being connected by a first end to the movable body, the first part being formed of at least first and second tubular portions aligned substantially along the same axis and which are connected together by a connecting member annular configured to maintain the seal between the two portions in case of misalignment of the first part e and the second part of the pipeline.
    5. Brief description of the figures
    The invention will be better understood, and other objects, details, characteristics and advantages thereof will appear more clearly on reading the detailed explanatory description which follows, of embodiments of the invention given by way of purely illustrative and nonlimiting examples, with reference to the appended schematic drawings.
    In these drawings:
    FIG. 1 schematically shows in axial section an example of a turbomachine with a blade pitch change system for a propeller according to the invention;
    Figure 2 is an example of a blade pitch change system of a propeller according to an example of the prior art;
    Figure 3 is an axial sectional view where are shown in more detail and schematically elements of a pitch change system connected to a blade of a propeller according to the invention;
    Figure 4 is a front view of a pitch change system in a turbomachine;
    Figure 5 is a perspective view of an example of control means according to the invention;
    Figure 6 is an axial sectional view of the control means cooperating with lubrication means according to the invention;
    Figure 7 is an axial sectional view of part of the control means illustrating first and second telescopic parts of the lubrication means of the load transfer bearing according to the invention;
    Figure 8 shows a rear view of the control means on which is arranged a routing conduit;
    Figure 9 shows in perspective an example of a routing conduit according to the invention;
    Figure 10 is an axial sectional view of the control means illustrating the connection between the conveying duct and spraying means according to the invention;
    Figure 11 illustrates in an axial section and in detail of an embodiment of the spraying means according to the invention;
    Figures 12 and 13 show embodiments of a connecting member of the lubrication means according to the invention.
    6. Description of embodiments of the invention
    In Figure 1 and in the following description is shown a turboprop non-shrouded fan of longitudinal axis X intended to equip an aircraft. However, the invention can be applied to other types of turbomachine.
    The turbomachine 1 comprises a nacelle 2 in which is arranged a gas generator which comprises, from upstream to downstream, a set of compressors 3, a combustion chamber 4 and a set of turbines
    5. A nozzle 8 is arranged downstream of the gas generator.
    In the present invention, and generally, the terms “upstream” and “downstream” are defined with respect to the circulation of gases in the turbomachine.
    The compressor set 3 can include one or two compressor (s) depending on the architecture of the single or double stage gas generator. The set of turbines 5 can comprise a high pressure turbine and a low pressure turbine, or two turbines (high pressure and intermediate pressure) and a low pressure turbine. The gas generator drives the low pressure turbine around the longitudinal axis X.
    The turbomachine comprises a pair of counter-rotating propellers with an upstream propeller 6 and a downstream propeller 7. These two upstream 6 and downstream 7 propellers are driven in rotation in a counter-rotating manner by the low pressure turbine by means of a mechanical transmission device 17. The upstream 6 and downstream 7 propellers are mounted coaxially with the longitudinal axis X of the turbomachine 1 and are arranged in parallel radial planes, which are perpendicular to the longitudinal axis X. In the present example, the propellers 6, 7 are mounted downstream of the gas generator. The mechanical transmission device 17, shown here diagrammatically, may comprise a differential reduction gear or a gearbox housing ίο planetary. It is of course possible to directly drive the upstream 6 and downstream 7 propellers by the low pressure turbine.
    According to the configuration described above, the air flow entering the turbomachine is compressed in the compressor assembly 3, then mixed with fuel and burned in the combustion chamber 4. The combustion gases generated then pass into the turbines 5 for driving, via the mechanical transmission device 17, the propellers 6, 7 in reverse rotation which provide most of the thrust. The combustion gases are expelled through the nozzle 8 participating in the thrust of the turbomachine 1. The gases pass through a gas flow stream extending substantially axially in the turbomachine between the nacelle 2 and a middle casing 56 associated with the generator gas.
