VARIABLE TILT FAN

Description

Technical field

[0001] The present invention relates to the general field of turbomachines equipped with one or two shrouded or unshrouded fans, and more particularly to the cylinder chamber allowing controlled adjustment of the pitch of the fan blades of these turbomachines.

[0002] The present invention aims to constitute a wedging device with an attached jack which optimizes the integration of the jack chamber. Previous techniques

[0003] We know of timing systems which allow the orientation of the blades which form the propellers of turbojet engines to be adjusted in order to regulate the thrust provided according to the environment using a jack device.

[0004] Patent application FR3046407 describes an annular actuator for a timing system whose body is formed by the bearing support, and on which the chamber end is attached. Sealing must be ensured by several added parts (cover, fixing dogs, etc.). In the event of deformation of the bearing support, for example when it is subjected to a strong unbalance of the fan, the piston can become stuck in the cylinder body.

[0005] Patent US4718823 describes a jack device having a jack body with an attached chamber end, the whole attached to the bearing support, which multiplies the assembly operations. In addition, this document does not describe the system for supplying the jack chamber.Patent application FR3036141A1 discloses a radial control shaft for a device for controlling the orientation of the fan blades of a turbomachine with an unducted fan, the shaft comprising an external part which is intended to be mounted in the control device from the outside thereof and to be coupled to at least one fan blade for adjusting its orientation, and an internal part, independent of the external part, which is intended to be mounted from the inside of the control device, to be connected to a motion transfer bearing to pivot the shaft about a radial axis, and to ensure closure of an oil enclosure in which said bearing is housed, the external and internal parts of the shaft being coupled to each other. Statement of the invention

[0006] The invention aims to overcome at least some of the aforementioned drawbacks and to propose a cylinder device system having an attached cylinder body, allowing simple assembly, which ensures that the cylinder does not get stuck in its chamber and which allows good sealing between the chamber and the piston.

[0007] In view of the above, the invention relates to a device as defined in claim 1.

[0008] Preferably, the internal volume of the cylinder body is closed upstream by a wall provided with a plurality of holes through which the cylinder rods pass.

[0009] For example, the cylinder body is secured to the annular casing forming the bearing support by a circular flange surrounding the cylinder body.

[0010] Advantageously, the circular flange is screwed onto the annular casing.

[0011] Preferably, the device comprises notches distributed around the inner contour of the chamber bottom.

[0012] In one embodiment, the device comprises an annular oil circuit centered on the longitudinal axis and surrounding the plurality of cylinder rods and comprising a through passage forming an oil inlet passing through the annular casing towards the cylinder body.

[0013] Advantageously, the annular oil circuit comprises a double circulation of oil through two substantially concentric annular channels.

[0014] The device may comprise several cylinder bodies in each of which a piston is housed, said cylinder bodies being distributed regularly around the longitudinal axis of the turbomachine and each piston being linked by one end of a cylinder rod to a synchronization ring.

[0015] According to one embodiment, the invention relates to a system for controlling the orientation of the fan blades of a turbomachine comprising at least one set of fan blades with adjustable orientation, said set being integral in rotation with a rotary ring, the fan blades being coupled, for the adjustment of their orientation, to a motion transfer bearing intended to pivot pivots of the fan blades around their radial axis, said motion transfer bearing comprising an internal ring connected to a device as defined previously.

[0016] The invention also relates to a method of mounting the device comprising, from a propeller shaft previously mounted on a main casing of the turbomachine by means of a rolling bearing, the assembly of each cylinder formed of the cylinder rods and the piston mounted on the cylinder body, said assembly being carried out by housing each cylinder one by one inside the casing forming the bearing support, and the assembly of this assembly on the main casing of the turbomachine and the propeller shaft. Brief description of the drawings

[0017] The invention will be better understood from a detailed study of some embodiments taken as non-limiting examples and illustrated by the appended drawings, in which: [ Fig 1 ] is a sectional view in its environment of a fixed jack device according to the invention. [ Fig 2 ] is a perspective and partial view of the device of the figure 1 . [ Fig 3] is a sectional view of the cylinder chamber made in the housing. [ Fig 4 ] is a first sectional view of the cylinder chamber in which the cylinder body receiving the cylinder is housed. [ Fig 5 ] is a second sectional view of the cylinder chamber in which the cylinder body receiving the cylinder is housed. Detailed description

