TURBOMACHINE MODULE EQUIPPED WITH A PITCH CHANGE SYSTEM AND A FLUID TRANSFER DEVICE

Abstract

Turbomachine module, this module having a longitudinal axis (X) and comprising: a propeller (3) comprising a plurality of variable-pitch blades (30), a speed reducer (34), a pitch change system (50) for the blades (30), a fluid transfer device (94) configured to supply fluid to the hydraulic actuator (52) of the pitch change system (50), this transfer device (94) comprising a stator part (96) engaged in a rotor part (97), and a member (99) for mechanically connecting the stator part (96) of the transfer device (94) to the planet carrier (38) of the speed reducer (34), and for fluidically connecting a fluid inlet port (98a) of the transfer device (94) to fluid pipes (95) configured to be connected to a fluid reservoir (91). Figure for abstract: Figure 4

Description

Title of the invention: TURBOMACHINE MODULE EQUIPPED WITH A PITCH CHANGE SYSTEM AND A FLUID TRANSFER DEVICE Field of invention

[0001] The present invention relates to the field of aircraft turbomachines. It relates in particular to a turbomachine module comprising variable-pitch blades, a blade pitch setting system and a device for transferring fluid to the setting system. It also relates to the corresponding turbomachine. Technical background

[0002] Turbomachines generally comprise a ducted propeller called a fan, or an unducted propeller, equipped with variable pitch moving blades. A propeller equipped with variable pitch or variable pitch blades makes it possible to adjust the pitch or orientation of the blades according to the flight parameters so as to optimize the operation of the propeller. This configuration makes it possible to optimize the module in which such a propeller is integrated. As a reminder, the pitch angle of a blade corresponds to the angle, in a longitudinal plane perpendicular to the axis of rotation of the blade, between the chord of the blade and the plane of rotation of the propeller.The variable-pitch blades can occupy a so-called reverse thrust position (known as "reverse") in which they generate counter-thrust to help slow down the aircraft and a feathering position in which, in the event of failure or breakdown, they limit their resistance. The propeller blades are rotated by a drive shaft. Such an example of a propeller or fan with variable-pitch blades is described in patent application FR-A1-3 087 233.

[0003] Turbomachines equipped with unducted propellers are known by the English term "open rotor" or "unducted fan". In this category of turbomachine, there are those which have two unducted and counter-rotating propellers (known by the English acronym UDF for "Unducted Fan") or those having a single unducted propeller and a rectifier comprising several stator blades (known by the English acronym USF for "Unducted Single Fan"). The propeller or propellers forming the propulsion part can be placed at the rear of the gas generator (or engine) so as to be of the pusher type or at the front of the gas generator so as to be of the tractor type. These turbomachines are turboprops which are distinguished from turbojets by the use of a propeller outside the nacelle (unducted) instead of an internal fan presented above. This allows to increase the rate of dilution in a very significant way without being penalized by the mass and drag of the casings or nacelles intended to surround the propeller or fan blades. Variable pitch allows for the same purpose to brake the aircraft or to limit resistance in the event of failure.

[0004] Currently, whether it is ducted fans or unducted propellers with variable pitch blades, the pitch change system comprises a control means which is connected on the one hand to a fan shaft which is typically driven by the engine shaft via a speed reducer and on the other hand to a connecting mechanism coupled to the variable pitch blades. The control means, located in a rotating frame of reference of the turbomachine, generally comprises a hydraulic actuator comprising a movable body which, when moved, acts on the position of the blades of the variable pitch blades. The actuator is supplied by a fluid whose supply source is arranged in a fixed frame of reference of the turbomachine. A fluid transfer device to allow the passage from the fixed frame of reference to the rotating frame of reference can be arranged downstream of the speed reducer involving a large radius integration which risks causing an increase in fluid leaks.Since the transfer device is in a difficult-to-access area, this can lead to accessibility problems for maintenance. Furthermore, the risk of leaks is greater downstream of the speed reducer because there are greater clearances downstream of the speed reducer and a greater tangential speed due to the larger dimensions of certain components, in particular the radius of the input shaft of the low-pressure turbine shaft which transmits the torque to the reducer.

[0005] Propellers today have large diameters to increase the bypass ratio of turbomachines. However, with the pitch change system and the large diameter of the propeller, the mass of the complete module comprising these elements is significant and can influence its stability during rotation of the propeller. This instability problem can also induce fluid leaks at the level of the control means and throughout the lubrication enclosure.

[0006] Furthermore, the arrangement of the fluid transfer device in such a space is not easy to access and does not allow independent assembly or disassembly without intervening on other parts of the turbomachine.

[0007] The Applicant has already proposed arranging the fluid transfer device upstream of the speed reducer. In document FR-A1-3 130 895 for example, a turbomachine module is described comprising a propeller, a speed reducer, and a system for changing the pitch of the propeller blades arranged axially upstream of the speed reducer and comprising a hydraulic actuator. The fluid transfer device is arranged axially upstream of the speed reducer and is configured to supply fluid to the hydraulic actuator for changing the pitch of the blades. This transfer device is centered on the axis and comprises a stator part at least partly engaged in a rotor part integral in rotation with the hydraulic actuator.

[0008] The integration of the transfer device upstream of the speed reducer allows in particular easy and rapid access to the transfer device so that it can be dismantled / assembled for maintenance.

[0009] The fluid transfer device comprises an internal fluid circuit comprising at least one fluid inlet port carried by the stator part and at least one fluid outlet port carried by the rotor part. The stator part of the transfer device is connected to the planet carrier by a connecting member. This member ensures on the one hand a mechanical connection of this stator part to the planet carrier, and on the other hand a fluid connection of the aforementioned inlet port to fluid pipes configured to be connected to a fluid reservoir.

[0010] In the aforementioned document, this member is formed by a tubular element forming a “flexible connection” between the stator part and the planet carrier in order to limit the risks of misalignment and constraints between the rotor and stator parts of the transfer device. Summary of the invention

[0011] The invention aims to optimize the technology described above and in particular to optimize the connecting member. This connecting member must advantageously allow certain degrees of freedom and prohibit other(s), which is not achievable or difficult to conceive with a simple tubular element.