    In FIGS. 3 and 4 is shown a casing 9 here generally cylindrical, mounted rotatably with respect to the nacelle 2 of the turbomachine around a rotor shaft of longitudinal axis X. The cylindrical casing 9 is also linked to a corresponding part of the mechanical transmission device 17. This rotary casing 9 or rotor casing comprises several skins or walls of revolution including at least one external wall 18 relative to a radial axis Y perpendicular to the longitudinal axis X. In the rest of the description, the terms "top >>," bottom >>, "upper >>," lower >> and "above" are defined with respect to the radial axis Y with regard to the distance from the longitudinal axis X. The rotary casing 9 comprises radial housings 11 and radial passages 53 which are coaxial and which are each traversed by a shaft 12 of radial axis Y, hereinafter radial shaft 12, connected to a foot 13 of blade 14 of a corresponding propeller 6, 7. The blades 14 extend radially outside the nacelle 2. In particular, the casing 9 comprises a polygonal ring 10, provided with radial cylindrical housings 11 here regularly distributed over its periphery. As for the external wall 18, this comprises the radial passages 53 here cylindrical regularly distributed over its periphery and crossed by the radial shafts 12. The latter extend radially through a structural arm 54 connecting the polygonal ring 10 to a radially internal skin 21 of the casing 9. This radially internal skin 21 is downstream of the median casing 56. It forms part of the wall of the gas flow stream. Each radial shaft 12 is held in its housing 53 by means of a rotary guide bearing making it possible to maintain the radial shafts in their housings 53. The rotary casing 9 is supported directly by rolling bearings on a fixed casing 15 or stator casing for ensure its rotation relative to the longitudinal axis X. The fixed casing 15 and the rotary casing 9 are coaxial.
    The turbomachine comprises a system 26 for changing the pitch of the blades 14 of the propeller 6 making it possible to vary the pitch or the pitch of the blades 14 around their radial axes so that they occupy angular positions according to the operating conditions of the turbomachine and the flight phases concerned.
    With reference to FIGS. 3 and 4, the pitch change system 26 comprises a control means 27 controlling the change of pitch of each of the blades 14 and a connection mechanism 31 connecting the control means 27 to the feet 13 of the blades 14. The control means 27 is housed between the rotary casing 9 and the fixed casing 15. The control means 27 comprises an actuator which comprises a fixed body 28 and a movable body 29 in translation relative to the fixed body 28 along the axis X. The actuator is arranged so as to move the connection mechanism substantially axially 31 which is connected to the radial shafts 12 of the feet of the blades in such a way that the axial displacement of the connecting mechanism 31 causes the pitch of the blades to change. This actuator is attached to the fixed casing
    15. That is to say that the latter is separated from the fixed casing 15 and does not constitute a structural element forming part of the fixed casing 15. The radial shafts 12 pivot around the axis Y in the radial passages 53 and 11 radial housings.
    The pitch change system 26 comprises a load transfer module 51 equipped with a load transfer bearing 34 and disposed between the link mechanism 31 and the movable body 29 so as to ensure the transmission of the axial forces exerted by the movable body 29 of the actuator. The connection mechanism 31 includes a set of articulated connecting rods which are regularly distributed around the actuator and which are intended to act on the feet of the blades 14 via the radial shafts 12 to drive them in rotation about their Y axis. has as many connecting rods 37 as there are blades. The actuator in the present invention advantageously comprises an annular actuator constituted by its movable rod relative to a fixed cylinder secured to the fixed casing 15.
