Module for aircraft turbine engine

Abstract

The invention relates to a module (3) having a longitudinal axis (X), comprising a hydraulic actuator (46) and a pump (54) for supplying fluid to the hydraulic actuator (46), the pump comprising an axial piston (54c) intended to be movable so as to rotate about the longitudinal axis (X) and configured to deliver fluid to the hydraulic actuator (46), and a connecting disc (54g) for connecting the axial piston (54c) to the hydraulic actuator (46). A connecting disc (54g) connected to the axial piston (54c) and engaging with an annular main disc (54e) centered on the longitudinal axis (X), intended not to rotate about the longitudinal axis (X) and inclined relative to the longitudinal axis (X), the connecting disc (54g) being arranged between the main disc (54e) and the axial piston (54c), the axial piston (54c) being movable so as to rotate in a direction (D) parallel to the longitudinal axis (X), inclination of the main disc (54e) causes movement of the axial piston (54c) in the direction (D).

Description

Technical Field

[0001] The present invention relates to the field of modules for aircraft turbine engines and more particularly to a module, such as a fan module or a propeller module, comprising a hub capable of rotational movement and variable pitch blades carried by the hub. Background Art

[0002] An aircraft turbine engine generally comprises a module extending around a longitudinal axis and having a hub capable of rotating about the longitudinal axis, on which blades are mounted. The module is generally connected to a gas generator. The gas generator comprises, from upstream to downstream, for example, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and a gas discharge nozzle. The rotor of the high-pressure compressor is connected to the rotor of the high-pressure turbine via a high-pressure shaft, and the rotor of the low-pressure compressor is connected to the rotor of the low-pressure turbine via a low-pressure shaft. The low-pressure shaft is also connected to a drive shaft of the hub of the module to drive the hub to rotate.

[0003] The module is, for example, a fan or a propeller. In the case of a fan, the blades are surrounded by an outer shell, which is attached to the nacelle of the aircraft. In the case of a propeller, the fan blades are mounted outside the nacelle, so that the fan blades are not surrounded by the outer shell.

[0004] As is known, in order to optimize the operation of the module and to ensure its operability according to the flight phase of the aircraft, in particular by maintaining a sufficient pumping margin, the orientation of the blades is changed during the flight of the aircraft. To this end, the blades are movable about a pitch axis extending perpendicularly to the longitudinal axis. The blades are called variable pitch blades. For example, the variable pitch blades can occupy a reverse thrust position, in which they generate reverse thrust to help slow down the aircraft, and a feathering position, in which, in the event of a malfunction or damage, they limit their drag.

[0005] In order to drive the blades in rotation about the pitch axis of the blades, the modules of the turbine engines generally include means for changing the pitch of the blades. Document FR-A1-3 087 232 describes a turbine engine comprising a fan module having a movable hub that can move about a longitudinal axis and on which variable pitch blades are mounted. The module comprises a blade pitch changing device comprising a hydraulic actuator connected to the blades and a supply pump for supplying fluid to the hydraulic actuator. According to the document, the pump is rotationally fixed to the hub.

[0006] In order to operate the pump and regulate the flow rate of the pump, the module also comprises an electric motor rotationally fixed to the pump.

[0007] This configuration is not entirely satisfactory. Since the electric motor is rotating and the energy source that powers the motor is in a stationary reference frame, it is necessary to provide energy transfer from the stationary reference frame to the rotating reference frame. To this end, the prior art module also includes a rotating power transformer for supplying electrical energy to the motor from an electrical energy source located in the stationary reference frame of the turbine engine.

[0008] However, the overall size of the turbine engine module makes it difficult to add a power transformer. Adding a transformer means increasing the size of the module. The weight and cost of the transformer also increase significantly.

[0009] Therefore, there is a need to provide a turbine engine module for an aircraft, the turbine engine module including a hub carrying variable pitch blades, the turbine engine module being compact, lightweight and low cost. Summary of the invention

[0010] To this end, the invention proposes a module for an aircraft turbine engine, the module comprising a longitudinal axis and comprising:

[0011] a hub, the hub being centered on the longitudinal axis and the hub being configured for rotational movement about the longitudinal axis,

[0012] - blades carried by the hub, each of the blades being movable about a pitch axis extending radially with respect to the longitudinal axis, and

[0013] - a device for varying the pitch of a blade about its pitch axis, the device comprising:

[0014] a hydraulic actuator configured for rotational movement about a longitudinal axis and configured to drive the blade about a pitch axis of the blade,

[0015] A supply pump for supplying fluid to a hydraulic actuator, the supply pump comprising: an axial piston configured to perform rotational movement around a longitudinal axis and configured to deliver fluid to the hydraulic actuator; and a connecting plate connected to the axial piston and cooperating with an annular main plate centered on the longitudinal axis, the main plate being configured not to rotate around the longitudinal axis and being able to tilt relative to the longitudinal axis, the connecting plate being arranged between the main plate and the axial piston, the axial piston being able to move translationally in a direction parallel to the longitudinal axis, the tilting of the main plate causing the axial piston to move in this direction, and

[0016] An auxiliary actuator is connected to the connecting disk and is configured to drive the connecting disk to rotate about the longitudinal axis.

