TURBOMACHINE COMPRISING AN UNFACED MOBILE BLOWER AND AN UNFACED FIXED RECTIFIER

Abstract

Turbomachine for an aircraft comprising: - an unfaired fan; - an unfaired stator comprising at least one guide vane (6) with variable pitch about an axis of rotation (Y); - a control system (19) for the pitch of the guide vane (6), the control system (19) comprising a guide vane (6) actuation device (20) which includes an electric motor (21); characterized in that the control system (19) further comprises a braking device (22) configured to occupy an active position in which the braking device (22) blocks the rotation of the guide vane (6) about the axis of rotation (Y) when the actuation device (20) is stopped, and a passive position in which the braking device (22) allows the rotation of the guide vane (6) about the axis of rotation (Y) when the actuation device (20) is running. Figure for the abridged version: 4

Description

Title of the invention: TURBOMACHINE COMPRISING AN UNFACED MOBILE BLOWER AND AN UNFACED FIXED RECTIFIER Technical field of the invention

[0001] The present invention relates to a turbomachine comprising a movable unshod blower and a fixed unshod straightener, and more specifically to the adjustment of the timing of the straightener guide vanes. Technical background

[0002] A turbomachine may include a mobile, unfaired blower that is driven into rotation by a turbine associated with a gas generator and a fixed, unfaired rectifier that is configured to rectify at least a part of the airflow generated by the blower.

[0003] Such a high bypass ratio turbomachine has the advantage of having excellent efficiency, including a reduction in fuel consumption and carbon dioxide emissions.

[0004] The straightener comprises an annular row of variable pitch guide vanes, i.e. guide vanes whose pitch (and more precisely the pitch angle) is adjustable according to, in particular, the flight parameters and the operating regimes of the turbomachine.

[0005] To adjust the timing of the guide vanes, the turbomachine includes an adjustment system which may be common to all guide vanes or specific to each of the guide vanes.

[0006] The adjustment system is placed in a compartment which is delimited in particular by an external fairing which forms the external aerodynamic lines of the turbomachine.

[0007] Traditionally, the adjustment system comprises one or more hydraulic cylinders and a mechanism specific to each of the guide vanes. Each mechanism includes, for example, several connecting rods and is configured to transform the movement initiated by the hydraulic cylinder(s) into a rotational movement of the corresponding guide vane.

[0008] Such an adjustment system has the particular disadvantage of being bulky.

[0009] Engine manufacturers are therefore seeking alternatives to reduce the size of the control system, in particular to be able to integrate additional equipment without having to increase the dimensions of the external aerodynamic lines of the turbomachine.

[0010] One solution could be to have an adjustment system comprising an electric motor specific to each of the guide vanes. The rotor of each electric motor would then be linked directly or indirectly to the corresponding guide vane in order to adjust its pitch.

[0011] A major drawback of such an embodiment is the need to constantly monitor the various electric motors, to the detriment of electrical consumption and the lifespan of the electric motors.

[0012] The objective of the present invention is to improve the variant stated above which uses electric motors to remedy the aforementioned drawbacks. Summary of the invention

[0013] The invention thus proposes a turbomachine for an aircraft comprising: - an unfaired blower which is mobile in rotation around a longitudinal axis X; - an unfaired straightener which is fixed in rotation about the longitudinal axis X, the straightener being configured to straighten at least part of an airflow generated by the unfaired blower, the straightener comprising at least one guide vane with variable pitch about an axis of rotation Y which is substantially perpendicular to the longitudinal axis X, the guide vane being integral with a shaft which is guided in rotation about the axis of rotation Y in a casing, the casing being fixed to a fixed structure of the turbomachine; - a system for adjusting the positioning of the guide blade, the adjustment system comprising a device for actuation of the guide blade around the axis of rotation Y, the actuation device comprising an electric motor; characterized in that the adjustment system further comprises a braking device configured to occupy an active position in which the braking device blocks the rotation of the guide vane around the axis of rotation Y when the actuation device is stopped, and a passive position in which the braking device allows the rotation of the guide vane around the axis of rotation Y when the actuation device is running.