[0012] We achieve this objective in accordance with the invention by means of a turbomachine module, this module having a longitudinal axis and comprising: - a propeller intended to be driven in rotation around the axis by a shaft and comprising a plurality of variable-pitch blades, - a speed reducer comprising a sun gear rotating about the axis, a crown gear rotating about the axis and the sun gear, and satellites mounted between the sun gear and the crown gear and meshed with the sun gear and the crown gear, the satellites being carried by a planet carrier which is fixed in rotation about the axis, the crown gear being connected to said shaft, - a blade pitch change system arranged axially upstream of the speed reducer and comprising a hydraulic actuator which extends along the axis and which is rotationally integral with the shaft, - a fluid transfer device arranged axially upstream of the speed reducer and configured to supply fluid to the hydraulic actuator for the purpose of changing the pitch of the blades, this transfer device being centered on the axis and comprising a stator part at least partly engaged in a rotor part integral in rotation with the hydraulic actuator, the device fluid transfer comprising an internal fluid circuit comprising at least one fluid inlet port carried by the stator part and at least one fluid outlet port carried by the rotor part, and - a mechanical connecting member of the stator part of the transfer device to the planet carrier, and of fluidic connection of said at least one fluid inlet port to fluid pipes configured to be connected to a fluid reservoir,

[0013] characterized in that the mechanical connecting member comprises an assembly of at least three elements comprising:

[0014] - a first upstream element capable of forming a mechanical connection with the stator part of the transfer device and to form a fluid connection between said at least one inlet port and the pipes,

[0015] - a second downstream element capable of forming a mechanical connection with the planet carrier, And

[0016] - at least one third intermediate element capable of forming a mechanical connection between the first and second elements so as to mutually block the first and second elements in rotation around the axis and to mutually allow degrees of freedom in translation and in rotation with respect to the other two axes perpendicular to the longitudinal axis in a three-dimensional frame of reference, or even also in translation along the longitudinal axis.

[0017] The connecting member has a dual function of fluid connection and mechanical connection. According to the invention, this connection has at least four or five degrees of freedom, namely two degrees of freedom in translation and in rotation with respect to the two axes perpendicular to each other and to the longitudinal axis, or even one degree of freedom in axial translation along the longitudinal axis. Alternatively, this last degree of freedom could be obtained by connecting the first element with the stator part of the transfer device.

[0018] The module also includes one or more of the following features, taken alone or in combination: - said third element is a grooved tubular sleeve which extends along the axis and which comprises an upstream end comprising male or female grooves engaged in female or male grooves of the first element, and a downstream end comprising male or female grooves engaged in female or male grooves of the second element. - the male splines (for example at both ends of the sleeve) have curved profiles and are capable of rotating in the corresponding female splines. the first element comprises an internal annular groove for receiving a first stop ring which surrounds the upstream end of the sleeve, this first stop ring being free to move axially around the sleeve towards the second element and being able to come into axial abutment against a stop of the sleeve when it moves axially around the sleeve towards the first element, and the second element comprises an internal annular groove for receiving a second stop ring which surrounds the downstream end of the sleeve, this second stop ring being free to move axially around the sleeve towards the first element and being able to come into axial abutment against a stop of the sleeve when it moves axially around the sleeve towards the second element; in the case of inverted splines, the ring-receiving grooves would be external grooves; at least three third elements are distributed around the axis and each provide said mechanical connection between the first and second elements; each of the third elements comprises a flexible member formed from a single piece; each of the third elements comprises three parallel walls, respectively upstream, intermediate and downstream, spaced from each other, the upstream and intermediate walls being connected together by two first side walls located on two opposite sides of each of these walls, and the intermediate and downstream walls being connected together by two second side walls located on two opposite sides of each of these walls, the first and second side walls being elastically deformable; the sides of the intermediate wall which are connected by the first side walls to the upstream wall are different from the sides of this intermediate wall which are connected by the second side walls to the downstream wall; the upstream wall comprises a central orifice crossed by a first pin which is carried by the first element and which extends parallel to the axis, the first pin being able to slide axially in the orifice and carrying a stop ring configured to limit an axial displacement stroke of the pin in the orifice in the direction of the transfer device, and the downstream wall comprises a central orifice crossed by a second pin which is carried by the second element and which extends parallel to the axis, the second pin being able to slide axially in the orifice and carrying a stop ring configured to limit an axial displacement stroke of the pin in the orifice in the direction of the reducer; each pin passes through a cylindrical ring engaged in the hole in the wall corresponding and capable of coming into axial abutment against the stop ring carried by this pin; said third element comprises a rigid body extending along the axis and carrying an elastically deformable annular block at each of its axial ends, the upstream end of the body being surrounded by a first block and integral in rotation with this first block which is fixed to the first element, and the downstream end of the body being surrounded by a second block and integral in rotation with this second block which is fixed to the second element; each of the blocks is secured to the body by radial screws passing through the block and screwed into the body; alternatively, each of the blocks is secured to the body by axial screws passing through the block and screwed into the body the first block is fixed to the first element by at least one screw or stud parallel to the axis, and the second block is fixed to the second element by at least one pin which is carried by the second element and which is parallel to the axis, said at least one pin being engaged in a complementary housing of the second block and capable of sliding axially in this housing; said third element comprises a helical spring extending along the axis; the spring comprises a downstream end which is engaged and fixed on a cylindrical stud of the second element, and an upstream end which is engaged in a cylindrical ring, this cylindrical ring being engaged in a cavity of the first element and able to slide axially in this cavity; the spring is axially constrained between the ring and the second element; the second element comprises a first clamping system, and the ring comprises a second clamping system, these first and second clamping systems being configured to be fixed to a spring stressing tool; said third element comprises a gimbal system extending along the axis; said cardan system comprises a two-part body, one of the body parts being connected by a first cardan connection to the first element, and the other of the body parts being connected by a second cardan connection to the second element, the two body parts being engaged and able to slide one inside the other; one of the body parts comprises internal splines engaged in external splines of the other body part, one of the body parts carrying a stop ring limiting the axial movement of the parts relative to each other.