    With reference to FIG. 5 in which the actuator is illustrated more precisely, the fixed body 28 is here cylindrical with a circular section. This fixed body 28 surrounds a cylindrical wall 16 of the fixed casing 15 and is mounted integral with this cylindrical wall 16 so as to be immobilized in rotation and in translation relative to the fixed casing 15 (cf. FIG. 4). To this end, the fixed body 28 comprises a connection ring 30 provided at an upstream end of the fixed body 28 and in abutment against a shoulder 40 of the fixed casing 15. The connection ring 30 is mounted on the fixed casing 15. The movable body 29 is arranged around the fixed body 28. In this way, the movable body 29 moves axially under the action of a command from the actuator. The movable body 29 only moves in translation. The latter 29 is immobilized in rotation relative to the fixed body by means of an anti-rotation device 44 fixed to the fixed body 28 and to the mobile body 29. This anti-rotation device 44 makes it possible in particular to prevent the rotation of the mobile body 29 around of the fixed body 28 during operation of the turbomachine. The anti-rotation device 44 comprises a cross member 45 extending along an axis substantially parallel to the axis X. The cross member 45 has a first end 46 connected to a yoke 48 fixed to the downstream edge of the fixed body 28 and a second end 47 opposite connected to a base 49 provided on the connection ring 30. The anti-rotation device 44 further comprises a support 50 fixed on the movable body 29 acting as a radial stop. This support 50 is crossed by the crosspiece 45 and also allows the guidance of the movable body 29 during its axial movement.
    The connection ring 30 is provided with connection interfaces 32 allowing the connection of various equipment necessary for the supply and operation of the actuator. These connection interfaces 32 include mechanical, hydraulic and / or electrical connectors ensuring the passage of the low pressure and high control pressure hydraulic lines (high flow and pressure).
    With reference to FIG. 6, the load transfer module 51 comprises an outer ring 33 and an annular internal ring 52. The outer shroud 33 is connected to the connecting mechanism 31 while the inner shroud 52 is connected to the movable body 29. For this purpose, the inner shroud 52 comprises an annular flange 42 extending along the radial axis Y and being secured to the level of a downstream end 39 of the movable body 29. Fixing means such as screws 43 make it possible to secure the flange 42 to the movable body 29. The bearing 34 comprises an outer ring 35 integral with the ferrule 33 and an inner ring 36 integral with the ferrule 52. The bearing 34 is here formed by a bearing with two rows of balls 38 which can be of the oblique contact type oriented in opposite directions so as to optimize the transmission of axial forces.
    The blade pitch change system 26 comprises lubrication means 60 of the load transfer bearing 34 comprising at least one line 61 of lubricant circulation which is configured to be connected to a supply source 69 of lubricant for its supply . This power source 69 is installed on the fixed parts of the turbomachine. The pipe 61 extends radially outside the movable body 29 relative to the longitudinal axis X. In other words, the pipe 61 extends radially above the movable body 29 and the fixed body 28. The pipeline also extends axially along an axis T parallel to the longitudinal axis X. The latter is connected on one side to the ring 30 to which the supply source 69 in lubricant is connected and another side to the movable body 29. In the present example, the pipe 61 is formed of a first part 62 and a second tubular part 63 extending along the axis T.
    In FIG. 6, the first part 62 has a first upstream end 64A which is received in a first cavity 41 of an interface 32 of the ring 30 in which it is fixed. This first upstream end 64A is fixed by screwing or by other similar means. The second part 63 has a first end 65A, here downstream, which is hydraulically connected in a second cavity 55 of a first local boss 19 positioned at the downstream end 39 of the movable body 29 of the actuator. The first and second parts 62, 63 are slidably mounted telescopically relative to each other along the axis T. In particular, the first part 62 slides in the second part 63. Of course, the second part 63 can be arranged so as to slide in the first part 62. In other words, the first part 62 is fixed relative to the fixed body 28 and the second part 63 moves axially according to the movement of the movable body 29 relative to the fixed body 28.
    With reference to FIG. 7, the first part 62 comprises at its second free downstream end 64B which slides inside the second part 63, a first vent hole 66 with a central axis C1 perpendicular to the axis T. A second vent hole 67 with a central axis C2 perpendicular to the axis T is also provided at the second free end 64B of the first part 62. The central axes C1, C2 of these first and second holes d 'vent 66, 67 are offset from each other and are defined in substantially parallel planes. A second free end 65B of the second part 63 is held radially in position and guided by a bore 57 formed in a second local boss 20 of the movable body 29. The second free end 65B comprises guide segments 73 to ensure correct guidance between the first and second parts of the pipeline. These guide segments 73 are split and installed in shallow grooves (not shown) formed in the wall of the second part 63.