[0014] The incorporation of a braking device into the adjustment system makes it possible to no longer keep the electric motor energized when the actuation device is stopped, in order to optimize its lifespan.

[0015] The braking device also makes it possible to considerably reduce the electrical requirements of the control system, and consequently of the turbomachine.

[0016] The turbomachine according to the invention may comprise one or more of the following features, taken individually or in combination with each other: - the braking device is mounted in the housing; - the shaft is guided in rotation around the Y axis of rotation in the housing via a first bearing and a second bearing, the braking device being disposed between the first bearing and the second bearing; - the electric motor is mounted on an internal end of the casing with reference to the longitudinal X axis; - The braking system includes: — a bracket attached to the housing; — a disc attached to the shaft and placed in the caliper; — a piston moving in translation along the axis of rotation Y, the piston being set in motion by an electromagnetic assembly which is carried by the caliper; — a compression spring which is supported both on the piston and on the electromagnetic assembly; with the disc blocked by the piston under the action of the spring, when the braking device is in active position, the electromagnetic assembly is not then electrically powered; the disc being released by the piston under the action of the electromagnetic assembly which is electrically powered, when the braking device is in passive position, the spring then being compressed by the piston; - the piston includes an annular head around the axis of rotation Y and several feet projecting from an internal face of the head, each foot including a blind orifice in which an electromagnet of the electromagnetic assembly is housed with play; - the piston includes several tabs projecting from a peripheral face of the head, each tab sliding in a groove formed in the caliper, so as to guide the piston in translation relative to the caliper; - the braking system is hydraulic, mechanical or electromagnetic; - the actuation device further includes an epicyclic gear reducer which comprises: — a mobile solar panel rotating around the Y axis of rotation and attached to a rotor of the electric motor; — a fixed crown that surrounds the solar panel and is attached to the case; — at least one rotating mobile satellite, and meshed with both the sun and the corona; — a mobile satellite carrier rotating around the Y axis of rotation and attached to the shaft; - the reducer is mounted in the housing; - the satellite carrier is made as a single unit with the shaft; - The adjustment system includes a position sensor associated with the shaft or a rotor of the electric motor, in order to measure the timing of the guide vane; - the adjustment system is controlled by an electronic control board which is specific to the guide vane; - the turbomachine includes a shrouded fan which is mobile in rotation around the longitudinal axis X and which is surrounded by a nacelle, the nacelle internally defining a compartment in which is located the housing and the adjustment system. Brief description of the figures

[0017] The invention will be better understood and other details, features and advantages of the invention will become more apparent upon reading the following description, given by way of non-limiting example and with reference to the accompanying drawings in which:

[0018] [Fig-1] [Fig.1] is a schematic longitudinal half-section view of a tower aircraft engine according to a first embodiment of the invention;

[0019] [Fig.2] [Fig.2] is a schematic view in longitudinal half-section of an aircraft turbomachine according to a second embodiment of the invention;

[0020] [Fig.3] [Fig.3] is a front view of a timing adjustment system for a guide vane of a turbomachinery straightener illustrated in Figures 1 and 2;

[0021] [Fig.4] [Fig.4] is a longitudinal sectional view of the adjustment system illustrated in [Fig.3];

[0022] [Fig.5] [Fig.5] is a cross-sectional view of the adjustment system according to the section plane VV of [Fig.4], the housing being hidden;

[0023] [Fig.6] [Fig.6] is a perspective view of the adjustment system, with the housing and braking device hidden;

[0024] [Fig.7] [Fig.7] is a detailed view of the braking device of the adjustment system;

[0025] [Fig.8] [Fig.8] is a detailed view of the brake device disc;