[0019] The invention further relates to an aircraft turbomachine comprising at least one turbomachine module having any one of the preceding characteristics. Brief description of the figures

[0020] The invention will be better understood, and other aims, details, characteristics and advantages thereof will appear more clearly on reading the detailed explanatory description which follows, of embodiments of the invention given as purely illustrative and non-limiting examples, with reference to the appended schematic drawings in which:

[0021] [Fig-1] [Fig.l] is a schematic view, in axial and partial section of an example of a turbomachine with a propeller here shrouded to which the invention applies;

[0022] [Fig.2] [Fig.2] schematically represents and follows an axial section partial, an example of a module with a system for changing the pitch of the blades of a propeller and a fluid transfer device cooperating with the pitch change system;

[0023] [Fig.3] [Fig.3] is a schematic axial sectional view of a means of control and a fluid transfer device;

[0024] [Fig.4] [Fig.4] is a perspective and partial sectional view of part of a module according to the invention and illustrates a first embodiment of the connecting member;

[0025] [Fig.5] [Fig.5] is a perspective view of a first part or upstream part of the connecting member of [Fig.4];

[0026] [Fig.6a-6b] Figures 6a and 6b are perspective and partial sectional views of the first part or upstream part of the connecting member and the fluid transfer device of [Fig.4];

[0027] [Fig.7] [Fig.7] is a perspective and partial sectional view of the three parts of the connecting member of [Fig.4];

[0028] [Fig.8] [Fig.8] is a sectional view of the three parts of the connecting member and the fluid transfer device of [Fig.4];

[0029] [Fig.9] [Fig.9] is an enlarged view of a detail of [Fig.8];

[0030] [Fig. 10] [Fig. 10] is a perspective and partial sectional view of a part of a module according to the invention and illustrates a second embodiment of the connecting member;

[0031] [Fig. 11] [Fig. 11] is a sectional view of the three parts of the connecting member and the fluid transfer device of [Fig. 10];

[0032] [Fig. 12] [Fig. 12] is a perspective and partial sectional view of a part of a module according to the invention and illustrates a third embodiment of the connecting member;

[0033] [Fig. 13] [Fig. 13] is a sectional view of the three parts of the connecting member and the fluid transfer device of [Fig. 12];

[0034] [Fig. 14] [Fig. 14] is a perspective and partial sectional view of a part of a module according to the invention and illustrates a fourth embodiment of the connecting member;

[0035] [Fig. 15] [Fig. 15] is a sectional view of the three parts of the connecting member and the fluid transfer device of [Fig. 14];

[0036] [Fig. 16] [Fig. 16] is a perspective and partial sectional view of a part of a module according to the invention and illustrates a fifth embodiment of the connecting member; and

[0037] [Fig. 17] [Fig. 17] is a sectional view of the three parts of the connecting member and the fluid transfer device of [Fig. 16]. Detailed description of the invention

[0038] The invention applies to a turbomachine intended to be mounted on an aircraft. The aircraft comprises a fuselage and at least two wings extending on either side of the fuselage along the axis of the fuselage. At least one turbomachine is mounted for example under each wing. The turbomachine may be a turbojet, for example a turbomachine equipped with a ducted fan (turbofan) or a turboprop, for example a turbomachine equipped with an unducted propeller ("open rotor", "USF" for "Unducted Single Fan" or "UDF" for "Unducted Fan"). Of course, the invention applies to other types of turbomachine.

[0039] Generally speaking and in the remainder of the description, the term “blower” is used to designate either a blower or a propeller.

[0040] In the present invention, and in general, the terms "upstream", "downstream", "axial" and "axially" are defined with respect to the circulation of gases in the turbomachine and here along the longitudinal axis X (and even from left to right in [Fig. 1]). Similarly, the terms "radial", "radially", "internal", "internal", "external" and "external" are defined with respect to a radial axis Z perpendicular to the longitudinal axis X and with respect to the distance from the longitudinal axis X. Insofar as the X axis is horizontal, the Z axis is vertical and oriented for example upwards. The Y axis is further defined, which is an axis perpendicular to the X and Z axes and which, with these axes, forms part of a three-dimensional reference frame of origin 0.

[0041] To facilitate its manufacture and assembly / mounting / disassembly, a turbomachine is generally modular, i.e. it comprises several modules which are manufactured independently of each other and which are then assembled together. The modularity of a turbomachine also facilitates its maintenance. In the present application, we understand by "turbomachine module", a module which includes in particular a blower or propeller and a shaft to drive the blower.

[0042] In [Fig. 1], the turbomachine 1 comprises a gas generator 2 upstream of which a fan 3 is mounted. The gas generator 2 typically comprises, from upstream to downstream, 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. The rotors of the low-pressure compressor 4 and the low-pressure turbine 8 are mechanically connected by a low-pressure shaft 9 so as to form a low-pressure body. The rotors of the high-pressure compressor 5 and the high-pressure turbine 7 are mechanically connected by a high-pressure shaft 10 so as to form a high-pressure body. The high-pressure body is guided in rotation about the longitudinal axis by a first bearing 11 with upstream rolling bearings and a second bearing 12 with downstream rolling bearings. The first bearing 11 is mounted radially between an intercompressor casing 13 and an upstream end of the high-pressure shaft 10.The inter-compressor casing 13 is arranged axially between the low and high pressure compressors 4, 5. The second bearing 12 is mounted radially between an inter-turbine casing 14 and a downstream end of the high pressure shaft 10. The inter-turbine casing 14 is arranged axially between the low and high pressure turbines 7, 8. The low pressure body is guided in rotation about the longitudinal axis X via a third bearing 15 with rolling bearings and a fourth, preferably double, bearing 16 with rolling bearings. The latter are mounted radially between an exhaust casing 17 and a downstream end of the low pressure shaft 9. The exhaust casing 17 is located downstream of the low pressure turbine 8. The third bearing 15 is mounted radially between an inlet casing 18 and an upstream end of the low pressure shaft 9. The high pressure shaft 10 extends radially at least partly outside the low pressure shaft 9 and are coaxial.

