ACTUATOR OF A MOUNTED PART ON A ROTATING SUPPORT DRIVED BY AN AIRCRAFT TURBOMACHINE

Abstract

The actuator (110) comprises: - an epicyclic gear train (103); - a fixed support (107) integral with a planet carrier (103PS) of the epicyclic gear train (103); - an electric motor (116) for moving the workpiece (108) relative to a rotating support (104) integral with an external planetary gear (103PE) of the epicyclic gear train (103), the electric motor (116) comprising a stator (116S) carried by the rotating support (104); and - a rotating transformer (112) comprising a wound stator (112S) carried by the fixed support (107) and a rotor (112R) carried by the rotating support (104) for transferring a motor voltage (Vm~) to the electric motor (116). Figure for the abbreviation: Fig. 1

Description

Title of the invention: ACTUATOR OF A MOUNTED PART ON A ROTATING SUPPORT DRIVED BY A TURBOMACHINE OF AN AIRCRAFT Technical field of the invention

[0001] The present invention relates to an actuator for a movable part mounted on a rotating support driven by an aircraft turbomachine. It is particularly applicable for setting the pitch of blades or rotor blades. Technological background

[0002] The French patent application published under number FR 2 831 225 A1 describes an actuator for a movable part mounted on a rotating support driven by a turbomachine of an aircraft, comprising: - a main electrical machine comprising a rotor supported by the rotating support and a wound stator attached to a fixed external structure of the turbomachine; and - an electric motor for moving the part relative to the rotating support, the electric motor having a stator carried by the rotating support.

[0003] More specifically, this known actuator is designed to change the orientation of the blades of a propeller mounted on the rotating support. Furthermore, in the previous publication, the electric motor is powered through a rotating transformer having a stator inductor fixed to the external fixed structure of the turbomachine and controlled by an electronic control circuit connected by a power link to an electrical power supply device for the turboprop.

[0004] Thus, this known actuator requires power transfer through the rotating transformer with a large radius, which necessitates the use of bulky coils. Furthermore, the rotor and stator of the rotating transformer are in the form of two rings facing each other, which hinders the integration of the actuator.

[0005] It may therefore be desirable to design an actuator where the power supply device is directly supported by the rotating support and with a low radius, thus alleviating all or part of the aforementioned constraints. Summary of the invention

[0006] An electrohydraulic or electromechanical actuator for a movable part mounted on a rotating support driven by an aircraft turbomachine is therefore proposed, characterized in that it comprises: - an epicyclic gear train comprising: • an internal planetary gear designed to be driven by the turbomachine, rotating around a main axis relative to a structural part of the aircraft, • an external planetary gear mounted to rotate around the main axis relative to the structural part of the aircraft, the rotating support being integral with the external planetary gear, • a satellite carrier attached to the structural part of the aircraft, • at least one satellite geared to both the inner planetary system and with the outer planetary gear; - a fixed support attached to the satellite carrier; - an electric motor for moving the part relative to the rotating support, the electric motor comprising a stator carried by the rotating support; - a rotating transformer which includes a wound stator carried by the fixed support and a rotor carried by the rotating support to transfer electrical power to the electric motor.

[0007] Thanks to the invention, it is possible to place the stator of the rotating transformer on the main axis of the turbomachine with its rotor rotating around it, which simplifies its integration.

[0008] Optionally, the actuator further comprises a DC electrical network of the aircraft and a DC-AC converter designed to supply voltage to the stator of the rotating transformer.

[0009] Optionally, the actuator also includes a motor voltage regulation device.

[0010] Optionally, a regulation device is also designed to regulate the motor voltage by controlling the DC-AC converter.

[0011] Optionally, the actuator also includes a device for measuring the orientation of the part and the control device is designed to regulate the motor voltage from the measured orientation and an orientation setpoint.

[0012] Optionally, the electric motor is also asynchronous.

[0013] A propulsion system for an aircraft is also proposed, comprising: - a turbomachine with a rotating shaft; - a propeller or blower mounted on the rotating support and having blades or dawns; and - an actuator for the blades or vanes, according to the invention.

[0014] An aircraft comprising a propulsion system according to the invention is also proposed. Brief description of the figures

[0015] The invention will be better understood with the aid of the following description, given solely by way of example and made with reference to the accompanying drawings in which: - [Fig. 1] is a simplified view of an example of an aircraft propulsion system comprising an example of an actuator according to the invention, - [Fig. 2] is a simplified view of an example of a motion converter that can be used in the actuator of [Fig. 1], and - [Fig.3] is a simplified view of another example of a motion converter that can be used in the actuator of [Fig.1]. Detailed description of the invention

[0016] With reference to [Fig.1], an example of an aircraft propulsion system 100, in which the invention is implemented, will now be described.