[0026] [Fig.9] [Fig.9] is a detailed view of the braking device, the electro assembly magnetic of the braking device being represented transparently and the caliper of the braking device being hidden;

[0027] [Fig. 10] [Fig. 10] is a detailed view of the braking device, the electromagnetic assembly and the caliper of the braking device being shown transparently;

[0028] [Fig. 11] the [Fig. 11] is a control diagram of an adjustment system;

[0029] [Fig. 12] the [Fig. 12] is a control diagram of several adjustment systems. Detailed description of the invention

[0030] Figures 1 and 2 show a turbomachine la, 1b with longitudinal axis X for an aircraft 2, such as an airplane. The turbomachine la, 1b comprises an unfaired fan 3 and an unfaired stator 4.

[0031] The term "non-faired" associated with the blower 3 means that the blades 5 of the The blower blades 3 are not enclosed at their free end by a fairing. Similarly, the term "unfaired" associated with the rectifier 4 means that the guide vanes 6 of the rectifier 4 are not enclosed at their free end by a fairing.

[0032] As illustrated in Figures 1 and 2, the unshod fan 3 is mobile in rotation around the X axis and driven in rotation by a power turbine 50 associated with a gas generator 7 arranged here downstream of the unshod fan 3. The unshod fan 3 comprises an annular row of variable pitch blades 5.

[0033] When the turbomachine la, 1b is in "propulsion" mode, the fan 3 generates an airflow which flows upstream to downstream around the external fairings 51 of the streamlined body of the turbomachine la, 1b, so as to propel or move forward the aircraft 2. The turbomachine la, 1b can also operate in "reversing" mode, so as to brake the aircraft 2, at the time of its landing.

[0034] By convention in this application, the terms "upstream" and "downstream" are defined with respect to the direction of airflow, when the turbomachine la, 1b is in "propeller" mode.

[0035] The power turbine 50 (or low-pressure turbine) is intended to drive the unshrouded fan 3 in rotation. The unshrouded fan 3 can be driven in rotation by the power turbine 50 via a speed reducer. The gas generator 7 conventionally comprises, from upstream to downstream, at least one compressor, one combustion chamber, and at least one expansion turbine (or high-pressure turbine). The compressor and the expansion turbine are rotationally linked to each other via a drive shaft. The gas generator 7 is supplied with air by an air inlet 8a, 8b which opens between the unshrouded fan 3 and the unshrouded rectifier 4.

[0036] As illustrated in Figures 1 and 2, the unshod straightener 4 is fixed in rotation about the X axis and is configured to straighten at least part of the airflow generated by the unshod blower 3. The straightener 4 is arranged here directly downstream of the unshod blower 3. The straightener 4 comprises a row of guide vanes 6 (stator vanes or OGV vanes for "Outlet Guide Vane") with variable pitch, each guide vane 6 being pitched about an axis of rotation Y which is substantially perpendicular to the X axis.

[0037] According to the first embodiment illustrated in [Fig. 1], the air inlet 8a directly supplies the gas generator 7. The air inlet 8a, the gas generator 7, and the power turbine 50 are surrounded by an annular compartment 9 around the X-axis, which is commonly referred to as the "Core compartment." The guide vanes 6 are arranged around this Core compartment 9.

[0038] According to the second embodiment illustrated in [Fig. 2], the turbomachine 1b further comprises a shrouded fan 10 which is placed in the air inlet 8b, this The shrouded fan 10 is more commonly known by its English designation, "Mid-Fan." The shrouded fan 10 rotates about the X-axis and is driven by the power turbine 50 (or low-pressure turbine). The shrouded fan 10 is enclosed by a nacelle 11, which internally defines an annular compartment 12 around the X-axis, commonly called the "Mid-Fan compartment." The gas generator 7 and the power turbine 50 are enclosed by an annular compartment 13 around the X-axis, commonly called the "Core compartment." The air inlet 8b splits into a primary stream 14, which supplies the gas generator 7, and a secondary stream 15, which is defined between the Core and Mid-Fan compartments 12 and 13. The guide vanes 6 are arranged around the Mid-Fan compartment 12, and in other words, around the nacelle 11.