[0043] In another configuration not shown, the low pressure or low pressure body comprises the low pressure compressor which is connected to an intermediate pressure turbine. A free power turbine is mounted downstream of the intermediate pressure turbine and is connected to the propeller described below via a power transmission shaft to drive it in rotation.

[0044] In the example shown, the fan 3 shown is shrouded by a casing 19 which carries (with stator blades mounted downstream of the fan) a nacelle 20. The fan 3 compresses an air flow which enters the turbomachine by dividing into a primary air flow F1 and a secondary air flow F2 at a separation nozzle 21. The latter is carried by the inlet casing 18 centered on the longitudinal axis X. The inlet casing 18 is extended downstream by an external casing or inter-stream casing 22. The primary air flow F1 circulates in a primary stream 23 which passes through the gas generator 2 and escapes therefrom through a primary nozzle 24. The secondary air flow F2 circulates in a secondary vein 25 and escapes from it through a secondary nozzle 26. The primary vein 23 and the secondary vein 25 are separated by the inter-vein casing 22.

[0045] The fan 3 comprises a series of blades 30 extending radially around a rotor 31. The rotor 31 is traversed by a cylindrical shaft 32, centered on the longitudinal axis X. The shaft 32 drives the rotor 31 in rotation around the longitudinal axis X. The shaft 32 is itself driven in rotation by a power transmission shaft of longitudinal axis X via a power transmission mechanism 33. In the present example, the power transmission shaft is the low pressure shaft 9. The shaft 32 and the low pressure shaft 9 are coaxial. Alternatively, the power shaft is a power turbine shaft supplied with gas by the gas generator 2.

[0046] With reference to Figures 1 and 2, the power transmission mechanism 33 is a speed reducer 34 making it possible to reduce the rotational speed of the shaft 32 relative to the speed of the low pressure shaft 9. On the other hand, the speed reducer 34 allows the arrangement of a fan with a large diameter so as to increase the bypass ratio.

[0047] The reducer 34 is of the planetary gear train type. The latter is housed in a lubrication enclosure 35 in which it is lubricated. The speed reducer is connected to the shaft 32. Typically, the speed reducer 34 comprises a sun gear 36 (or internal planetary), satellites 37, a planet carrier 38 and an external ring gear 39 (or external planetary). In the present example, the sun gear 36 is centered on the longitudinal axis X and is coupled in rotation with the power shaft (here the low pressure shaft 9) along the longitudinal axis X. The latter comprises first elements intended to cooperate with second complementary coupling elements carried by the sun gear 36. The satellites 37 (in the form of pinions) are carried by the planet carrier 38 and each rotates around an axis substantially parallel to the longitudinal axis X. Each of the satellites 37 meshes with the sun gear 36 and the outer ring gear 39.The satellites 37 are arranged radially between the sun gear 36 and the outer ring gear 39 and meshed with the latter.

[0048] The outer ring 39 is coupled in rotation with the shaft 32. The ring 39 is centered on the longitudinal axis. In this way, the sun 36 forms the input of the speed reducer 34 while the outer ring 39 forms the output thereof. The planet carrier 38 is, on the other hand, fixed relative to the ring 39. The planet carrier 38 is in particular fixed to a fixed structure of the turbomachine via a support shell 40. The latter is rigidly fixed to the input casing 18 of the turbomachine. The support shell 40 is also fixed to a first bearing support 41, fixed, integral with the input casing 18. The first bearing support 41 is installed downstream of the speed reducer speed 34. Alternatively, the planet carrier 38 is fixed on a radially internal shell of the input casing 18 or directly on a second bearing support 44. This bearing support 44 described below is installed upstream of the speed reducer 34.

[0049] The third bearing 15 is mounted downstream of the speed reducer 34. Rolling guide bearings are also arranged upstream of the speed reducer 34 to guide the fan shaft 32 in rotation. These bearings are also arranged in the lubrication enclosure 35. More precisely, we can see a fifth bearing 42 with (ball) bearings just upstream of the reducer 34 and a sixth bearing 43 with (roller) bearings upstream of the bearing 42. The outer rings of these bearings are carried by the second bearing support 44, fixed, integral with the inlet casing 18. The inner rings are integral with the fan shaft 32.

[0050] With reference to figures 1 and 2, the blades 30 are variable-pitch. Each blade 30 comprises a root 45 and a blade 46 extending radially outward from the root 45. In the example of this figure 1, the free end of the blades is delimited radially by the casing 19. The root 45 of each blade 30 is typically in the form of a shaft which is pivotally mounted along a setting axis C in an internal housing 47 of a ring 48. Alternatively, the root and the blade are separated, the blade 46 fitting into the root 45 via a dovetail connection. The ring 48 is integral with the fan rotor 31, is centered on the longitudinal axis and comprises several housings 47 distributed regularly around the axis X. There are as many housings 47 as there are blade roots. The setting axis C is parallel to the radial axis.The shaft of the foot 45 is pivotally mounted by means of at least two guide bearings 49 mounted in each housing 47 and in a superimposed manner along the radial axis Z. These bearings 49 are preferably, but not limited to, rolling bearings and the rolling elements here respectively comprise balls.

[0051] The blades 30 are set using a pitch change system 50 installed in the rotor 31. The pitch change system 50 is arranged in particular upstream of the speed reducer 34. The pitch change system 50 comprises a control means 52 intended to act on the blades 30. The pitch change system 50 also comprises a connecting mechanism 51 connecting the blades 30 to the control means 52.

[0052] The control means 52 is arranged upstream of the speed reducer 34 and comprises a linear actuator (linear cylinder) with an axis coaxial with the longitudinal axis X. Alternatively, the actuator is of the rotary type (rotary cylinder) along the longitudinal axis X.

[0053] The control means 52 (actuator) will not be described in detail and reference may be made to the prior application FR-A1-3 130 895 to know an example of it. configuration and operation.

[0054] The pitch change system 50 comprises means for supplying fluid to the actuator ensuring its control. The fluid received by the actuator is for example a pressurized hydraulic fluid, coming from a fluid supply system 90, so that the actuator occupies at least two positions. Of course, the actuator can occupy several intermediate positions depending on the different flight phases of the aircraft. These two positions correspond respectively to the thrust reversal position known in English as "reverse" and to the feathering position of the variable-pitch blades. The movement of the actuator along the longitudinal axis X causes the movement of the connecting mechanism 51, such that the latter causes the blades of the blades to pivot and pitch around the pitch axis C.