[0017] According to the invention, the module comprises a pump having an axial piston connected to the connecting disc and driven in translation by the main disc.

[0018] The stroke of the piston varies according to the inclination of the main disc, thereby enabling the pump flow to be varied. According to the pump flow, the hydraulic actuator can change the pitch of the blades to the desired angle.

[0019] Since the pump has a variable flow rate, it is no longer necessary to rotate the electric motor to adjust the flow rate of the pump. This makes it possible to eliminate the need for a rotating power transformer to supply electrical energy to the electric motor.

[0020] The module according to the invention is therefore more compact, lighter and consumes less energy.

[0021] Furthermore, according to the invention, the main disc does not rotate. This makes it possible to simplify the configuration of the pump and the module.

[0022] Furthermore, according to the invention, the axial piston rotates. This makes it possible to transfer fluid between the pump and the hydraulic actuator without rotating the hydraulic transfer device, thereby limiting fluid leakage.

[0023] The present invention may include one or more of the following features taken alone or in combination with each other:

[0024] - the pump comprises a shroud mounted around the main disc and the connecting disc and the shroud is configured not to rotate about the longitudinal axis,

[0025] - the main platter can be tilted at an inclination angle α between -45° and 45°, an angle α of 0° corresponding to a position of the main platter perpendicular to the longitudinal axis,

[0026] - the device further comprises an actuator connected to the main disc and configured to tilt the main disc relative to the longitudinal axis,

[0027] - the connecting disc is configured to be capable of rotational movement about a longitudinal axis and to plan against the main disc,

[0028] - the axial piston is connected to the connecting disc via a ball joint,

[0029] - the pump comprises a transmission shaft centered on a longitudinal axis, the transmission shaft being rotationally fixed to the connecting disc and the main disc being mounted around the transmission shaft,

[0030] a drive shaft is rotationally fixed to the hub and is configured to drive the transmission shaft in rotation about the longitudinal axis,

[0031] - the electronic control circuit is configured to send instructions to the auxiliary actuator to drive the connection disk to rotate about the longitudinal axis,

[0032] - the auxiliary actuator is connected to the connection plate by a spline connection or a universal joint connection or an Oldham joint connection or a snap-in connection,

[0033] the hydraulic actuator is a cylinder rotationally fixed to the drive shaft, the hydraulic actuator comprising a box, a rod arranged in the box, and a first chamber and a second chamber defined in the box, the first chamber and the second chamber being connected to a pump, the rod or the box being movable in translation and connected to the blade,

[0034] The box or rod is rotationally fixed to the drive shaft.

[0035] The invention also relates to a turbine engine for an aircraft, comprising a module according to any one of the preceding characteristics. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Other features and advantages will emerge from the following description of non-limiting embodiments of the invention with reference to the accompanying drawings, in which:

[0037] Figure 1 is a schematic diagram of an aircraft turbine engine shown in axial section;

[0038] Figure 2 is a schematic axial cross-sectional view of a module according to the present invention;

[0039] Figure 3a is a functional schematic diagram of modules according to an example of an embodiment of the present invention;

[0040] Figure 3b is a functional schematic diagram of a module according to another embodiment of the present invention;

[0041] Figure 4a is a schematic diagram of a disk of a pump equipped with a module, the disk being in a first position;

[0042] Figure 4b is a schematic diagram of a disk of a pump equipped with a module, the disk being in a second position;

[0043] Figure 5 is a schematic diagram of a module according to a specific embodiment of the present invention;

[0044] Figure 6 is a schematic diagram of a module according to a specific embodiment of the present invention. DETAILED DESCRIPTION

[0045] The aircraft comprises a fuselage and at least two wings, at least two wings extending on both sides of the fuselage along the fuselage axis. At least one turbine engine 1 is installed under each wing. The turbine engine 1 can be a turbojet engine, for example, a turbine engine equipped with a ducted fan, the ducted fan is equipped with variable pitch blades, and the ducted fan is called a variable pitch fan (Variable Pitch Fan, VPF). Alternatively, the turbine engine 1 can be a turboprop engine, for example, a turbine engine equipped with an unducted propeller (Unducted Single Fan (USF) or Unducted Dual Fan (UDF)). Of course, the present invention is applicable to other types of turbine engines.