[0039] As illustrated in Figures 3 and 4, each guide vane 6 is fixed to a shaft 16 which is guided in rotation about the Y axis in a housing 17, the housing 17 being fixed to a fixed structure 18 of the turbomachine la, 1b. The turbomachine la, 1b includes a pitch adjustment system 19 for each guide vane 6. The adjustment system 19 includes an actuation device 20 for the guide vane 6 about the Y axis, the actuation device 20 comprising an electric motor 21.

[0040] According to the invention, the adjustment system 19 further comprises a braking device 22 configured to occupy an active position in which the braking device 22 blocks the rotation of the guide vane 6 around the Y axis when the actuation device 20 is stopped, and a passive position in which the braking device 22 allows the rotation of the guide vane 6 around the Y axis when the actuation device 20 is running.

[0041] The term "running" associated with the actuation device 20 means that the actuation device 20 (and in particular the electric motor) generates mechanical power to actuate the guide vane 6 around the Y axis. Conversely, the term "stopped" associated with the actuation device 20 means that the actuation device 20 (and in particular the electric motor which is no longer energized) does not generate any mechanical power to actuate the guide vane 6 around the Y axis.

[0042] The incorporation of a braking device into the adjustment system makes it possible to no longer keep the electric motor under power and therefore to no longer make it exert torque when the actuation device is stopped, in order to optimize the life of the device and to reduce to some extent the electrical power consumed by the whole system.

[0043] The braking device thus makes it possible to significantly reduce the electrical requirements of the control system, and consequently of the turbomachine.

[0044] The braking device 22 can be mounted in the housing 17 or outside the case 17.

[0045] The shaft 16 can be guided in rotation around the Y-axis in the housing 17 via a first bearing 23 and a second bearing 24. In the present case, the braking device 22 is advantageously arranged between the first bearing 23 and the second bearing 24. Indeed, such an arrangement of the braking device 22 ensures optimal alignment between the moving and fixed parts of the braking device 22.

[0046] The electric motor 21 can be a DC motor, a stepper motor, an AC motor, etc.

[0047] The electric motor 21 can be single-coil or double-coil, in case redundancy is desired.

[0048] The electric motor 21 can be mounted in the housing 17 or outside the housing 17.

[0049] The braking device 22 can be electromagnetic, hydraulic, mechanical, etc.

[0050] The actuation device 20 may further include a gear train reducer, and preferably an epicyclic gear train reducer 25.

[0051] A gear train reducer makes it possible to reduce the output speed while increasing the output torque.

[0052] An epicyclic gear reducer 25 has the advantage of having a high reduction ratio while being compact.

[0053] The gear train reducer may include one or more reduction stages, depending on the desired reduction ratio.

[0054] The adjustment system 19 may include a position sensor associated with the shaft 16 or with a rotor 26 of the electric motor 21, so as to measure the timing of the guide vane 6, and thus precisely control the guide vane 6.

[0055] The position sensor can be an angular sensor of the RVDT type for "Rotary Variable Differential Transformer" or a linear sensor of the LVDT type for "Linear Variable Differential Transformer".

[0056] The different adjustment systems 19 can be controlled independently, jointly or in groups (two or three for example).

[0057] According to the embodiment illustrated in figures 3 to 10, the adjustment system 19 includes an actuation device 20 which is here a geared motor and an electromagnetic braking device 22.

[0058] The geared motor 20 comprises the electric motor 21 and an epicyclic gear reducer 25.

[0059] The guide vane 6 is here secured to the shaft 16 via fastening means which may be screws.

[0060] As illustrated in [Fig. 4], the housing 17 internally defines a housing in which are mounted two bearing bearings 23, 24 intended to guide the shaft 16, the electromagnetic braking device 22 disposed between the two bearing bearings 23, 24 and the epicyclic gear reducer 25.