[0055] The pitch change system 50 will not be described in detail and reference may be made to the prior application FR-A1-3 130 895 to learn an example of its configuration and operation.

[0056] The rotor 31 may also comprise a device 180 for feathering the blades 46, in particular in the event of failure (or breakdown) of the control means 52 (for example a failure in the hydraulic supply of the control means 52). As a reminder, the feathering position corresponds to a positive setting generally substantially equal to 90°.

[0057] The feathering device 180 will not be described in detail and reference may be made to the prior application FR-A1-3 130 895 to learn an example of its configuration and operation.

[0058] The fluid supply system 90 makes it possible to distribute a lubricating fluid to the various components and / or equipment that need it, such as the control means 52, the bearings, etc. The supply system 90 comprises, for example, a fluid reservoir 91, a hydraulic pump 92 making it possible to circulate the fluid to the components and / or equipment from the reservoir 91, and a servovalve 93 making it possible to regulate the pressure of the fluid in the control means 52 according to the necessary setting. The servovalve 93 is electrically controlled by an electronic computer 27 of the turbomachine, which is known by the acronym “ECU” for “Electronic Control Unit.” The reservoir 91 is arranged in a fixed reference frame of the turbomachine and generally in the nacelle 20 illustrated in [Fig.l] or in the inter-vein casing 22. The pump 92 and the servovalve 93 are also arranged in the fixed reference frame of the turbomachine.

[0059] The turbomachine comprises a fluid transfer device 94, between a stator and a rotor, mounted in the supply system 90. The control means 52 being located in a rotating reference frame, the fluid transfer device 94 or bearing of fluid transfer system allows the transfer of fluid from the fixed reference to the rotating reference of the turbomachine 1. This transfer device 94 is known by the English acronym "OTB" for "Oil transfer Bearing". The fluid transfer device 94 is arranged upstream of the speed reducer 34. The location of the fluid transfer device is advantageous because it makes it easier to disassemble / assemble without intervening on the speed reducer. The supply system 90 also comprises several supply pipes 95 for conveying the fluid to the components and / or equipment. The pipes 95 (two in the present example) pass through the planet carrier 38 and are connected to the servovalve 93. In [Fig.4], one of the two pipes shown passes through the planet carrier 38 and is connected to the fluid transfer device 94.The planet carrier 38, which is immobile in rotation, allows the passage of the pipes 95 through it as well as inside the fan shaft 32.

[0060] The transfer device 94 can extend inside the shaft 32 (which is hollow) so as to reduce the axial and radial size. This is illustrated precisely in [Fig. 2]. More precisely still, the transfer device 94 is arranged inside the control means 52. The size is advantageously reduced upstream where the control means 52 is located. The transfer device 94 comprises a stator part 96 and a rotor part 97.

[0061] One of the stator and rotor parts is engaged in the other, so as to reduce the size and form a compact assembly that is easy to assemble and disassemble. In the example shown in [Fig. 3], it is the stator part 96 which is engaged in the rotor part 97.

[0062] The stator portion 96 is mounted securely to a fixed structure of the turbomachine. In the present example, the stator portion 96 is fixed to the planet carrier 38 by a connecting member 99. This connecting member 99 is configured so as to provide a “flexible connection” between the stator portion 96 and the planet carrier 38 here. In this way, the risks of misalignment and stresses between the rotor portion 97 and the stator portion 96 are reduced.

[0063] The transfer device 94 will not be described in detail and reference may be made to the prior application FR-A1-3 130 895 to learn an example of its configuration and operation.

[0064] Essentially, the transfer device 94 comprises an internal fluid circuit comprising at least one fluid inlet port 98a carried by the stator part 96 and at least one fluid outlet port 98b carried by the rotor part 97. The or each outlet port 98b is connected to the pitch change system 50 and in particular to the hydraulic actuator for the purpose of supplying it with fluid and changing the pitch of the blades 30. The or each inlet port 98a is connected to the pipe 95 or to one of the pipes 95.

[0065] Preferably, the pipes 95 do not take up any force.

[0066] The invention relates to an improvement of the module and in particular of the connecting member 99. This connecting member 99 has a dual function:

[0067] - it provides a mechanical connection of the stator part 96 of the transfer device 94 to the satellite carrier, and

[0068] - it provides a fluid connection from the fluid inlet ports 98a to the pipes 95 of fluid configured to be connected to the reservoir 91.

[0069] The particularity of the connecting member 99 according to the invention is that it is formed by the assembly of at least three elements 100, 110, 120 comprising:

[0070] - a first upstream element 100 capable of forming a mechanical connection with the part stator 96 of the transfer device 94 and to form a fluid connection between the or each inlet port 98a and the corresponding pipe 95,

[0071] - a second downstream element 120 capable of forming a mechanical connection with the carrier- satellites 38, and

[0072] - at least one third intermediate element 110 capable of forming a connection mechanical between the first and second elements 100, 120 so as to mutually block the first and second elements 100, 120 in rotation around the X axis and to mutually allow degrees of freedom in translation and in rotation with respect to the other two axes Y, Z or even also in translation along the X axis.

[0073] Figures 4 and following illustrate several embodiments of this connecting member 99.

[0074] In these different embodiments, the first upstream element 100 comprises a part 101 centered on the axis X and comprising at least one internal channel for connecting the or each pipe 95 to the inlet port(s) 98a of the transfer device 94. The channel comprises at least one inlet port 98c connected to each pipe 95 and at least one outlet port 98d connected to the aforementioned inlet port 98a of the transfer device 94.

[0075] The ports 98c are here located at the external periphery of the part 101. There are two or three of them here. These ports 98ca can open radially outwards. The pipes 95 extend from these ports 98c through the reducer 34 and can be bent into an L as illustrated in [Fig.3].

