Turbine engine comprising actuator and aircraft comprising such turbine engine and corresponding actuation method
By designing an actuator including cylinders, pistons and bidirectional servo valves, the problem of rapid movement of the actuator in the aircraft is solved, and reliable actuation in high temperature and vibration environments is achieved, simplifying the design and reducing fuel demand.
Patent Information
- Application Number
- CN202380085350.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Priority Date
- 2022-12-13
- Filing Date
- 2023-12-01
- Publication Date
- 2025-07-22
AI Technical Summary
It is difficult for existing actuators to achieve rapid movement power in aircraft, and fuel actuators have problems such as large fuel demand, excessive machine size, high leakage risk, and difficulty in integrating in high temperature and vibration environments.
The actuator design is adopted including cylinders, pistons, fluid pipelines and bidirectional servo valves. The large cross-sectional area of the bidirectional servo valve and the difference in head loss are used to achieve rapid movement of the piston and is compatible with the thermal and vibration conditions of the aircraft.
Fast and reliable actuator movement in the aircraft is achieved, simplifying design and reducing fuel demands, adapting to high temperature and vibration environments.
Smart Images
Figure CN120359357A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of fast actuators.
[0002] In particular, the present invention relates to an actuator, a turbomachine and an aircraft comprising such an actuator, as well as a corresponding actuation method. Prior Art
[0003] Some applications (especially aircraft applications) require actuators to have fast movement power, while certain actuators do not have such fast movement power.
[0004] For example, the movement power of an electro-pneumatic actuator is slower than that of a fuel actuator.
[0005] A fuel actuator is, for example, a hydraulic actuator controlled by a pressure obtained from a fuel circuit supplying a gas turbine combustion.
[0006] Installing a fuel actuator on a machine requires a complex machine architecture. The fuel requirement of the fuel actuator may lead to an oversized fuel circuit of the machine, and this oversized dimension may cause leakage or injection effects.
[0007] The machine may generate an environment of high temperature and strong vibration, making it difficult to integrate the actuator and may hinder the implementation of certain types of actuators (such as electric actuators). Summary of the Invention
[0008] Therefore, an object of the present invention is to overcome all or some of the above-mentioned drawbacks and to provide an actuator having a fast movement power compatible with the thermal and vibration conditions of an aircraft.
[0009] An object of the present invention is an actuator comprising a cylinder, the cylinder comprising a rod provided with a piston, the piston at least partially defining a first chamber and a second chamber, the actuator comprising a first fluid line and a second fluid line fluidly connected to the first chamber, an elastic return device being arranged in one of the first chamber and the second chamber in a predetermined position and being configured to exert a force on the piston, the first fluid line comprising a calibration port, the actuator comprising a two-way servo valve fluidly connected to the second fluid line, the cross-sectional area of the two-way servo valve being greater than or equal to ten times the cross-sectional area of the calibration port, or the head loss in the first fluid line being greater than or equal to ten times the head loss in the second fluid line.
[0010] Compared with the reduced cross-sectional area of the calibration port, the larger cross-sectional area of the servo valve enables a greater power for the movement of the piston in a first direction (especially when the elastic device returns to the predetermined position), as well as a lower power for another movement of the piston in a second direction opposite to the first direction.
[0011] Using a two-way servo valve ensures a simple actuator design.
[0012] The actuator design is compatible with the thermal and vibration conditions of the aircraft.
[0013] The actuator may include a common pipeline leading to the first chamber, and the first fluid pipeline and the second fluid pipeline are fluidly connected to the common pipeline.
[0014] The two-way servo valve may include an electromagnetic control member.
[0015] In one embodiment, the two-way servo valve is configured to have at least one passage state and a blocked state. The passage state enables fluid to flow through the two-way servo valve into the second fluid pipeline, and the blocked state prevents fluid from flowing through the two-way servo valve into the second fluid pipeline.
[0016] The two-way servo valve may include a proportional control member configured to position the piston at an intermediate position of the piston stroke.