[0046] In the present invention, the terms "axial" and "axially" are defined relative to the longitudinal axis X of the turbine engine 1 or of the module 3 of the turbine engine 1. The terms "upstream" and "downstream" are defined relative to the flow of gases in the turbine engine 1 and are here defined along the longitudinal axis X (even in the Figure 1 Similarly, the terms "radial" and "radially" are defined relative to a radial axis Z that is perpendicular to the longitudinal axis X. The terms "inner", "inner", "outer" and "outer" are defined relative to the distance along the radial axis Z from the longitudinal axis X.

[0047] Figure 1 An example of a turbine engine 1 is shown. The turbine engine 1 comprises a gas generator 2 and a module 3 according to the invention.

[0048] The gas generator 2 includes 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 from upstream to downstream. The rotor of the low-pressure compressor 4 and the rotor of the low-pressure turbine 8 are mechanically connected by a low-pressure shaft 9 to form a low-pressure body. The rotor of the high-pressure compressor 5 and the rotor of the high-pressure turbine 7 are mechanically connected by a high-pressure shaft 10 to form a high-pressure body. The high-pressure shaft 10 extends radially at least partially outside the low-pressure shaft 9. The low-pressure shaft 9 and the high-pressure shaft 10 are coaxial. The high-pressure body rotates around the longitudinal axis X guided by a first rolling bearing 11 upstream and by a second rolling bearing 12 downstream. The first bearing 11 is radially mounted between the compressor inter-casing 13 and the upstream end of the high-pressure shaft 10. The compressor inter-casing 13 is axially arranged between the low-pressure compressor 4 and the high-pressure compressor 5. The second bearing 12 is mounted between the turbine inter-casing 14 and the downstream end of the high-pressure shaft 10. The turbine inter-casing 14 is axially arranged between the low-pressure turbine 8 and the high-pressure turbine 7. The low-pressure body is guided to rotate around the longitudinal axis X by a third rolling bearing 15 and a fourth rolling bearing 16. For example, the fourth bearing 16 is a double bearing. The fourth bearing 16 is installed between the exhaust casing 17 and the 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 installed between the inlet casing 18 and the upstream end of the low-pressure shaft 9. The inlet casing 18 is located upstream of the low-pressure compressor 4. More specifically, the inlet casing 18 is arranged axially between the module 3 and the low-pressure compressor 4.

[0049] exist Figure 1 In the example shown, the module 3 is mounted upstream of the gas generator 2. Advantageously, according to this example, stator vanes 20 are arranged downstream of the module 3. The stator vanes 20 comprise, for example, vanes 200, which are mounted on the inlet casing 18. These vanes 200 are called outlet guide vanes (OGV). The stator vanes 20 make it possible to rectify the flow downstream of the module 3 in order to optimize the operation of the turbine engine 1.

[0050] In another embodiment (not shown), the module 3 is installed downstream of the gas generator 2 .

[0051] Furthermore, the module 3 according to the invention comprises blades 30 .

[0052] exist Figure 1 In the example shown, the blades 30 are surrounded by an outer casing 19. A nacelle (not shown) is attached to the outer casing 19. In this example, the module 3 is a fan module.

[0053] In another example, not shown, the module 3 is a propeller module. The blades 30 are not surrounded by an outer casing, in this example the blades 30 are arranged around the nacelle.

[0054] Reference Figure 2, the module 3 according to the invention further comprises a hub 43. The hub 43 is annular and centered on the longitudinal axis X. The hub comprises an internal space 310. The hub 43 is fixed to a cone centered on the longitudinal axis X. The cone is arranged upstream of the hub 43. The cone forms an air inlet nozzle for the turbine engine 1. The hub 43 is connected to the cone, for example, by an attachment arm 43a, which extends radially relative to the longitudinal axis X. For example, the attachment arm 43a is connected to the cone and the hub 43 by an assembly 43b of screws and nuts. The hub 43 comprises inner receptacles, which are evenly distributed around the longitudinal axis X.

[0055] The blades 30 are carried by the hub 43 and are evenly distributed on the hub 43. The blades extend radially from the hub 43. The blades 30 are driven in rotation about the longitudinal axis X. Each blade 30 comprises a root 41 and a blade 40 extending radially outwards from the root 41.