[0076] The part 101 comprises an upstream part which comprises the outlet ports 98d which open axially upstream and are capable of cooperating by male-female interlocking with complementary means of the stator part 96 of the transfer device 94. To facilitate this interlocking which is generally carried out blindly, the upstream part of the part 101 may further comprise centering elements 103, such as orifices, intended to cooperate with complementary centering elements 108, such as axial fingers, carried by the stator part 96 of the transfer device 94. transfer 94.

[0077] Preferably, the centering elements 108 in the form of axial fingers are conical or have conical ends. This makes it possible to take up the misalignments caused by the degrees of freedom. These centering elements preferably have limited deflections to allow assembly.

[0078] It is generally the downstream part of the part 101 which is connected to the third element.

[0079] In the various embodiments, the second downstream element 120 comprises a flange 121 or fixing lugs to the planet carrier 38, for example by means of screws or the like. The second element 120 is also preferably centered on the X axis.

[0080] Figures 4 to 9 illustrate a first embodiment in which the third element 110 is a fluted tubular sleeve which extends along the axis X and which comprises an upstream end comprising male flutes 112 engaged in female flutes 113 of the first element 100, and a downstream end comprising male flutes 114 engaged in female flutes 115 of the second element 120.

[0081] Alternatively, the fluted tubular sleeve could include ends with female flutes engaged in or over male flutes.

[0082] The male grooves 112, 114 of the two ends of the sleeve preferably have curved profiles, as illustrated in [Fig.9], and are capable of swiveling in the corresponding female grooves 113, 115.

[0083] The first element 100 comprises an internal annular groove 102 for receiving a first stop ring 104 which surrounds the upstream end of the sleeve. This first stop ring 104 is free to move axially around the sleeve in the direction of the second element 120 and is capable of coming into axial abutment against a stop 106 of the sleeve when it moves axially around the sleeve in the direction of the first element 100 ([Fig.9]).

[0084] The second element 120 comprises an internal annular groove 122 for receiving a second stop ring 124 which surrounds the downstream end of the sleeve. This second stop ring 124 is free to move axially around the sleeve in the direction of the first element 100 and is capable of coming into axial abutment against a stop 126 of the sleeve when it moves axially around the sleeve in the direction of the second element 120.

[0085] Alternatively, particularly when the grooves are reversed, the first and second elements could comprise external annular grooves for receiving the stop rings.

[0086] The member 99 can be mounted in the following manner, before its mounting on the planet carrier 38 of the reducer and before its connection to the transfer device 94. The rings stop rings 104, 124 are previously mounted around the sleeve. The grooves 112 of the sleeve are engaged in the grooves 113 then the stop ring 104 is mounted in its groove 102 to block the sleeve with respect to the first element 100. The grooves 114 of the sleeve are engaged in the grooves 115. The stop ring 124 is then mounted in its groove 122 to block the sleeve with respect to the second element 120. The member 99 can be fixed to the reducer 34 and the transfer device 94 can be mounted blindly from upstream on the first element 100.

[0087] Figures 10 and 11 illustrate a second embodiment in which at least three third elements 110 are distributed around the X axis and each provide the mechanical connection between the first and second elements 100, 120.

[0088] Each of these third elements 110 comprises a flexible member formed from a single piece.

[0089] In the example shown, each of the third elements 110 comprises three parallel walls, respectively upstream 130, intermediate 131 and downstream 132, spaced from each other.

[0090] The upstream 130 and intermediate 131 walls are connected together by two first side walls 133 located on two opposite sides of each of these walls 130, 131.

[0091] The intermediate 131 and downstream 132 walls are connected together by two second side walls 134 located on two opposite sides of each of these walls 131, 132.

[0092] The first and second side walls 133, 134 are elastically deformable and have, for example, a general C or U shape.

[0093] As in the example shown, the sides of the intermediate wall 131 which are connected by the first side walls 133 to the upstream wall 130 are preferably different from the sides of this intermediate wall 131 which are connected by the second side walls 134 to the downstream wall 132.

[0094] In the case where each of these walls 130, 131, 132 had a substantially parallelepiped shape, two opposite edges of the intermediate wall 131 would be connected by the first side walls 133 to the upstream wall 130, and the two other opposite edges of this intermediate wall 131 would be connected by the second side walls 134 to the downstream wall 132.

[0095] Advantageously, the upstream wall 131 comprises a central orifice 135 crossed by a first pin 136 which is carried by the first element 100 and which extends parallel to the axis X.

[0096] This first pin 136 is capable of sliding axially in the orifice 135 and carries a stop ring 137 configured to limit an axial displacement stroke of the pin 136 in the orifice 135 in the direction of the transfer device 94.

[0097] The downstream wall 133 comprises a central orifice 138 crossed by a second pin 139 which is carried by the second element 120 and which extends parallel to the axis X.

[0098] This second pin 139 is capable of sliding axially in the orifice 138 and carries a stop ring 140 configured to limit an axial displacement stroke of the pin 139 in the orifice 138 in the direction of the reducer 34.

[0099] Each pin 136, 139 preferably passes through a cylindrical ring 141 engaged in the orifice 135, 138 of the corresponding wall 131, 133 and capable of coming into axial abutment against the stop ring 137, 140 carried by this pin.

[0100] The member 99 can be mounted in the following manner, before its mounting on the planet carrier 38 of the reducer and before its connection to the transfer device 94. The third elements 110 are each assembled on the second element 120, by engaging the pins 139 of the second element 120 in the orifices 138 or in the rings 141 of the elements 110. The stop rings 140 are then mounted in the grooves of the pins 139 to axially block the elements 110 on the pins 139. The third elements 110 are then each assembled on the first element, by engaging the pins 136 of the first element 100 in the orifices 135 or in the rings 141 of the elements 110. The stop rings 137 are then mounted in the grooves of the pins 136 to axially block the elements 110 on the pins 136. The member 99 can be fixed to the reducer 34 and the transfer device 94 can be mounted blindly from upstream on the first element 100.

[0101] Figures 12 and 13 illustrate a third embodiment in which the third element 110 comprises a rigid body 150 extending along the axis X and carrying an elastically deformable annular block 152, 154 at each of its axial ends.

[0102] The upstream end of the body 150 is surrounded by a first block 152 and is rotationally integral with this first block 152 which is fixed to the first element 100.