[0018] The invention applies to any turbomachine equipped with at least one ducted or unducted fan, and whose propeller blades (in the case of an unducted fan) or fan blades (in the case of a ducted fan) are equipped with a pitch change system. The invention applies in particular to turboprops with one or more pusher propellers, as well as to turbojets with propeller(s) (called "Open Rotor" in English) which comprise a propeller (and a variable-pitch stator for the USF - "Unducted Single Fan", or "single unducted fan") or two counter-rotating propellers placed upstream (in the "puller" version in English) or downstream (in the "pusher" version in English) of the gas generator.

[0019] The invention also applies to turbomachines with a ducted fan.

[0020] The architecture of these types of turbomachines is well known to those skilled in the art and will therefore not be described here in detail. Briefly, these turbomachines comprise one or more propellers (in the case of a turbomachine with an unducted fan) or a fan (in the case of a turbomachine with a ducted fan) each consisting of a set of fan blades (or vanes) with a variable pitch angle, that is to say that their orientation can be modified by means of a blade orientation control system described below.

[0021] There Figure 1 partially represents a device 1 comprising an example of a control system 2 for the orientation of the blades of a propeller of a turbomachine with an unducted fan according to the invention.

[0022] Of course, in the case of a turbomachine with a shrouded fan, the principle of the invention described below applies in the same way to the fan blades.

[0023] This control system 2 comprises a rotating ring 4 (or hub) centered on the longitudinal axis XX of the turbomachine and provided with orifices 6 through which the pivots 8 of the fan blades are mounted (not shown in the figures).

[0024] Each pivot 8 is coupled, for adjusting the orientation of the corresponding blade, to a motion transfer bearing 10 (also called LTB for “Load Transfer Bearing”) intended to pivot said pivot around its radial axis ZZ.

[0025] For this purpose, the motion transfer bearing 10 comprises an outer ring 12 and an inner ring 14, these rings 12, 14 being centered on the longitudinal axis XX of the turbomachine, movable in translation along this axis XX, and defining rolling tracks for bearings (here two rows of balls 16 with angular contact to transmit axial forces in both directions).

[0026] The outer ring 12 of the motion transfer bearing is coupled, directly or indirectly, to an inner radial end of the pivots, for example by means of lever arms 18.

[0027] When the inner ring of the motion transfer bearing moves axially under the actuation of a jack device, it pivots the lever arms and thus the pivots 8 in the holes 6 of the rotating ring around their radial axis ZZ, thereby causing the fan blades to pivot.

[0028] Downstream of the jack device, the turbomachine also comprises a main casing 19 carrying a ball bearing 21 intended to support in rotation the propeller shaft 23 which supports the rotating ring 4.

[0029] This propeller shaft 23 is preferably driven by a turbine and a reducer (not shown in the figures).

[0030] On this main casing 19, an annular casing 20 is fixed, centered on the longitudinal axis XX of the turbomachine and inclined relative to it by an angle generally greater than thirty degrees (this inclination being oriented so as to give the casing 20 the shape of a cone open downstream).

[0031] Typically, this casing 20 serves as a support for a rolling bearing 24 intended to guide the rotating ring 4 in rotation.

[0032] For this purpose, the casing 20 carries the outer ring 24a of the rolling bearing 24 (the inner ring 24b of which is integral with the rotating ring 4).

[0033] In addition, the casing 20 and the rotating ring 4 delimit between them an oil enclosure 25 containing the jack device 1.

[0034] This oil chamber 25 is pressurized in depression so that the oil does not escape.

[0035] To limit the leakage rates outside the enclosure, it is notably planned to have a seal 27 downstream of the pivots of the fan blades, between a ferrule 23a of the propeller and the main casing 19.

[0036] Leaks are possible at the holes 6 of the rotating ring 4 in which the pivots of the fan blades are mounted.