[0017] The propulsion system 100 comprises first of all a turbomachine 102.

[0018] The propulsion system 100 further comprises an epicyclic gear train 103 comprising First, there is an inner planetary gear 103P. This is driven by the turbomachine 102, rotating about a main axis P relative to a structural part 105 of the aircraft. The planetary gear train 103 further comprises at least one planet 103S and a planet carrier 103PS attached to the structural part 105 of the aircraft and supporting each planet 103S. The planetary gear train 103 also includes an outer planetary gear 103PE mounted to rotate about the main axis P relative to the structural part 105 of the aircraft. Each planet 103S is meshed with both the inner planetary gear 103PI and the outer planetary gear 103PE. In this way, the rotation of the inner planetary gear 103PI drives the rotation of the outer planetary gear 103PE, with a certain drive ratio.

[0019] The propulsion system 100 further comprises a rotating support 104 attached to the outer planetary gear 103PE and a fixed support 107 attached to the satellite carrier 103PS, both located on the opposite side of the satellite carrier 103PS from the turbomachine 102. Thus, the fixed support 107 forms a fixed frame of reference and the rotating support 104 forms a rotating frame of reference.

[0020] The propulsion system 100 further comprises a propeller 106 mounted on the rotating support 104. The propeller 106 comprises blades 108. The terms propeller and blades also respectively cover a blower and the blades of this blower.

[0021] In order to change their orientation relative to the rotating shaft 104, the blades 108 are mounted movable relative to the rotating support 104. More precisely, in the illustrated example, they are mounted pivotally around respective radial axes A.

[0022] In order to control the orientation of the blades 108, the propulsion system 100 further includes an actuator 110. This actuator 110 is particularly suitable for ducted or unducted turbomachine architectures (USF). Single Fan”, VPF from English “Variable Pitch Fan”).

[0023] The actuator 110 first comprises a three-phase or single-phase rotating transformer 112. It thus includes a rotor 112R carried by the rotating support 104 and a stator 112S carried by the fixed support 107. In particular, the stator 112S is located on the main axis P, and the rotor 112R extends around the main axis P to rotate around it. The stator 112S is designed to receive electrical energy and to transmit it to the rotor 112R, regardless of the angle of rotation between them. For example, the stator 112S of the main rotating transformer 112 receives electrical energy from a DC power supply 115 of the aircraft, via a DC-AC converter 117 (inverter). The DC power supply 115 and the inverter 117 are located in the fixed frame of reference. The routing of electrical harnesses to the rotating transformer 112 can be provided through the fixed satellite carrier 103PS.

[0024] The actuator 110 further comprises an electric motor 116 for blade pitch control 108, having a stator 116S and a rotor 116R. This is, for example, an asynchronous electric motor, such as a squirrel-cage motor. The electric pitch control motor 116 is supported by the rotary support 104, which means in particular that its stator 116S is supported by the rotary support 104 and that the rotor 116R is designed to rotate relative to the stator 116S and therefore relative to the rotary support 104.

[0025] The electric timing motor 116, and more particularly its stator 116S, is electrically powered by the rotor 112R of the main rotating transformer 112, in order to rotate the rotor 116R. The electrical connection between the rotor 112R and the electric timing motor 116 is carried by the rotating support 104, without returning in particular to the fixed reference frame.

[0026] The actuator 110 further includes a motion converter 124, carried by the rotating support 104 (and therefore in the rotating frame) designed to convert the rotation of the rotor 116R into a movement of the blades 108. Examples of motion converter 124 will be described later.

[0027] To control the change in the orientation of the blades 108, the actuator 110 may further include a device 126 for measuring the orientation of the blades 108 and a device 128 for regulating the motor voltage Vm~ (in particular, its level and / or frequency) to control the electric pitching motor 116 based on the measured orientation of the blades 108 and a setpoint C for the orientation of the blades 108. The control is, for example, vector or scalar. The control device 128 is, for example, designed to regulate the motor voltage Vm~ by controlling the inverter 117.