    The lubrication means 60 comprise sealing means ensuring the seal between the first part 62 and the second part 63 of the pipe 60. In FIG. 7, the sealing means comprise a first seal 72 making it possible to produce so permanent sealing between the first and second telescopic parts 62, 63. This first joint 72 is of dynamic type because it must allow the relative displacement of the second part 63 relative to the first part 62. This dynamic joint 72 comprises a first element 72a and at least a second element 72b made of a material polymer. Here, two second elements 72b are provided. The first and second elements 72a, 72b are formed from different polymer materials. Advantageously, but not limited to, the first element 72a is made of an elastomer and the second elements 72b are made of a polytetrafluoroethylene or equivalent. The first element 72a has substantially the shape of a T. The two second elements 72b have an annular shape and rest on the branches of the T of the first element 72a. In particular, the second elements 72b are on either side of the leg of the T. This joint 72 is mounted in a first groove 74 formed in the wall of the second part 63. The first groove 74 is oriented towards the external wall of the first part 62 of the pipe 61. Once mounted, the first elastomer element 72a is crushed or compressed by the wall of the second part 63 and the two branches of the T of the first element 72a rise respectively on either side second elements 72b.
    These sealing means also comprise a second annular scraper seal 70 installed at the free end 65B of the second part 63. The second scraper seal 70 makes it possible to clean the external wall of the second part 62 of the pipeline from any deposit of dirt (dust, sand, etc.) during the sliding of the second part 63 in order to preserve the physical integrity of the first seal 72. This second scraper seal 70 is housed in a second open groove 71 formed in the wall of the second part 63. The second groove 71 is oriented towards the external wall of the first part 62 of the pipe 61. In this example, the second scraper seal 70 comprises a first part 70a and a second part 70b made of a polymer material. The first part 70a of the second scraper seal 70 is made of an elastomer and the second part 70b is made of a polytetrafluoroethylene or equivalent. The second part 70b has a substantially L shape and is in contact with the wall of the first part 62. The first part 70a is annular and is inserted between the second part 70b and the internal wall of the second part 63 of the pipe. The first part 70a makes it possible to compress the second part 70b so that it can scrape the external wall of the first part 62.
    The sealing means 60 also comprise seals 85 arranged around the first ends 64A, 65A of the first and second parts 62, 63 at the place of their fixing with the movable body and the fixed body (cf. FIGS. 6 and 12) .
    FIGS. 8 and 9 illustrate a conduit 75 for conveying lubricant from the lubrication means 60, this conduit transferring the lubricant from the pipe 61 to the bearing 34. For this purpose, the conduit 75 comprises a tubular body 76 which is curved and which is arranged at least partly around the actuator and in particular downstream of the movable body 29. The conduit 75 for routing comprises an inlet end 78 which is hydraulically connected in the cavity 55 of the first boss room 19 of the movable body 29. For this, this inlet end 78 is equipped with a connector 79 which comprises a body 80 with a passage orifice and a nut 81 for hydraulic connection mounted on said body 80. More specifically, the conduit 75 is fixed to the rear face of the internal shroud 52 (cf. FIG. 8). The rear face is carried by the flange 42. The latter comprises openings 68 (cf. FIGS. 6 and 10) passing through the wall of the flange 42 and one of which is crossed by the connector 79. The duct 75 is fixed by means for example of flexible 77 necklaces. Such flexible collars 77 are connected to bent portions of the tubular body 76 so as to create flexibility. The conduit 75 also comprises a plurality of axial tubes 82 which are each connected to the body 76 by a first end 83. The second axially opposite end 84 of each axial tube 82 comprises a fixing end piece 106 intended to be connected to spraying means 86 of lubricant in the load transfer bearing 34. The axial tubes 82 pass through the openings 68 formed in the wall of the flange 42 and extend axially outside the movable body 29. In particular, the tubes 82 are arranged between the movable body 29 and the internal ferrule 52. The conduit 75 routing is made of a metallic material. The connector 79 is also made of a metallic material adapted to the metallic material of the first local boss 19 of the movable body 29.