[0017] The piston may be associated with a sealed rolling diaphragm to seal the first chamber and the second chamber.
[0018] The cross-sectional area of the two-way servo valve may be more than twenty times the cross-sectional area of the calibration port.
[0019] Another object of the present invention is a turbine engine, which includes an actuator as previously defined, a first fluid source and a second fluid source. One of the first fluid pipeline and the second fluid pipeline is configured to obtain a first fluid from the first fluid source, and the other fluid pipeline is configured to obtain a second fluid from the second fluid source. The pressure of the first fluid is greater than the pressure of the second fluid.
[0020] The first fluid source may include a compressor, and the second fluid includes air at atmospheric pressure.
[0021] Another object of the present invention is an aircraft, which includes an actuator as defined above and / or a turbine engine as defined above.
[0022] Another object of the present invention is an actuation method, which is implemented by the actuator as defined above, or by the turbine engine as defined above, or by the actuator included in the aircraft as defined above. The actuation method includes the following steps:
[0023] - Changing the state of the two-way servo valve so that the two-way servo valve is in a first state;
[0024] - Move the piston and the rod in a first direction at a first speed, said movement being caused by a first difference in the forces acting on the piston, said first difference depending at least on the pressure in the first chamber and the force exerted by the elastic return means on the piston;
[0025] and / or
[0026] - Change the state of the two-way servo valve such that the two-way servo valve is in a second state; and
[0027] - Move the piston and the rod in a second direction opposite to the first direction at a second speed different from the first speed, said movement being caused by a second difference in the forces acting on the piston, said second difference depending at least on the pressure in the first chamber and the force exerted by the elastic return means on the piston. Description of the Drawings
[0028] Other objects, features and advantages of the present invention will become apparent upon reading the following description, which is given by way of non-limiting example only and with reference to the accompanying drawings, in which:
[0029] Figure 1 schematically shows an aircraft comprising a turbomachine and an actuator according to the present invention;
[0030] Figure 2 schematically shows an actuator according to a first embodiment of the present invention;
[0031] Figure 3 schematically shows an actuator according to a second embodiment of the present invention; and
[0032] Figure 4 schematically shows an actuation method according to the present invention. Detailed Description
[0033] Figure 1 Schematically shown is an aircraft 2 (e.g., a helicopter or an airplane), which includes an auxiliary turbine engine 4 (e.g., a turbine engine of an auxiliary power unit (or APU, Auxiliary Power Unit)). Such an auxiliary turbine engine 4 is different from the turbine engine dedicated to propelling the aircraft. However, like the turbine engine, such an auxiliary turbine engine includes movable members that need to be actuated. These movable members (also called "variable geometry") are, for example, inlet guide vanes (or IGV, Inlet Guide Vanes) and / or anti-pump valves. The aircraft 2 includes, for example, a start valve that needs to be actuated and / or an auxiliary power unit for regulating pressurized air. Thus, the aircraft includes at least one actuator 6. However, the use of the actuator 6 according to the present invention is not limited to the scope of the auxiliary turbine engine 4. The actuator 6 can be implemented in the turbine engine of the main engine (that is, dedicated to propelling the aircraft), or in the air system (air conditioning, de-icing, etc.) of the aircraft that obtains pressurized air from the turbine engine.
[0034] Figure 2 Schematically shown is a first embodiment of the actuator 6.
[0035] The actuator 6 includes a cylinder 8, which includes a rod 10 provided with a piston 12. The piston 12 defines a first chamber 14 and a second chamber 16 within the cylinder 8. The rod 10 is configured to perform a longitudinal movement within the cylinder 8. In the example shown, the rod 10 extends from the piston 12 into the second chamber 16 and passes through a first wall 18 of the cylinder 8. Alternatively, the rod 10 can extend from the piston 12 into the first chamber 14 and pass through a second wall 20 of the cylinder 8 opposite to the first wall 18. The cylinder 8 then includes a sealing element to ensure the sealing of the first chamber 14 at the second wall 20.