[0103] The downstream end of the body 150 is surrounded by a second block 154 and is rotationally integral with this second block 154 which is fixed to the second element 120.

[0104] As in the example shown, each of the blocks 152, 154 can be secured to the body 150 by radial screws 156 passing through the block 152, 154 and screwed into the body 150.

[0105] Alternatively, the blocks could be secured to the body by axial screws.

[0106] The first block 152 is fixed to the first element 100 by at least one screw 158 or a stud parallel to the X axis.

[0107] The second block 154 is fixed to the second element 120 by at least one pin 160 which is carried by the second element 120 and which is parallel to the X axis.

[0108] The or each pin 160 is engaged in a housing 162 complementary to the second block 154 and capable of sliding axially in this housing 162.

[0109] The member 99 can be mounted in the following manner, before its mounting on the planet carrier 38 of the reducer and before its connection to the transfer device 94. The blocks 152, 154 are previously mounted and fixed on the body 150. The or each pin 160 is mounted on the second element 120 and the or each screw or stud 158 is mounted on the first element 100. The third elements 110 are then assembled to the first and second elements 100, 120. The member 99 can be fixed to the reducer 34 and the transfer device 94 can be blindly mounted from upstream on the first element 100.

[0110] Figures 14 and 15 illustrate a fourth embodiment in which the third element comprises a helical spring 170 extending along the axis X.

[0111] The spring 170 comprises a downstream end which is engaged and fixed on a cylindrical stud 172 of the second element 120, and an upstream end which is engaged in a cylindrical ring 174.

[0112] The cylindrical ring 174 is engaged in a cavity 176 of the first element 100 and capable of sliding axially in this cavity 176.

[0113] The spring 170 is preferably axially constrained between the ring 174 and the second element 120.

[0114] The second element 120 may comprise a first clamping system 178, and the ring 174 may comprise a second clamping system 179, these first and second clamping systems 178, 179 being configured to be fixed to a tool for stressing the spring 170. This tool is schematically represented by dotted lines in [Fig. 15].

[0115] In the case where the intermediate element is movable in translation, it could be pressed axially in one direction or the other by the force of the spring.

[0116] The member 99 can be mounted in the following manner, before its mounting on the planet carrier 38 of the reducer and before its connection to the transfer device 94. The spring 170 is engaged on the stud 172 of the second element 120. The aforementioned tooling is mounted around the spring 170 and can be in the form of two half-shells capable of being fixed to the second element 120. The ring 174 is attached to the spring 170 and further fixed to the tooling. The tooling is interposed axially between the ring 174 and the second element 120 and has an axial dimension along the axis which is a function of the desired prestress level. The clamping of this tooling between the ring 174 and the second element 120 therefore makes it possible to achieve this stress level. The ring 174 is then engaged in the cavity 176 of the first element 100 and the tooling can be removed, preferably after the member 99 is fixed to the reducer 34 and connected to the transfer device 94.

[0117] Figures 16 and 17 illustrate a fifth embodiment in which the third element 110 comprises a gimbal system 180 extending along the X axis.

[0118] The gimbal system 180 comprises a body 182 in two parts 184, 186.

[0119] One of the parts 184 of the body 182 is connected by a first cardan joint 188 to the first element 100.

[0120] The other of the parts 186 of the body 182 is connected by a second cardan connection 190 to the second element 120.

[0121] The two parts 184, 186 of the body 182 are engaged and able to slide into one another.

[0122] One of the body portions 184, 186 may comprise internal grooves 192 engaged in external grooves 194 of the other body portion.

[0123] One of the parts 184, 186 of the body may carry a stop ring 196 limiting the axial displacement travel of the parts 184, 186 relative to each other.

[0124] The connecting member 99 according to the invention makes it possible to supply oil to the transfer device 94 while adapting to the movements of the reducer 34. The different embodiments described above make it possible to ensure this dual function while also resolving the problems of the prior art thanks to the five degrees of freedom conferred by this connecting member.

Claims

Claims

1. Turbomachine module, this module having a longitudinal axis (X) and comprising: - a propeller (3) intended to be driven in rotation around the axis (X) by a shaft (32) and comprising a plurality of blades (30) with variable pitch, - a speed reducer (34) comprising a sun gear (36) rotatable about the axis (X), a crown gear (39) rotatable about the axis (X) and the sun gear (36), and satellites mounted between the sun gear (36) and the crown gear (39) and meshed with the sun gear (36) and the crown gear (39), the satellites (37) being carried by a planet carrier (38) which is fixed in rotation about the axis (X), the crown gear (39) being connected to said shaft (32), - a pitch change system (50) for the blades (30) arranged axially upstream of the speed reducer (34) and comprising a hydraulic actuator (52) which extends along the axis (X) and which is rotationally integral with the shaft (32), - a fluid transfer device (94) arranged axially upstream of the speed reducer (34) and configured to supply fluid to the hydraulic actuator (52) for the purpose of changing the pitch of the blades (30), this transfer device (94) being centered on the axis (X) and comprising a stator part (96) at least partly engaged in a rotor part (97) integral in rotation with the hydraulic actuator (52), the fluid transfer device (94) comprising an internal fluid circuit (98) comprising at least one fluid inlet port (98a) carried by the stator part (96) and at least one fluid outlet port (98b) carried by the rotor part (97), and - a member (99) for mechanically connecting the stator part (96) of the transfer device (94) to the planet carrier (38), and for fluidically connecting said at least one fluid inlet port (98a) to fluid pipes (95) configured to be connected to a fluid reservoir (91), characterized in that the mechanical connecting member (99) comprises a assembly of at least three elements comprising: - a first upstream element (100) capable of forming a mechanical connection with the stator part (96) of the transfer device (94) and of forming a fluid connection between said at least one inlet port (98a) and the pipes (95), - a second downstream element (120) capable of forming a mechanical connection with the planet carrier (38), and - at least one third intermediate element (110) capable of forming a mechanical connection between the first and second elements (100, 120) so as to mutually block the first and second elements (100, 120) in rotation around the axis (X) and to mutually allow degrees of freedom in translation and in rotation with respect to the other two axes (Y, Z) perpendicular to the longitudinal axis (X) in a three-dimensional reference frame (X, Y, Z), or even also in translation along the longitudinal axis (X).