[0037] These leaks are however compensated by the seals of the oil enclosure.

[0038] Furthermore, this oil enclosure 25 extends downstream of the rolling bearing 21 and can 10 contain a reducer and seals between the different shafts.

[0039] According to the invention, the jack device 1 intended to ensure pivoting of the fan blades comprises in particular an annular jack body 22 which is centered on the longitudinal axis XX of the turbomachine and which is housed inside the space delimited by the casing 20 forming a bearing support.

[0040] As illustrated by the Figure 3 , the cylinder body 22 is a part added to the casing 20, unlike the cylinder bodies of the state of the art which form a single part with the casing 20.

[0041] The cylinder body 22 delimits an internal volume inside which a piston 30 is capable of sliding, separating the internal volume of the cylinder body into two chambers isolated from each other, namely an upstream chamber 22a and a downstream chamber 22b.

[0042] A plurality of independent pistons or each linked by their rod to a synchronizing ring can be provided.

[0043] This synchronizing ring acts as a synchronizer for the pistons 30 by being able to slide inside the internal volume of the cylinder body 22 under the effect of a hydraulic fluid (not shown) injected under pressure into one or other of the upstream and downstream chambers.

[0044] As illustrated by the Figure 4 , the internal volume of the cylinder body 22 is closed upstream by a wall 26 provided with a plurality of holes 28 crossed by the cylinder rods 42. The holes 28 are distributed around the longitudinal axis XX of the turbomachine.

[0045] Furthermore, the internal volume of the cylinder body 22 is closed downstream by a chamber bottom 32 which forms, unlike the chamber bottoms of known devices, a single piece with the annular casing 20 forming a bearing support.

[0046] The production of the chamber bottom 32 entirely in the material of the annular casing 20 makes it possible to overcome the difficulties of adding a closure attached to the casing 20 directly opposite the piston. An added chamber bottom causes in particular difficulties with sealing and premature wear, while its integration into the casing increases its mechanical resistance to the high hydraulic pressure constraints in the chambers 22a, 22b.

[0047] Furthermore, an added chamber bottom requires special arrangements for sealing the internal volume of the cylinder body, for example at its internal periphery, so as to ensure sealing of the internal volume of the cylinder body in which there is significant oil pressure.

[0048] The cylinder body 22 can be secured to the annular casing 20 forming a bearing support by a circular flange 31 crowning the cylinder body 22.

[0049] The circular flange 31 is screwed onto the annular casing 20, for example by a series of holes distributed circularly around the longitudinal axis XX of the turbomachine, at an external periphery of the flange 31, and which are crossed by screws (not shown in the figures) up to threads arranged opposite on the casing.

[0050] As also shown on the Figure 2 , the jack device 1 according to the invention also comprises a plurality of jack rods 42 which are mounted through the holes 28 of the wall 26 of the jack body.

[0051] These cylinder rods are preferably regularly distributed around the longitudinal axis XX of the turbomachine to correspond to the stall force requirement.

[0052] The number of cylinder rods is a compromise between the force to be applied to each rod, which directly influences the section of each rod, and the number of rods, which influences the weight of the system.

[0053] Preferably there are at least 4 rods to distribute the forces on the piston.

[0054] Each cylinder rod 42 has a downstream end which is fixed to a piston 30 which can be connected to a synchronization ring 34 of the cylinder body by a cylinder rod 42 and an upstream end which is connected to the internal ring 14 of the motion transfer bearing 10 to drive it in translation.

[0055] The fixing of the cylinder rods on each piston 30 can be done by means of nuts 44 which are tightened on the downstream end of the rods, these being threaded.

[0056] Likewise, at their upstream end, the cylinder rods 42 are connected to the internal ring 14 of the motion transfer bearing by means of screws 46 extending in a radial direction ( Figure 1 ).

[0057] The synchronizing ring function can be performed either by the inner ring 14 in the case of a plurality of cylinder bodies 22 ( Figures 3, 4 And 5 ) or by a synchronization ring separate from the internal ring 14 and formed by the single piston 30 in the case of a single annular-shaped cylinder ( Figure 2 ).