[0036] The cylinder 8 includes a first fluid line 22 fluidly connected to the first chamber 14, and the first fluid line 22 is directly connected to the first chamber 14 here. The cylinder 8 includes a second fluid line 24 fluidly connected to the first chamber 14, and the second fluid line 24 is directly connected to the first chamber 14 here.
[0037] The cylinder 8 includes an elastic return device 26, which is disposed in the second chamber 16 at a predetermined position and is capable of applying a force to the piston 12. The elastic return device 26 includes, for example, a helical spring around the rod 10 to apply a longitudinal force to the piston 12 during the longitudinal movement of the piston 12. Alternatively, the elastic return device 26 can be disposed in the first chamber 14.
[0038] The first fluid line 22 and the second fluid line 24 are, for example, tubular pipes with a constant cross-section.
[0039] The first fluid line 22 includes a calibration port 28 which includes, for example, a restriction port that locally reduces the cross-section of the first fluid line 22 such that the first fluid line 22 locally has a smaller cross-section than the constant cross-section of the second fluid line 24. The calibration port 28 is particularly capable of changing the pressure and / or flow rate of the fluid flowing in the first fluid line 22, which fluid is preferably gaseous. The actuator 6 includes a two-way servo valve 30 fluidly connected to the second fluid line 24. In a particular embodiment, the two-way servo valve 30 is directly connected to the second fluid line 24 such that the fluid flowing from the first end 32 of the second fluid line 24 to the second end 34 of the second fluid line 24 necessarily flows through the two-way servo valve 30, the first end 32 being directly connected to the first chamber 14 here.
[0040] The flow of fluid through the first fluid line 22 is restricted by the cross-sectional area of the calibration port 28, and the flow of fluid through the second fluid line 24 is restricted by the cross-sectional area of the two-way servo valve 30, the cross-sectional area of the two-way servo valve 30 being greater than or equal to ten times the cross-sectional area of the calibration port. Alternatively, if the head loss in the first fluid line 22 is greater than or equal to ten times the head loss in the second fluid line 24, the ratio of the two cross-sectional areas may be less than ten.
[0041] Preferably, the two-way servo valve 30 includes an electromagnetic control 36. The electromagnetic control 36 does not take up much space, requires low electrical operating power, and provides high responsiveness. Alternatively, the two-way servo valve 30 may include a hydraulic or electrical control.
[0042] In this first embodiment, the two-way servo valve 30 includes only a first state and a second state. For example, the first state corresponds to the passing state of the two-way servo valve 30 (that is, the state in which fluid can flow through the two-way servo valve 30 and thus through the second fluid line 24), and the second state corresponds to the blocking state of the two-way servo valve 30 (that is, the state in which fluid cannot flow through the two-way servo valve 30 and thus through the second fluid line 24).
[0043] Advantageously, the piston 12 includes a sealing element configured to prevent fluid from flowing between the first chamber 14 and the second chamber 16. In the example shown, the actuator 6 includes a sealed rolling diaphragm 38 associated with the piston 12, the piston 12 and the rolling diaphragm 38 defining the first chamber 14 and the second chamber 16 and preventing fluid transfer between the first chamber 14 and the second chamber 16.
[0044] The actuator 6 includes a first fluid source 40 and a second fluid source 42.
[0045] The first fluid line 22 is capable of obtaining a first fluid under a first pressure. The first fluid is, for example, air under high pressure, in particular air having a pressure at least twice that of air under atmospheric pressure. The first fluid is taken, for example, from a first fluid source 40. Preferably, the first fluid source 40 is located near the actuator 6 to reduce the length of the first fluid line 22. In the example shown, the first fluid is taken from the compressor (not shown) of the propulsion motor of the aircraft 2. Alternatively, the first fluid may be taken from another fluid source of the propulsion motor, for example, from a blower.