[0061] The electric motor 21 is mounted on an internal end of the housing 17 with reference to the X axis. More specifically, the motor 21 comprises a stator 27 fixed to the internal end of the housing 17 via, for example, an annular row of screws around the Y axis, and a rotor 26 movable in rotation about the Y axis.

[0062] As illustrated in [Fig.3], the housing 17 externally comprises a mounting bracket 28 which is fixed to the fixed structure 18 of the turbomachine la, 1b via, for example, two bolts.

[0063] As illustrated in particular in Figures 4 and 7, the electromagnetic braking device 22 comprises: - a caliper 29 attached to the housing 17; - a disc 30 attached to the shaft 16 and placed in the bracket 29; - a piston 31 movable in translation along the Y axis, the piston 31 being set in motion by an electromagnetic assembly 32 which is carried by the caliper 29; - a compression spring 33 which is supported both on the piston 31 and on the electromagnetic assembly 32.

[0064] The disc 30 is blocked by the piston 31 under the action of the spring 33 when the braking device 22 is in the active position. The electromagnetic assembly 32 is then not electrically powered. The braking device 22 is thus normally in the active position.

[0065] The disc 30 is released by the piston 31 under the action of the electrically powered electromagnetic assembly 32, when the braking device 22 is in the passive position. The spring 33 is then compressed by the piston 31.

[0066] As illustrated in particular in Figures 8 and 9, the disc 30 is fixed to the shaft 16 via complementary splines 34. The disc 30 is located directly between a wing 35 of the caliper 29 and the piston 31.

[0067] As illustrated in Figures 4, 7 and 9, the piston 31 comprises an annular head 36 about the Y axis and several feet 37 projecting from an inner face of the head 36. The feet 37 are distributed regularly around the Y axis. Each foot 37 comprises a blind orifice 38 in which an electromagnet 39 of the electromagnetic assembly 32 is housed with clearance.

[0068] Each electromagnet 39 comprises an iron core surrounded by a coil which is electrically powered or not, depending on the active or passive position of the braking device 22.

[0069] As illustrated in Figures 9 and 10, the piston 31 further comprises several tabs 40 projecting from a peripheral face of the head 36. The tabs 40 are distributed regularly around the Y axis. Each tab 40 slides in a groove 41 formed in the caliper 29, so as to guide the piston 31 in translation relative to the caliper 29.

[0070] As illustrated in figures 4 and 5, the epicyclic gear reducer 25 comprises: - a solar 42 (or planetary) mobile in rotation around the Y axis and fixed to the rotor 26 of the electric motor 21; - a fixed crown 43 which surrounds the solar element 42 and which is integral with the case 17; - three rotating mobile satellites 44, each satellite 44 being meshed with both the solar 42 and the corona 43; - a satellite carrier 45 movable in rotation around the Y axis and fixed to the shaft 16.

[0071] More precisely, as illustrated in [Fig.5], the three satellites 44 are distributed regularly around the Y axis. Each satellite 44 is guided in rotation on a finger 46 of the satellite carrier 45 via one or more bearings.

[0072] The rotor 26 of the electric motor 21 is linked in rotation with the solar 42 by means of connection (for example splines) or by shrink fitting.

[0073] As illustrated in [Fig. 4], the planet carrier 45 is formed as a single piece (or from a single piece of material) with the shaft 16, the planet carrier 45 and the shaft 16 thus being a single unit. Alternatively, the planet carrier 45 could be attached and fixed to the shaft 16, for example by means of screws or bolts.

[0074] The control system 19 is electrically powered via an electrical power distribution unit (known by the English acronym PMU for "Power Management Unit") which may already be installed in the turbomachine la, 1b to power other equipment, namely one or more de-icing devices and / or one or more electric machines configured to operate in "motor" and "generator" mode, or which may be installed in the turbomachine la, 1b specifically for the control system 19. The electric machines are intended to participate in the electrical hybridization of the turbomachine la, 1b.