[0028] Furthermore, by attaching the fixed support 107 to the satellite carrier 103PS and the mobile support 104 to the outer planetary gear 103PE, it is possible to position the fixed support 107 on the main shaft P, with the rotating support 104 around it. The stator 112S of the main rotating transformer 112 can thus be placed on the main shaft P with its rotor 112R around it.

[0029] With reference to [Fig.2], a first example of a motion converter 124 will now be described in more detail.

[0030] In this first example, the motion converter 124 includes a hydraulic pump 202 driven by the rotor 116R of the electric timing motor 116. The hydraulic pump 202 is, for example, of fixed displacement, which allows it to be robust.

[0031] The motion converter 124 further comprises a hydraulic cylinder 204 having two chambers separated by a piston 205 and actuated by the hydraulic pump 202.

[0032] When the rotor 116R of the electric timing motor 116 rotates in one direction, the hydraulic pump 202 fills the first chamber to move the piston 205 in one direction. When the rotor 116R of the electric motor 116 rotates in the other direction, the hydraulic pump 202 fills the second chamber to move the piston 205 in the opposite direction.

[0033] The motion converter 124 further includes a mechanism 206 for transforming the translational movement of the hydraulic cylinder 204 into a rotational movement of the blade 108 around the axis A.

[0034] With reference to [Fig.3], a second example of a motion converter 124 will now be described in more detail.

[0035] This second example is similar to the first example in [Fig.2], except that the hydraulic pump 202 and the hydraulic cylinder 204 are replaced by a ball screw 302 carrying a nut that translates in one direction and in the opposite direction according to the direction of rotation of the rotor 116R of the electric timing motor 116.

[0036] It should be noted that the invention is not limited to the embodiments described above. It will indeed be apparent to those skilled in the art that various modifications can be made to the embodiments described above, in light of the information just disclosed to them.

[0037] In the detailed presentation of the invention given above, the terms used shall not be interpreted as limiting the invention to the embodiments set forth in this description, but shall be interpreted as including all equivalents which can be foreseen by a person skilled in the art by applying their general knowledge to the implementation of the teaching which has just been disclosed to them.

Claims

1.

2. Demands Device comprising a rotating support (104) driven by a turbine (102) of an aircraft and an actuator (110) of a part (108) movably mounted on the rotating support (104), the actuator (110) comprising: - an epicyclic gear train (103) comprising: • an internal planetary gear (103PI) designed to be driven by the turbomachine (102), rotating about a main axis (P) relative to a structural part (105) of the aircraft, • an external planetary gear (103PE) mounted to rotate about the main axis (P) relative to the structural part (105) of the aircraft, the rotating support (104) being integral with the external planetary gear (103PE), • a satellite carrier (103PS) integral with the structural part (105) of the aircraft, • at least one satellite (103S) meshed with both the inner planetary (103PI) and the outer planetary (103PE); - a fixed support (107) attached to the satellite carrier (103PS); - an electric motor (116) for moving the part (108) relative to the rotating support (104), the electric motor (116) comprising a stator (116S) carried by the rotating support (104); and - a rotating transformer (112) which includes a stator (112S) wound carried by the fixed support (107) and a rotor (112R) carried by the rotating support (104) to transfer a so-called motor voltage (Vm~) to the electric motor (116), the stator (112S) being placed on the main axis (P) and the rotor (112R) extending around the main axis (P) to rotate around the latter. Device according to claim 1, wherein the actuator (110) further comprises a DC electrical network (115) of the aircraft and a DC-AC converter (117) designed to supply the voltage (Vm~) to the stator (112S) of the rotating transformer (112).

3. Device according to claim 1 or 2, wherein the actuator (110) further comprises a motor voltage regulation device (128).

4. Device according to claim 3, wherein the regulating device (128) is designed to regulate the motor voltage (Vm~) by controlling the DC-AC converter (117).

5. Device according to claim 3 or 4, wherein the actuator (110) further comprises a device (126) for measuring an orientation of the part (108) and wherein the control device (128) is designed to regulate the motor voltage (Vm~) from the measured orientation and an orientation setpoint (C).

6. Device according to any one of claims 1 to 5, wherein the electric motor (116) is asynchronous.

7. Aircraft propulsion system (100), comprising: - a turbomachine (102) having a rotating support (104); - a propeller or fan (106) mounted on the rotating support (104) and having blades or vanes (108); and - a device according to any one of claims 1 to 6, wherein the actuator (110) is designed to actuate the blades or vanes (108).

8. Aircraft comprising a propulsion system (100) according to claim 7.

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