    With reference to FIGS. 10 and 11, spraying means 86 of the lubrication means are mounted on the internal ferrule 52 of the load transfer module 51. The internal ferrule 52 comprises an annular skirt 87 extending along the radial axis Y and on which the spraying means 86 are fixed with suitable fixing members. The spraying means 86 are distributed azimuthly around the longitudinal axis X. The internal ferrule 52 is also provided with an orifice 88 with a radial axis passing through the wall on the one hand and on the other radially. The inner ring 36 of the bearing 34 also includes an opening 89 with a radial axis passing through its wall on both sides and radially. The axes of the opening 89 and the orifice 88 are coaxial. At least part of the spraying means 86 extends radially through the orifice 88 and the opening 89 so as to spray the lubricant inside the bearing 34 and directly on the bearings 38. Correct targeting of the means of spraying 86 is carried out by means of centering means 90 arranged on the internal shroud 52 so as to orient and center their spraying. These centering means 90 are advantageously, but not limited to, centering sleeves which are fixed on the skirt 87 of the internal ferrule 52. Fastening elements such as screws allow the sleeves to be fixed. Alternatively, the positioning of the spraying means can be achieved by pins.
    The spraying means 86 comprise, in the present example, nozzles 107. For each row of bearings is provided at least two nozzles 107 so as to prevent the risks of obstruction of one of the nozzles. Advantageously, the nozzles 107 are arranged and distributed with respect to one another along an angular section of the order of 180 ° for uniform cooling and lubrication of the bearings. However, the nozzles 107 can be placed close to each other for integration reasons. The position of the nozzles 107 is controlled by integration constraints.
    According to another aspect of the invention as illustrated in FIGS. 12 and 13, the first tubular part 62 of the pipe 61 is formed of at least a first tubular portion 91 and a second tubular portion 92 which are connected therebetween by a connecting member 93 configured so as to allow the misalignment of the first part 62 and the second part 63 of the pipe 61. As described above, the first end 64A of the first part 62 is fixed to the ring 30 of the actuator via an interface 32. This fixed connection requires the direction of this first part 62 which is fixed relative to the second part 63. The connection member 93 and the first part 62 formed of these two portions 91, 92 solve the problems of misalignment that can occur between the first and second parts of the pipe 61 during the axial movement of the movable body 29 of the actuator. These misalignment problems can be due to manufacturing dispersions, namely, geometric tolerances, mounting tolerances between different parts of the actuator, and / or the deformation of the actuator undergoing the radial forces of the rotating part. .
    The external connecting member 93 comprises a substantially cylindrical wall 94 which envelops the free ends 91 A, 92A of the first and second tubular portions 91, 92. At each free end 91 A, 92A is arranged a ball joint 95. Each ball joint 95 is interposed between a wall of the first and second tubular portions 91, 92 and the wall 94 of the connecting member 93. The link to ball 95 is advantageously, but not limited to, produced by a plain bearing having an outer ring 96 and an inner ring 97. The wall 94 of the connection member 93 carries the outer ring 96 while the wall of each first and second portion carries respectively an inner ring 97. The spherical plain bearing is mounted to slide so as to allow pivoting and tilting of the connecting member 93 as illustrated in FIG. 13 in the event of misalignment. A system 98 for fixing the spherical plain bearing arranged on the edge of each free end 91 A, 92A makes it possible to maintain the spherical bearings on the tubular portions. This fixing system 98 comprises an internal nut 99 and a nut brake 100 axially blocking the internal ring 97 of the spherical plain bearing. An elastic ring 101 for holding the nut brake is also provided. Sealing elements 102 are installed on both sides axially of the two ball joints. The sealing elements 102 can be a lip seal or an O-ring. To be able to use standard elements, a spacer
    103 is placed axially between an internal ring 97 and a sealing element 102 of each spherical plain bearing. An external nut 104 and its braking system 105 allow the assembly to be finalized. The external nut
    104 and the braking system 105 are carried by the connecting member 93, in particular the wall 94.