[0056] The root 41 comprises, for example, a tenon which is mounted in a sleeve. The root 41 is pivotally mounted in the inner housing of the hub 43 along the pitch axis C. Advantageously, each inner housing is mounted with a root 41. The sleeve is centered on the pitch axis C and is housed in the inner housing of the hub 43.

[0057] The pitch axis C is parallel to the radial axis Z and therefore extends radially with respect to the longitudinal axis X. The root 41 is pivotally mounted in the hub 43, in particular via a sleeve, by means of two guide bearings 44 mounted in each inner housing and superposed along the radial axis Z. These bearings 44 are preferably, but not exclusively, ball bearings.

[0058] The hub 43 can perform a rotational movement around the longitudinal axis X. In order to drive the hub 43 to rotate around the longitudinal axis X, thereby driving the blade 30 to rotate around the longitudinal axis, the module 3 includes a drive shaft 32. The drive shaft 32 is at least partially arranged in the internal space 310. The internal space is centered on the longitudinal axis X. The drive shaft 32 is guided and rotated in the internal space 310 by the first guide bearing 32a and the second guide bearing 32b. For example, the first guide bearing 32a is a rolling bearing. For example, the second guide bearing 32b is a rolling bearing. The first guide bearing 32a is arranged downstream of the second guide bearing 32b. The first guide bearing 32a includes a ball 320a, which is arranged between an outer ring 321a and an inner ring 322a. The second guide bearing 32b includes a roller 320b, which is arranged, for example, between an outer ring 321a and an inner ring 322a. The inner ring 322a is fixed to the drive shaft 32, and the outer ring 321a is carried by the bearing support 34. The first guide bearing 32a and the second guide bearing 32b may share the same outer ring and inner ring, or the first guide bearing and the second guide bearing may be formed by separate rings. The bearing support 34 is fixed. The bearing support extends radially between an end flange 34a connected to the inlet housing 18 and a base 34b cooperating with the outer ring 321a.

[0059] The drive shaft 32 comprises an upstream end to which a trunnion 53 is attached. The trunnion 53 extends radially outwards. The trunnion 53 is connected to the hub 43, for example by means of a first flange 52, to drive the hub in rotation about the longitudinal axis X.

[0060] For example, the drive shaft 32 is driven in rotation by the low-pressure shaft 9. In order to reduce the rotation speed of the drive shaft 32 relative to the low-pressure shaft 9, the module 3 advantageously comprises a mechanical reducer 33 connecting the low-pressure shaft 9 to the drive shaft 32.

[0061] Reference Figure 1 , the reducer 33 is arranged in a lubricating enclosure 35. The lubricating enclosure 35 is axially arranged, for example, inside the inlet housing 18 between the third bearing 15 and the second guide bearing 32b.

[0062] The reducer 33 is, for example, a reducer 33 having a planetary gear train or a pinion gear train. The reducer 33 includes: an inner planetary gear (also called a sun gear) configured to cooperate with the low-pressure shaft 9; an outer ring gear rotationally fixed to the drive shaft 32 or connected to a fixed structure of the turbine engine 1 (such as the inlet housing 18); and a planet carrier that does not rotate (for example, fixed to the inlet housing 18) or rotationally fixed to the drive shaft 32. The reducer 33 also includes planetary gears meshing with the sun gear and the outer ring gear.

[0063] Each blade 30 can perform a rotational movement around a pitch axis C. To this end, according to the invention, the module 3 comprises a device 45 for changing the pitch of the blade 30 around the pitch axis C of the blade. Advantageously, the device 45 is at least partially arranged in the internal space 310 of the hub 43. This makes it possible to facilitate the maintenance of the device 45, because the device is easily accessible. The device 45 is arranged upstream of the reducer 33. The device 45 comprises a hydraulic actuator 46, which can perform a rotational movement around the longitudinal axis X and is configured to drive the blade 30 around the pitch axis C of the blade 30. The hydraulic actuator 46 is, for example, a hydraulic cylinder. For example, the hydraulic actuator is arranged in the internal space 310. The hydraulic actuator 46 is rotationally fixed to the drive shaft 32. The drive shaft 32, for example, has a shell 50, which extends radially inwardly from the drive shaft 32 and is connected to the hydraulic actuator 46.

[0064] The hydraulic actuator 46 comprises a box 48 and a rod 49 . The box 48 is cylindrical, centred on the longitudinal axis X. This configuration makes it possible to limit the overall dimensions required for the hydraulic actuator 46 in the hub 43 axially and radially. The box 48 extends radially around the rod 49 .

[0065] The rod 49 extends axially between a first end 49a and a second end 49b.