[0058] As illustrated by the Figures 4 And 5 , the device 1 comprises an annular oil circuit 29 centered on the longitudinal axis XX and surrounding the plurality of cylinder rods 42.

[0059] The use of several 42 cylinders ensures redundancy of their function.

[0060] Cylinder maintenance is also easier: it is no longer buried under the fan hub, but is now easily accessible on the bearing support. In addition, the cylinders can be replaced individually in the event of maintenance.

[0061] The oil circulation in the oil circuit 29 is supplied from the oil enclosure 25 and opens into the cylinder body 22 through a through passage 29c forming an oil inlet passing through the annular casing 20 towards the cylinder body 22.

[0062] The through passage 29c is transverse to the radial axis of the device 1 and directed towards the bottom of the chamber 32.

[0063] The casing 20 includes an annular widening 41 from the passage 29c to the bottom of the chamber 32, which allows the oil to flow to the bottom of the chamber 32.

[0064] The chamber bottom 32 returns the oil to the piston 30. Each chamber bottom 32 associated with a cylinder thus allows the oil supply to this cylinder.

[0065] As illustrated, the annular widening 41 can form a space of approximately rectangular section according to the cutting plane of the Figure 1 , located between the casing 20 and the cylinder body 22.

[0066] Furthermore, the chamber bottom 32 may comprise notches 33, distributed over the inner contour of the chamber bottom 32 ( Figure 3 ).

[0067] The notches 33 delimit hollows allowing the oil arriving from the opening 29c and from the widening 41 to be inserted towards the downstream chamber 22b, between the piston 42 and the bottom of the chamber 32, in particular when the piston 42 is against the notches 33.

[0068] The notches 33 also ensure that the chamber bottom 32 is not obstructed, a foreign body or fouling being able to find a home between the notches and not on them, so that the stroke of the cylinder 22 is not obstructed.

[0069] The annular oil circuit 29 may comprise a double circulation of oil through two substantially concentric annular channels 29a, 29b.

[0070] In particular, two complementary oil circuits 29a, 29b can be used, each supplying half of the cylinders 42, to ensure that the system is resistant to failure of one of the two oil systems.

[0071] For example, the two annular channels 29a, 29b are superimposed, for the sake of optimizing the compactness of the device 1. They may also each have a section of substantially trapezoidal shape, in particular rectangular.

[0072] The two annular channels 29a, 29b serve respectively, for the one closest radially to the axis XX and for the one furthest away, to carry out the circulation of oil between the different jacks 22, and to supply oil to the chamber bottom 32 via the bearing support.

[0073] In this case, the radially closest conduit is therefore the one which opens onto the opening passage 29c.

[0074] The operation of the jack device 1 follows obviously from the above.

[0075] To adjust the orientation of the pivots of the fan blades 8, a hydraulic fluid is injected under pressure into one or other of the upstream and downstream chambers 22a, 22b of the chamber, which causes a movement of each piston 30, (and of the synchronization ring if there is one to which all the pistons 30 are linked) along the longitudinal axis XX of the turbomachine. The rods 42 then translate axially in a synchronized manner so as to move the motion transfer bearing upstream or downstream. In turn, this translation of the bearing causes a pivoting of the lever arms 18 resulting in a synchronized pivoting of the fan blades.

[0076] The assembly of the jack device according to the invention is as follows.

[0077] Firstly, the propeller shaft 23 is assembled to the reducer and the rolling bearing 21 (and its support) to the main casing 19 of the turbomachine. The cylinder rods 42 and the pistons 30 taken one by one or mounted on the synchronizing ring are then assembled on the cylinder body 22 and the casing 20 forming a bearing support.

[0078] The assembly formed by the cylinder rods 42, the pistons 30 independent or mounted on the synchronization ring, the cylinder body, the casing forming the bearing support and the rolling bearing 24 can then be brought axially from upstream to downstream to assemble it on the main casing 19 of the turbomachine and 15 the propeller shaft 23.

[0079] The motion transfer bearing 10 is then assembled with the cylinder rods 42.