    权利要求:
    Claims (6)
    [1" id="c-fr-0001]
    System (26) for changing the pitch of blades (14) of at least one propeller (6, 7) of a turbomachine provided with a plurality of blades, the system (26) comprising:
    - a control means (27) acting on a connection mechanism (31) connected to the propeller blades, said control means (27) comprising a fixed body (28) and a body movable (29) in translation according to a longitudinal axis (X) relative to said fixed body (28),
    - a load transfer module (51) arranged between the link mechanism (31) and the control means (27), the load transfer module (51) comprising at least one mounted load transfer bearing (34) on the movable body and cooperating with the link mechanism, and
    - lubrication means (60) of said bearing (34) characterized in that the lubrication means (60) comprise:
    - at least one line (61) for circulating lubricant configured to be connected to a source (69) of lubricant supply, the line extending radially outside the movable body (29) relative to the axis longitudinal (X) and comprising at least first and second tubular parts (62, 63) slidingly mounted telescopically relative to one another along an axis parallel (T) to the longitudinal axis (X), the first part (62) being connected by a first upstream end (64A) to said fixed body (28) and the second part (63) being connected by a first downstream end (65A) to the mobile body (29),
    means for spraying lubricant into the bearing which are mounted on said movable body (29), and
    - at least one lubricant delivery duct (75) mounted on the movable part (29) and configured so as to transfer the lubricant from the circulation pipe (61) to said spraying means.
    [2" id="c-fr-0002]
    2. System (26) according to the preceding claim, characterized in that the first part (62) slides inside the second part (63).
    [3" id="c-fr-0003]
    3. System (26) according to any one of the preceding claims,
    10 characterized in that the first part (62) has a first end fixed to a connection ring (30) of the fixed body (28), said ring (30) being integral with a fixed casing (15) of the turbomachine.
    [4" id="c-fr-0004]
    4. System (26) according to the preceding claim, characterized in that
    The first part (61) is equipped in the vicinity of its second free end (64B) with at least one first vent hole (66) with a central axis (C1) and a second vent hole (67 ) of central axis (C2), said axes (C1, C2) being perpendicular to the longitudinal axis (X) and being defined in offset and substantially parallel planes.
    [5" id="c-fr-0005]
    5. System (26) according to any one of claims, characterized in that the first part (62) is formed of at least first and second tubular portions (91, 92) aligned substantially along the same axis (T ), the first and second portions (91, 92)
    2 5 tubulars being interconnected by an annular connection member (93) configured so as to maintain a seal between the first and second portions (91,92) in the event of misalignment.
    [6" id="c-fr-0006]
    6. System (26) according to the preceding claim, characterized in that
    3 0 that a ball joint (95) is interposed at each free end (91 A, 92A) of the first and second portions (91, 92) and between the walls of said first and second portions (91, 92) and the annular connection member (93).
    System (26) according to any one of the preceding claims, characterized in that the load transfer module (51) comprises an internal ferrule (52) on which the spraying means (86) are mounted, the internal ferrule (52 ) being equipped with an orifice (88) of coaxial radial axis with an opening (89) of an inner ring (36) of said bearing (34), the spraying means (86) extending at least in part to through the orifice (88) and the opening (89).
    System (26) according to any one of the preceding claims, characterized in that the load transfer bearing (34) is equipped with a two-row bearing and the spraying means (86) comprise at least two nozzles (107 ) for each row, the nozzles (107) being distributed azimuthally around said longitudinal axis (X).
    System (26) according to any one of the preceding claims, characterized in that the conveying conduit (75) comprises a curved tubular body (76) which is arranged at least partially around the movable body (29) and fixed on a rear face of the internal shroud (52).