[0066] The hydraulic actuator 46 further comprises a first chamber 46a and a second chamber 46b. The first chamber 46a and the second chamber 46b are defined inside the box body 48 and are axially delimited by an annular wall 46c arranged in the box body 48. The annular wall 46c is fixed to the second end 49b of the rod 49, for example.

[0067] exist Figure 3a In the first example shown, the rod 49 is movable in translation in the cassette 48. The rod 49 is movable in translation in the cassette 48 along the longitudinal axis X. In this example, the cassette 48 is fixed to the drive shaft 32. A housing 50 is connected to the cassette 48.

[0068] according to Figure 3b In another example shown, the box 48 is movable in translation along the longitudinal axis X. In this example, the rod 49 is rotationally fixed to the drive shaft 32 . A housing 50 is connected to the rod 49 .

[0069] The rod 49 or the box 48 moves in translation under the pressure of the fluid circulating in each chamber 46a, 46b.

[0070] Advantageously, the device 45 comprises a connection mechanism 47 which connects the vane 30 to the hydraulic actuator 46, in particular to a rod 49 or to a box 48 of the hydraulic actuator 46. The connection mechanism 47 enables the translation movement of the hydraulic actuator 46 to be converted into a rotation movement of the vane 30. The connection mechanism 47 comprises an annular portion 47a, a connecting rod 47b and an eccentric 47c. The annular portion 47a is removably attached to the rod 49 (e.g. Figure 3a ) (e.g., removably attached to the second end 49b) or removably attached to the box body 48 (e.g., Figure 3b 47a). The annular portion 47a is also detachably connected to a connecting rod 47b. The connecting rod 47b cooperates with an eccentric 47c which is fixed to the blade 30, in particular to the root 41. The annular portion 47a thus enables the hydraulic actuator 46 to be removed, for example for maintenance operations, without affecting the blade 30, which remains attached to the connecting rod 47b by the eccentric 47c.

[0071] In order to drive the rod 49 or the box 48 in translation and thus drive the blade 30 about the pitch axis C of the blade 30 via the connection 47, the device 45 according to the invention also comprises a pump 54 for supplying fluid to the hydraulic actuator 46. For example, the pump 54 is located upstream of the reducer 33. The pump 54 is arranged inside the drive shaft 32.

[0072] The pump 54 is a reversible hydraulic pump with variable displacement and axial piston.

[0073] The pump 54 is connected to the first chamber 46 a and the second chamber 46 b of the hydraulic actuator 46 .

[0074] Reference Figure 3a and Figure 3b The pump 54 comprises a transmission shaft 54a around which a main disc 54e is mounted. The transmission shaft 54a is centered on the longitudinal axis X and is driven to rotate by the drive shaft 32, for example, by means of an accessory gearbox (AGB).

[0075] Advantageously, the pump 54 also comprises a shroud 54b mounted around the main disc 54e. The shroud 54b is for example annular and centred on the longitudinal axis X. The shroud 54b does not rotate relative to the longitudinal axis X. The shroud is connected to a fixed part of the module 3 or turbine engine 1, such as the inlet casing 18.

[0076] According to the invention, the pump 54 comprises an axial piston 54 c configured to deliver fluid to the hydraulic actuator 46. The axial piston 54 c is cylindrical or substantially cylindrical and has an axis of revolution parallel to the longitudinal axis X. The pump 54 comprises at least two axial pistons 54 c, which are advantageously evenly distributed around the longitudinal axis X. The axial pistons 54 c are rotationally fixed to the transmission shaft 54 ​​a.

[0077] According to the present invention, the axial piston 54c can be moved translationally in a direction parallel to the longitudinal axis X. Advantageously, the axial piston 54c can be moved translationally in two opposite directions along the direction D, for example, translationally from upstream to downstream and translationally from downstream to upstream. More specifically, each axial piston 54c can be moved translationally in a receiving chamber 54d for receiving a fluid, which is formed, for example, in a barrel 54f opposite to the main disc 54e. The number of receiving chambers 54d is as many as the number of axial pistons 54c. According to another example not shown, each receiving chamber 54d is arranged in a separate barrel, i.e., the number of barrels is as many as the number of receiving chambers 54d. Each receiving chamber 54d is rotationally fixed to the transmission shaft 54a. For example, the receiving chamber is rotationally fixed to the hydraulic actuator 46, in particular rotationally fixed to the box body 48.

[0078] The main disc 54e is annular and is centered on the longitudinal axis X. In particular, the main disc extends in a radial plane relative to the longitudinal axis X and therefore relative to the transmission shaft 54a. The main disc 54e does not rotate around the longitudinal axis X. Therefore, the main disc is not driven in rotation by the transmission shaft 54a.