[0046] Advantageously, the calibration port 28 of the first fluid line 22 results in little interference of the actuator 6 with the first fluid source 40. Then, the first fluid line 22 takes a small amount of fluid from the first fluid source 40, and the energy requirement of the first fluid source 40 increases slightly.
[0047] The second fluid line 24 is capable of obtaining a second fluid under a second pressure. The second fluid is taken, for example, from a second fluid source 42. In the example shown, the second fluid source 42 is the atmosphere, and the second fluid is the air in which the aircraft 2 moves. Therefore, the pressure of the second fluid is lower than that of the first fluid. Then, the second fluid line 24 discharges the fluid from the first chamber 14 and the first fluid line 22 to the atmosphere.
[0048] When the two-way servo valve 30 is in the blocked state, the flow rate of the fluid flowing in the second fluid line 24 is zero or very low, and only the first fluid line 22 can inject the pressurized fluid into the first chamber 14. When the first fluid is injected into the first chamber 14, the pressure in the first chamber 14 increases. Therefore, a force is exerted on the piston 12 against the elastic return device 26 and the external force of the member controlled by the actuator 6. If the force exerted by the pressure in the first chamber 14 on the piston is high enough, the piston 12 moves in the direction of the first wall 18. This movement continues until the forces on the piston 12 reach equilibrium, and these forces depend on the force exerted by the elastic return device 26 on the piston 12, the flow rate of the fluid flowing in the first fluid line 22, and the flow rate of the fluid flowing in the second fluid line 24.
[0049] When the two-way servo valve 30 is in the passing state, the fluid contained in the first chamber 14 can flow from the first end 32 of the second fluid line 24 to the second end 34 of the second fluid line 24. If the fluid pressure in the first chamber 14 is high enough, the fluid contained in the first chamber 14 will suddenly escape from the first chamber 14 through the second fluid line 24, and then the pressure in the first chamber 14 will rapidly drop. Then, the force exerted by the elastic reset device 26 on the piston 12 is greater than the force exerted by the fluid pressure in the first chamber 14 on the piston 12. Then, the piston 12 moves rapidly towards the second wall 20 of the cylinder 20, and the rapid movement of the piston 12 depends at least on the force exerted by the elastic reset device 26 on the piston 12, the cross-sectional area difference between the first fluid line 22 and the second fluid line 24 connected to the calibration port 28 and the two-way servo valve 30, and the external force of the member controlled by the actuator 6. This movement continues until the forces on the piston 12 reach equilibrium, and these forces depend on the force exerted by the elastic reset device 26 on the piston 12, the flow rate of the fluid flowing in the first fluid line 22, and the flow rate of the fluid flowing in the second fluid line 24.
[0050] In Figure 2 the example, the movement of the piston 12 towards the first wall 18 when the two-way servo valve 30 changes from the passing state to the blocking state is slower than the movement of the piston 12 towards the second wall 20 when the two-way servo valve 30 changes from the blocking state to the passing state. The speed difference between these two movements mainly depends on the ratio between the section of the first fluid line 22 including the calibration port 28 and the section of the second fluid line 24 including the two-way servo valve 30, and on the ratio between the first pressure and the second pressure. The stiffness of the elastic reset device 26 may also affect this speed difference. When the two-way servo valve 30 changes to the passing state, since the cross-sectional area of the two-way servo valve 30 is greater than or equal to ten times the cross-sectional area of the calibration port 28, the highest speed of the piston 12 moving towards the second wall 20 is guaranteed. Simultaneously or alternatively, in order to ensure the desired speed difference between these two movements, it can be stipulated that the head loss in the first fluid line 22 is greater than or equal to ten times the head loss in the second fluid line 24. Optionally, the cross-sectional area of the two-way servo valve 30 is greater than twenty times the cross-sectional area of the calibration port 28 to ensure that the movement of the piston 12 towards the second wall 20 when the two-way servo valve 30 changes to the passing state is much faster than the movement of the piston 12 towards the first wall 18 when the two-way servo valve 30 changes to the blocking state. For example, the cross-sectional area of the two-way servo valve 30 is approximately twenty-five times the cross-sectional area of the calibration port 28.