[0080] The downstream casing 23a of the propeller is then assembled with the rotating ring 4 and the pivots of the fan blades are mounted on this downstream casing.

[0081] The lever arms 18 and the fan blade pivot studs are added to link the pivots to the motion transfer bearing 20.

[0082] Finally, an upstream propeller casing 23b is assembled 23c to the propeller shaft 23 via a splined connection and to the rotating ring 4.

[0083] Disassembly of the jack device is carried out in reverse order.

[0084] A device 1 is thus assembled, serving as a bearing support integrating a particularly compact and resistant chamber bottom and oil circulation.

[0085] In addition, the bearing support is advantageously designed to allow printing using a 3D printing technology of the “Powder Bed Fusion” type (from the Anglicism “Laser Bed Melting”). This allows the part to be produced in a single piece and to integrate the oil circulation pipes 29.

Claims

1. Device (1) with a fixed actuator for a system for controlling (2) the orientation of the fan blades of a turbomachine, comprising: an annular casing (20) for the turbomachine, at least one actuator body (22) accommodated inside the annular casing forming a support for a bearing, said annular casing (2) being configured to be centred on a longitudinal axis (X-X) of the turbomachine and inclined with respect to this axis, each actuator cylinder body (22) comprising an inner volume in which a piston (30) is able to slide, separating the inner volume into two chambers (22a, 22b) isolated from each other; and at least one actuator rod (42) passing through the annular casing (20) forming a support for the bearing and each actuator cylinder rod (42) having one end fastened to the piston (30) and an opposite end intended to be connected to an inner ring (14) of a movement transfer bearing (10) to drive it in translation, characterised in that said inner volume of the actuator cylinder body (22) is closed downstream by a chamber bottom (32) which forms one-piece with the annular casing (20) forming a support for the bearing.

2. Device (1) according to claim 1, wherein the inner volume of the actuator cylinder body (22) is closed upstream by a wall (26) provided with a plurality of holes (28) through which the actuator cylinder rods (42) pass.

3. Device (1) according to any of the preceding claim, wherein the actuator cylinder body (22) is secured to the annular casing (20) forming a support for the bearing by a circular flange (31) surrounding the actuator cylinder body (22).

4. Device (1) according to claim 3, wherein the circular flange (31) is screwed onto the annular casing (20).

5. Device (1) according to any of the preceding claims, comprising slots (33) distributed over the internal contour of the chamber bottom 32).

6. Device (1) according to any of the preceding claims, including an annular oil circuit (29) centred on the longitudinal axis (X-X) and surrounding the plurality of actuator cylinder rods (42) and including a through passage (29c) forming an oil inlet passing through the annular casing (20) towards the actuator cylinder body (22).

7. Device (1) according to claim 6, wherein the annular oil circuit (29) includes a double circulation of oil through two substantially concentric annular channels (29a, 29b).

8. Device (1) according to any of the preceding claims, including several actuator cylinder bodies (22) in each of which a piston (30) is accommodated and said actuator cylinder bodies (22) are evenly distributed around the longitudinal axis (X-X) of the turbomachine.

9. System for controlling (2) the orientation of the fan blades of a turbomachine, comprising a device (1) according to any of claims 1 to 8 and at least one set of fan blades with adjustable orientation, said set being secured in rotation with a rotary ring (4), the fan blades being coupled, for the adjustment of their orientation, to the movement transfer bearing (10) intended to make pivots (8) of the fan blades pivot about their radial axis, said movement transfer bearing comprising an inner ring (14) connected to said device (1).

10. Method for mounting the device according to any of claims 1 to 8, comprising, starting from a propeller shaft (23) mounted beforehand on a main casing (19) of the turbomachine via a rolling bearing (21), assembling each actuator cylinder formed of the at least one actuator cylinder rod (42) and the piston (30) mounted on the actuator cylinder body (22), said assembly being performed by accommodating each actuator cylinder one after another inside the casing (20) forming a support for the bearing, and the assembly of this set on the main casing (19) of the turbomachine and the propeller shaft (23).