[0079] According to the invention, the main platter 54e can be tilted relative to the longitudinal axis X. Thus, the main platter 54e is mounted such that it can rotate about an axis of rotation Y, which is perpendicular to the longitudinal axis X and to the radial axis Z. The main platter 54e is connected to the transmission shaft 54a, for example, by a pivot connection Y' having an axis parallel to the axis of rotation Y.

[0080] Advantageously, the main disc 54e may be tilted at an inclination angle α comprised between -45° and 45°, it being understood that an angle α of 0° corresponds to a position of the main disc 54e perpendicular to the longitudinal axis X.

[0081] Advantageously, the device 45 also includes an actuator 55, which is connected to the main disk 54e. The actuator 55 is configured to tilt the main disk 54e relative to the longitudinal axis X. The actuator 55 is, for example, an electric actuator (such as an electric cylinder) or a hydraulic actuator (such as a hydraulic cylinder). The actuator 55 is fixed to the main disk 54e, so that the actuator does not rotate around the longitudinal axis X. For example, the actuator is connected to the main disk 54e by a ball joint. This configuration makes it easier for the actuator 55 to tilt the main disk 54e without complicating the configuration of the module 3. The actuator 55 can also be connected to the module 3 or the casing of the turbine engine 1 by a ball joint.

[0082] According to the present invention, the pump 54 includes a connecting disc 54g, which is connected to the axial piston 54c and is arranged between the main disc 54e and the axial piston 54c. The connecting disc 54g is installed around the transmission shaft 54a. The connecting disc 54g and the main disc 54e are coaxial. Advantageously, the outer diameter of the main disc 54e is greater than the outer diameter of the connecting disc 54g. The main disc 54e cooperates with the connecting disc 54g. Advantageously, the connecting disc 54g is rotationally fixed to the main disc 54e around the rotation axis Y. Therefore, the connecting disc 54g can be tilted relative to the main disc 54e. Preferably, the connecting disc 54g can be tilted at the same angle as the tilt angle α of the main disc 54e. The connecting disc 54g, for example, is flatly abutted on the main disc 54e. Preferably, the connecting disc 54g can perform rotational movement around the longitudinal axis X. The connecting disc is rotationally fixed to the transmission shaft 54a.

[0083] The axial piston 54c is connected to the connecting plate 54g via a ball joint 54h.

[0084] When the axial piston 54c is connected to the connecting disk 54g, the inclination of the main disk 54e causes the inclination of the connecting disk 54g and the displacement of the axial piston 54c in the direction D. The stroke of the axial piston 54c in the receiving chamber 54d changes according to the inclination of the main disk 54e. This makes it possible to adjust the flow rate of the pump 54. Advantageously, when the inclination angle α of the main disk 54e is between 0° and 45° (e.g. Figure 4a ), the pump 54 is in the discharge mode, and when the inclination angle α of the main plate 54e is between -45° and 0° (as shown in FIG. Figure 4b As shown), the pump 54 is in the suction mode.

[0085] according to Figure 5In the preferred embodiment of the present invention shown, the device 45 also includes an auxiliary actuator 56, which is advantageously connected to the connection disk 54g by means of a spline connection (such as a short spline with circular teeth) or a universal joint connection or an Oldham joint connection or an embedded connection. The auxiliary actuator 56 is configured to drive the connection disk 54g to rotate. The auxiliary actuator 56 is, for example, an electric motor, which includes a rotor and a stator, the rotor being connected to the connection disk 54g, and the stator being coaxially arranged around the rotor. For example, the rotor is centered on the longitudinal axis X, and the stator is connected to the fixed structure of the turbine engine 1 or module 3.

[0086] This type of auxiliary actuator 56 enables the connection disk 54g to be driven in rotation about the longitudinal axis X when the drive shaft 32 is not functional. Typically, during maintenance phases of the turbine engine 1, the drive shaft 32 does not rotate and therefore the drive shaft 32 does not drive the connection disk 54g in rotation about the longitudinal axis X via the drive shaft 54a of the pump 54. During these phases, the connection disk 54g is driven in rotation by the auxiliary actuator 56. The auxiliary actuator 56 is coupled to the pump 54, for example by means of a gear coupled by a dog clutch, so that the auxiliary actuator 56 can drive the connection disk 54g only when the drive shaft 32 is not driven in rotation.

[0087] A spline connection, a universal joint connection, an Oldham joint connection or an embedded connection are preferred connection methods because they are compatible with the tilt angle of the connection plate 54g.