[0075] The geared motor 20 and the electromagnetic braking device 22 are thus connected to the electrical power distribution box via one or more electrical harnesses. It is possible to use a single electrical harness for different power supplies, for example an electric motor and a defrosting device, in order to minimize space requirements.

[0076] According to the embodiment illustrated in [Fig.1], the housing 17 and the adjustment system 19 associated with each of the guide vanes 6 are located in the Core compartment 9.

[0077] According to the embodiment illustrated in [Fig.2], the housing 17 and the adjustment system 19 associated with each of the guide vanes 6 are located in the Mid-Fan compartment 12.

[0078] Regarding the assembly, the complete housings 17 are assembled before the turbomachine la, 1b is sent to the aircraft manufacturer. Thus, when the turbomachine la, 1b arrives at the aircraft manufacturer, all that remains is to attach each guide vane 6 to the corresponding shaft 16.

[0079] As illustrated in [Fig. 1 1], each control system 19 is controlled by an electronic control board 47 which is specific to the guide vane 6. Each electronic control board 47 is associated with an identifier which is unique in order to know the mounting position on the turbomachine of each control system 19.

[0080] As illustrated in [Fig. 12], the various electronic control boards are connected to a control box 48 which is common to all the guide vanes 6, via a communication network 49. The control box 48 is in turn connected to one or more engine computers (better known by the English acronym EEC for "Electronic Engine Control").

[0081] When the electronic control board 47 receives a calibration command, the braking device 22 switches to the passive position and the actuation device 20 is activated to achieve the desired calibration. Once the adjustment is made, the braking device 22 returns to the active position and the control unit 48 is informed of this new angular position via the communication network 49.

[0082] The control unit 48 can send either a common timing instruction to all electronic control boards (in absolute or relative mode) or a specific timing instruction to one or more electronic control boards using their identifier. The control unit 48 confirms the new angular positions to the engine control unit(s), generally on both channels of each control unit.

[0083] As an alternative to the embodiment illustrated in Figures 11 and 12, the control systems 19 can be directly controlled by one or more engine control units (ECUs). The control systems 19 can then be electrically powered, in whole or in part, by the ECU(s). Such an alternative embodiment allows the guide vanes 6 to be controlled in a common manner. To enhance the safety of the turbomachine, the rotors 26 of the electric motors 21 can be interconnected by flexible shafts, so as to synchronize all the guide vanes 6 even if one of the electric motors 21 fails.

[0084] The embodiments illustrated in Figures 1 and 2 are in no way limiting. For example, with reference to [Fig. 1], the unshod fan 3 could be arranged downstream of the gas generator 7 and the power turbine 50, the unshod rectifier 4 would then be upstream of the unshod fan 3.

Claims

Claims

1. A turbomachine (1a, 1b) for an aircraft (2) comprising: - an unducted fan (3) which is rotatable about a longitudinal axis (X); - an unducted rectifier (4) which is fixed in rotation about the longitudinal axis (X), the rectifier (4) being configured to straighten at least a portion of an airflow generated by the unducted fan (3), the rectifier (4) comprising at least one guide vane (6) with variable pitch about an axis of rotation (Y) which is substantially perpendicular to the longitudinal axis (X), the guide vane (6) being secured to a shaft (16) which is guided in rotation about the axis of rotation (Y) in a housing (17), the housing (17) being fixed to a fixed structure (18) of the turbomachine (1a, 1b);- a system (19) for adjusting the setting of the guide vane (6), the adjustment system (19) comprising a device (20) for actuating the guide vane (6) around the axis of rotation (Y), the actuating device (20) comprising an electric motor (21); characterized in that the adjustment system (19) further comprises a braking device (22) configured to occupy an active position in which the braking device (22) blocks the rotation of the guide vane (6) around the axis of rotation (Y) when the actuating device (20) is stopped, and a passive position in which the braking device (22) allows the rotation of the guide vane (6) around the axis of rotation (Y) when the actuating device (20) is running.;

2. Turbomachine (1a, 1b) according to claim 1, characterized in that the braking device (22) is mounted in the housing (17).