2. Turbomachine module according to claim 1, characterized in that said third element (110) is a grooved tubular sleeve which extends along the axis (X) and which comprises an upstream end comprising male (112) or female grooves, respectively, engaged in female (113) or male grooves, respectively, of the first element (100), and a downstream end comprising male (114) or female grooves, respectively, engaged in female (115) or male grooves, respectively, of the second element (120).

3. Turbomachine module according to claim 2, characterized in that the male splines (112, 114) have curved profiles and are capable of swiveling in the corresponding female splines (113, 115).

4. A turbomachine module according to claim 2 or 3, characterized in that the first element (100) comprises an internal annular groove (102) for receiving a first stop ring (104) which surrounds the upstream end of the sleeve, this first stop ring (104) being free to move axially around the sleeve in the direction of the second element (120) and being able to come into axial abutment against a stop (106) of the sleeve when it moves axially around the sleeve in the direction of the first element (100), and the second element (120) comprises an internal annular groove (122) for receiving a second stop ring (124) which surrounds the downstream end of the sleeve, this second stop ring (124) being free to move axially around of the sleeve towards the first element (100) and being able to come into axial abutment against a stop (126) of the sleeve when it moves axially around the sleeve towards the second element (120).

5. Turbomachine module according to claim 1, characterized in that at least three third elements (110) are distributed around the axis (X) and each provide said mechanical connection between the first and second elements (100, 110).

6. Turbomachine module according to claim 5, characterized in that each of the third elements (110) comprises a flexible member formed from a single piece.

7. Turbomachine module according to claim 5 or 6, characterized in that each of the third elements (110) comprises three parallel walls, respectively upstream (130), intermediate (131) and downstream (132), spaced from each other, the upstream and intermediate walls (130, 131) being connected together by two first side walls (133) located on two opposite sides of each of these walls (130, 131), and the intermediate and downstream walls (131, 132) being connected together by two second side walls (134) located on two opposite sides of each of these walls (131, 132), the first and second side walls (133, 134) being elastically deformable.

8. Turbomachine module according to claim 7, characterized in that the sides of the intermediate wall (131) which are connected by the first side walls (133) to the upstream wall (130), are different from the sides of this intermediate wall (131) which are connected by the second side walls (134) to the downstream wall (132).

9. Turbomachine module according to claim 7 or 8, characterized in that the upstream wall (130) comprises a central orifice (135) crossed by a first pin (136) which is carried by the first element (100) and which extends parallel to the axis (X), the first pin (136) being able to slide axially in the orifice (135) and carrying a stop ring (137) configured to limit an axial displacement stroke of the pin (136) in the orifice (135) in the direction of the transfer device (94), and the downstream wall (132) comprises a central orifice (138) crossed by a second pin (139) which is carried by the second element (120) and which extends parallel to the axis (X), the second pin (139) being able to slide axially in the orifice (138) and carrying a stop ring (140) configured to limit an axial displacement stroke of the pin (139) in the orifice (138) towards the reducer (34).

10. Turbomachine module according to claim 9, characterized in that each pin (136, 139) passes through a cylindrical ring (141) engaged in the orifice (135, 138) of the corresponding wall (131, 133) and capable of coming into axial abutment against the stop ring (137, 140) carried by this pin (136, 139).

11. Turbomachine module according to claim 1, characterized in that said third element (110) comprises a rigid body (150) extending along the axis (X) and carrying an elastically deformable annular block (152, 154) at each of its axial ends, the upstream end of the body (150) being surrounded by a first block (152) and integral in rotation with this first block (152) which is fixed to the first element (100), and the downstream end of the body (150) being surrounded by a second block (154) and integral in rotation with this second block (154) which is fixed to the second element (120).

12. Turbomachine module according to claim 11, characterized in that each of the blocks (152, 154) is secured to the body (150) by radial screws (156) passing through the block and screwed into the body.

13. Turbomachine module according to claim 11 or 12, characterized in that the first block (152) is fixed to the first element (100) by at least one screw (158) or a stud parallel to the axis (X), and the second block (154) is fixed to the second element (120) by at least one pin (160) which is carried by the second element (120) and which is parallel to the axis (X), said at least one pin (160) being engaged in a housing (162) complementary to the second block (154) and capable of sliding axially in this housing (162).

14. Turbomachine module according to claim 1, characterized in that said third element (110) comprises a helical spring (170) extending along the axis (X).

15. Module according to claim 14, characterized in that the spring (170) comprises a downstream end which is engaged and fixed on a cylindrical stud (172) of the second element (120), and an upstream end which is engaged in a cylindrical ring (174), this cylindrical ring (174) being engaged in a cavity (176) of the first element (100) and able to slide axially in this cavity (176).

16. Turbomachine module according to claim 15, characterized in that the spring (170) is axially stressed between the ring (174) and the second element (120).

17. Turbomachine module according to claim 15 or 16, characterized in that the second element (120) comprises a first clamping system (178), and the ring (174) comprises a second clamping system (179), these first and second clamping systems (178, 179) being configured to be fixed to a spring stressing tool (170).

18. Turbomachine module according to claim 1, characterized in that said third element (110) comprises a gimbal system (180) extending along the axis (X).

19. Turbomachine module according to claim 18, characterized in that said gimbal system (180) comprises a body (182) in two parts (184, 186), one of the parts (184) of the body (182) being connected by a first gimbal connection (188) to the first element (100), and the other of the parts (186) of the body (182) being connected by a second gimbal connection (190) to the second element (120), the two parts (184, 186) of the body (182) being engaged and able to slide one inside the other.

20. Turbomachine module according to claim 19, characterized in that one of the parts (184, 186) of the body (182) comprises internal grooves (192) engaged in external grooves (194) of the other part of the body, one of the parts of the body carrying a stop ring (196) limiting the axial displacement travel of the parts (184, 186) relative to each other.

21. Aircraft turbomachine, comprising at least one turbomachine module according to any one of the preceding claims.