[0088] Reference Figure 6 Advantageously, in order to control and regulate the speed of the actuator 55 and possibly of the auxiliary actuator 56, the module 3 also comprises a control box 57 and an electronic control circuit 58. The control box 57 is supplied with electrical energy, for example, by an electrical energy source 59 situated in the turbine engine 1. The electronic control circuit 58 is situated, for example, in the turbine engine 1. The electronic control circuit 58 is, for example, a digital computer, such as a Full Authority Digital Electronic Computer (FADEC).

[0089] Advantageously, the module 3 comprises a sensor 60. The sensor 60 enables the measurement of information I1 sent to the electronic control circuit 58. The information I1 is, for example, the position of the box 48 or the rod 49 of the hydraulic actuator 46. The sensor 60 is, for example, a linear sensor of the Linear Variable Differential Transformer (LVDT) type. The sensor 60 is configured to measure the position of the rod 49 or the box 48 of the hydraulic actuator 46. For example, the sensor is located in the hydraulic actuator 46. In another example, not shown, the sensor 60 is a position sensor. The position sensor is used to measure the position of the blade 30.

[0090] The sensor 60 provides the information I1 to the electronic control circuit 58. The electronic control circuit 58 will then provide instructions to the control box 57, which will determine the position of the actuator 55 and, if necessary, control the rotation of the auxiliary actuator 56 to adjust the flow of the pump 54 by tilting the auxiliary disk 54g and modify the position of the rod 49 or the box 48 of the hydraulic actuator 46 according to the desired pitch setting of the blades 30.

[0091] The electronic control circuit 58 also or alternatively receives a signal S1 concerning the flight conditions of the aircraft and / or the state of the turbine engine 1 . The signal S1 is also or alternatively taken into account to provide an instruction O1 to the control box 57 .

[0092] The pump 54 is fluidly connected to the hydraulic circuit C. The hydraulic supply circuit C includes, for example, a first circuit C1 that connects at least one of the receiving chambers 54 d of the pump 54 to the first chamber 46 a of the hydraulic actuator 46 and a second circuit C2 that connects the second chamber 46 b of the hydraulic actuator 46 to at least one of the receiving chambers 54 d of the pump 54 .

[0093] The hydraulic supply circuit C is a closed circuit. The hydraulic supply circuit is independent of the hydraulic lubrication circuit of the turbine engine 1, which is configured to lubricate the reducer 33, for example. The fluid in the hydraulic supply circuit C that supplies the hydraulic actuator 46 is, for example, a hydraulic fluid. For example, the liquid is a pressurized oil or a phosphate ester (such as Skydrol). Therefore, the fluid is a fluid that circulates in a closed circuit in the hydraulic supply circuit C and is independent of the lubrication circuit of the turbine engine 1. Therefore, the fluid can be different from the oil used in the lubrication circuit of the turbine engine 1. Therefore, the fluid can have a lower freezing point or viscosity characteristics, especially when the operating temperature of the turbine engine 1 is low, the lower freezing point or viscosity characteristics are more suitable for the conditions of the turbine engine 1. For example, the freezing point of the fluid in the hydraulic supply circuit C is between -70°C and -50°C, in particular between -65°C and -60°C. The fluid pressure in the hydraulic supply circuit C is advantageously greater than 100 bar, preferably greater than 200 bar, and even more preferably between 250 bar and 350 bar. Since the hydraulic supply circuit C is closed, the hydraulic supply circuit is not charged and a high pressure can be achieved in the hydraulic circuit. This makes it possible to reduce the overall size of the hydraulic actuator 46.

[0094] Reference Figure 6, the hydraulic circuit C advantageously comprises, for example, a hydraulic accumulator 61 to compensate for changes in the volume of the fluid due to the compressibility and expansion of the fluid. The hydraulic accumulator 61 is in fluid communication with the pump 54. The hydraulic accumulator 61 may be integrated with the pump 54. The hydraulic accumulator 61 is rotationally fixed to the hydraulic actuator 46, so that it can perform a rotational movement about the longitudinal axis X.

[0095] Since the axial piston 54 c and the hydraulic accumulator 61 can rotate relative to the longitudinal axis X, the invention makes it possible to dispense with a rotating hydraulic delivery device.

[0096] Thanks to the invention, the tilting of the main disc 54e drives the axial piston 54c in translation. This makes it possible to vary the stroke of the axial piston 54c and therefore the flow rate of the pump 54. The volumes in the first chamber 46a and the second chamber 46b of the hydraulic actuator 46 vary, which causes the rod 49 or the box 48 of the hydraulic actuator 46 to move in translation, thus causing the blade 30 to be driven in rotation about the pitch axis C of the blade.