    System (26) according to the preceding claim, characterized in that the conveying conduit (75) comprises tubes (82) extending along an axis substantially parallel to the longitudinal axis (X), said tubes being connected by a first end (83) to the body (76) of the conveying conduit (75) and via a second end (84) to the spraying means (86).
    1/7
    47A
    29A 13A
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    同族专利:
    公开号 | 公开日
    CN109641649A|2019-04-16|
    US20200172228A1|2020-06-04|
    EP3504120B1|2020-10-28|
    US10940938B2|2021-03-09|
    FR3055309B1|2018-08-17|
    EP3504120A1|2019-07-03|
    WO2018037183A1|2018-03-01|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    CH271823A|1946-07-18|1950-11-15|Vickers Armstrongs Ltd|Propulsion installation comprising a reversible pitch marine propeller.|
    US20100008779A1|2008-07-14|2010-01-14|Carvalho Paul A|Integrated actuator for a propeller system|
    WO2013050704A1|2011-10-03|2013-04-11|Snecma|Turbo engine with propeller for an aircraft with a system for changing the pitch of the propeller|
    WO2014013201A1|2012-07-20|2014-01-23|Snecma|Device for the transfer of heat between a lubrication pipe and a turbomachine blade pitch actuator control hydraulic pipe|FR3086326A1|2018-09-24|2020-03-27|Safran Aircraft Engines|LUBRICATION SYSTEM FOR A GUIDE BEARING OF A SHAFT OF AN AIRCRAFT TURBOMACHINE|
    FR3100223A1|2019-08-30|2021-03-05|Airbus Helicopters|Power transmission box, rotorcraft equipped with such a transmission box and associated variation method|FR2992703B1|2012-06-27|2015-01-30|Snecma|BEARING WITH MEDIUM LUBRICATION AND SYSTEM FOR CHANGING THE PITCH OF THE BLADES OF AN AIRCRAFT AIRBORNE PROPELLER, EQUIPPED WITH THE SAID BEARING|
    FR3013325B1|2013-11-20|2015-11-27|Snecma|PRESSURE OIL SUPPLY DEVICE OF A TURBOMACHINE LINEAR ACTUATOR|FR3075860B1|2017-12-22|2019-11-29|Safran Aircraft Engines|DYNAMIC SEAL BETWEEN TWO ROTORS OF AN AIRCRAFT TURBOMACHINE|
    FR3094031B1|2019-03-18|2021-05-14|Safran Aircraft Engines|SET FOR A TURBOMACHINE|
    法律状态:
    2017-05-17| PLFP| Fee payment|Year of fee payment: 2 |
    2018-03-02| PLSC| Publication of the preliminary search report|Effective date: 20180302 |
    2018-07-20| PLFP| Fee payment|Year of fee payment: 3 |
    2019-07-22| PLFP| Fee payment|Year of fee payment: 4 |
    2020-07-21| PLFP| Fee payment|Year of fee payment: 5 |
    2021-07-22| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1657974A|FR3055309B1|2016-08-26|2016-08-26|PASTE CHANGE SYSTEM EQUIPPED WITH MEANS FOR LUBRICATING A LOAD TRANSFER BEARING|
    FR1657974|2016-08-26|FR1657974A| FR3055309B1|2016-08-26|2016-08-26|PASTE CHANGE SYSTEM EQUIPPED WITH MEANS FOR LUBRICATING A LOAD TRANSFER BEARING|
    PCT/FR2017/052237| WO2018037183A1|2016-08-26|2017-08-16|Pitch-changing system equipped with means for lubricating a load-transfer bearing|
    CN201780052251.6A| CN109641649A|2016-08-26|2017-08-16|Pitch-variable system equipped with the device for lubricating load transmission bearing|
    US16/327,288| US10940938B2|2016-08-26|2017-08-16|Pitch-changing system equipped with means for lubricating a load-transfer bearing|
    EP17768171.5A| EP3504120B1|2016-08-26|2017-08-16|Pitch-changing system equipped with means for lubricating a load-transfer bearing|
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