3. Turbomachine (1a, 1b) according to claim 2, characterized in that the shaft (16) is guided in rotation about the axis of rotation (Y) in the housing (17) via a first bearing (23) and a second bearing (24), the braking device (22) being arranged between the first bearing (23) and the second bearing (24).

4. Turbomachine (la, 1b) according to one of the preceding claims, characterized in that the electric motor (21) is mounted on an internal end of the housing (17) with reference to the longitudinal axis (X).

5. Turbomachine (1a, 1b) according to one of the preceding claims, characterized in that the braking device (22) comprises: - a caliper (29) secured to the housing (17); - a disc (30) secured to the shaft (16) and placed in the caliper (29); - a piston (31) movable in translation along the axis of rotation (Y), the piston (31) being set in motion by an electromagnetic assembly (32) which is carried by the caliper (29); - a compression spring (33) which bears both on the piston (31) and on the electromagnetic assembly (32); the disc (30) being blocked by the piston (31) under the action of the spring (33), when the braking device (22) is in the active position, the electromagnetic assembly (32) then not being electrically powered; the disc (30) being released by the piston (31) under the action of the electromagnetic assembly (32) which is electrically powered, when the braking device (22) is in the passive position, the spring (33) then being compressed by the piston (31).

6. Turbomachine (la, 1b) according to claim 5, characterized in that the piston (31) comprises a head (36) annular around the axis of rotation (Y) and several feet (37) projecting from an internal face of the head (36), each foot (37) comprising a blind orifice (38) in which is housed with play an electromagnet (39) of the electromagnetic assembly (32).

7. Turbomachine (la, 1b) according to claim 6, characterized in that the piston (31) comprises several tabs (40) projecting from a peripheral face of the head (36), each tab (40) sliding in a groove (41) formed in the caliper (29), so as to guide the piston (31) in translation relative to the caliper (29).

8. Turbomachine (1a, 1b) according to one of claims 1 to 4, characterized in that the braking device (22) is hydraulic or mechanical or electromagnetic.

9. Turbomachine (la, 1b) according to one of the preceding claims, characterized in that the actuating device (20) further comprises an epicyclic gear reducer (25) which comprises: - a sun gear (42) movable in rotation around the axis of rotation (Y) and secured to a rotor (26) of the electric motor (21); - a fixed crown (43) which surrounds the sun gear (42) and which is secured to the housing (17); - at least one satellite (44) movable in rotation, and meshed with both the sun gear (42) and the crown gear (43); - a planet carrier (45) movable in rotation around the axis of rotation (Y) and secured to the shaft (16).

10. Turbomachine (1a, 1b) according to claim 9, characterized in that the reducer (25) is mounted in the housing (17).

11. Turbomachine (la, 1b) according to claim 9 or 10, characterized in that the planet carrier (45) is made in one piece with the shaft (16).

12. Turbomachine (la, 1b) according to one of the preceding claims, characterized in that the adjustment system (19) comprises a position sensor associated with the shaft (16) or with a rotor (26) of the electric motor (21), so as to measure the setting of the guide vane (6).

13. Turbomachine (1a, 1b) according to one of the preceding claims, characterized in that the adjustment system (19) is controlled by an electronic control card (47) which is specific to the guide vane (6).

14. Turbomachine (1b) according to one of the preceding claims, characterized in that the turbomachine (1b) comprises a ducted fan (10) which is rotatable about the longitudinal axis (X) and which is surrounded by a nacelle, the nacelle (11) internally defining a compartment (12) in which the housing (17) and the adjustment system (19) are located.

Images