[0097] Thanks to the invention, no additional components are required, such as a rotating electric transformer associated with the electric motor enabling the flow rate of the pump 54 to be varied, or a rotating oil conveyor enabling the oil to be conveyed between the pump 54 and the hydraulic actuator 46, which also reduces oil leaks and the need for an additional recovery pump. Furthermore, since no electric motor is running when the aircraft is in flight, the pump 54 is driven by the drive shaft 32, and therefore the power consumption is low.

[0098] Furthermore, since the pump 54 is advantageously reversible, no flow switching valves or controlled circuits are required during the flight phases of the aircraft.

Claims

1. A module (3) for an aircraft turbine engine (1), said module (3) comprising a longitudinal axis (X), and include: a hub (43) centered on the longitudinal axis (X) and configured to be capable of rotational movement around the longitudinal axis (X), - blades (30) carried by said hub (43), each of said blades (30) being movable about a pitch axis (C) extending radially with respect to said longitudinal axis (X), and - means (45) for varying the pitch of the blade (30) about its pitch axis (C), said means (45) comprising: a hydraulic actuator (46) configured to be capable of rotational movement about the longitudinal axis (X) and configured to drive the blade (30) about its pitch axis (C), A supply pump (54) for supplying fluid to the hydraulic actuator (46), the supply pump comprising: an axial piston (54c) configured to be capable of rotational movement about the longitudinal axis (X) and configured to deliver the fluid to the hydraulic actuator (46), and a connecting disc (54g), which is connected to the axial piston (54c) and cooperates with an annular main disc (54e) centered on the longitudinal axis (X), wherein the main disc (54e) is configured not to rotate around the longitudinal axis (X) and is capable of tilting relative to the longitudinal axis (X), and the connecting disc (54g) is arranged between the main disc (54e) and the axial piston (54c), The axial piston (54c) is capable of translationally moving in a direction (D) parallel to the longitudinal axis (X), the tilting of the main plate (54e) causing the axial piston (54c) to move in the direction (D), and An auxiliary actuator (56) is connected to the connecting disk (54g) and is configured to drive the connecting disk (54g) to rotate around the longitudinal axis (X).

2. Module according to the preceding claim, in, The pump (54) includes a shield (54b) mounted around the main disk (54e) and the connecting disk (54g), and the shield is configured not to rotate around the longitudinal axis (X).

3. A module according to any one of the preceding claims, in, The main plate (54e) can be tilted at an inclination angle α between -45° and 45°, an angle α of 0° corresponding to a position of the main plate (54e) perpendicular to the longitudinal axis (X).

4. A module according to any one of the preceding claims, in, The device (45) also includes an actuator (55) connected to the main plate (54e) and configured to tilt the main plate (54e) relative to the longitudinal axis (X).

5. A module according to any one of the preceding claims, in, The connecting disk (54g) is configured to be capable of rotational movement around the longitudinal axis (X) and to abut flatly against the main disk (54e).

6. A module according to any one of the preceding claims, in, The axial piston (54c) is connected to the connecting plate (54g) via a ball joint (54h).

7. A module according to any one of the preceding claims, in, The pump (54) comprises a transmission shaft (54a) centered on the longitudinal axis (X), the transmission shaft being rotationally fixed to the connecting disc (54g), and the main disc (54e) being mounted around the transmission shaft.

8. Module according to the preceding claim, further comprising a drive shaft (32) rotationally fixed to the hub (43) and configured to drive the transmission shaft (54a) in rotation about the longitudinal axis (X).

9. A module according to any one of the preceding claims, further comprising an electronic control circuit (58) configured to send instructions (O1) to the auxiliary actuator (56) to drive the connecting disk (54g) to rotate around the longitudinal axis (X).

10. A module according to any one of the preceding claims, in, The auxiliary actuator (56) is connected to the connection plate (54g) by a spline connection or a universal joint connection or an Oldham joint connection or an embedded connection.

11. A module according to any preceding claim in combination with claim 8, in, The hydraulic actuator (46) is a cylinder rotationally fixed to the drive shaft (32), and includes a box body (48), a rod (49) arranged in the box body (48), and a first chamber and a second chamber (46a, 46b) defined in the box body (48), the first chamber and the second chamber being connected to the pump (54), the rod (49) or the box body (48) being movable in translation and connected to the impeller (30).

12. Module according to the preceding claim, It is characterized in that The rod (49) or the box (48) is rotationally fixed to the drive shaft (32).

13. A turbine engine (1) for an aircraft, comprising a module (3) according to any one of the preceding claims.

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