[0051] Preferably, the cylinder 8 includes a position sensor 44 for measuring the position of the rod 10 of the cylinder 8, and the actuator 6 includes a control unit 46 configured to issue a control signal to control the state of the two-way servo valve 30. For example, the position sensor 44 transmits the position of the rod 10 of the cylinder 8 to the control unit 46, and the control unit 46 issues a control signal based on the transmitted position.
[0052] Advantageously, the two-way servo valve 30 is configured such that in the absence of a control signal (e.g., during an electrical failure of the control unit 46 or the two-way servo valve 30), the actuator 6 is placed in a rest position that enables the risk of damage to the actuator 6 and / or the turbomachine 4 and / or the aircraft 2 to be reduced by positioning the rod 10 of the cylinder 8 in a position that is particularly suitable for dealing with safety issues. For example, the two-way servo valve 30 is configured to be in a passage state in the absence of control to quickly place the actuator 6 in the rest position.
[0053] Figure 3 A second embodiment of the actuator 6 is schematically shown.
[0054] The actuator 6 includes a common line 48 leading to the first chamber 14. The first fluid line 22 and the second fluid line 24 are fluidly connected to the common line 48, and the first end 32 of the second fluid line 24 is directly connected to the common line 48. This embodiment simplifies the embodiment of the actuator 6 and is also compatible with Figure 2 the embodiment of
[0055] The first fluid line 22 is capable of receiving a second fluid at a second pressure from a second fluid source 42, and the second fluid line 24 is capable of receiving a first fluid at a first pressure from a first fluid source 40. The first fluid line 22 includes a calibration port 28.
[0056] The two-way servo valve 30 includes a passage state and a blocking state.
[0057] Advantageously, the two-way servo valve 30 is configured to be in a blocking state in the absence of control to quickly place the actuator 6 in the rest position.
[0058] When the two-way servo valve 30 is in the passing state, the first fluid obtained from the first fluid source 40 can flow from the second end 34 of the second fluid pipeline 24 to the first end 32 of the second fluid pipeline 24, and then from the first end 32 of the second fluid pipeline 24 to the first chamber 14. If the pressure of the first fluid is sufficient, the first fluid will suddenly enter the first chamber 14, and then the pressure in the first chamber 14 will increase rapidly. Thus, the force exerted on the piston 12 by the fluid pressure in the first chamber 14 is greater than the sum of the force exerted on the piston 12 by the elastic reset device 26 and the external force of the member controlled by the actuator 6. Then, the piston 12 moves rapidly towards the first wall 18 of the cylinder 8, and this rapid movement is carried out against the force exerted on the piston 12 by the elastic reset device 26. This movement continues until the forces on the piston 12 reach equilibrium, and these forces depend on the force exerted on the piston 12 by the elastic reset device 26, the flow rate of the fluid flowing in the first fluid pipeline 22, and the flow rate of the fluid flowing in the second fluid pipeline 24.
[0059] When the two-way servo valve 30 is in the blocked state, the flow rate of the fluid flowing in the second fluid pipeline 24 is zero or very low, and only the first fluid pipeline 22 can allow the fluid in the first chamber 14 to escape from the cylinder 8. When the fluid in the first chamber 14 escapes from the first chamber 14 through the first fluid pipeline 22, the pressure in the first chamber 14 decreases. If the force exerted on the piston 12 by the elastic reset device 26 is high enough relative to the force exerted on the piston 12 by the fluid pressure in the first chamber 14, the piston 12 moves in the direction of the second wall 20. This movement continues until the forces on the piston 12 reach equilibrium, and these forces depend on the force exerted on the piston 12 by the elastic reset device 26, the flow rate of the fluid flowing in the first fluid pipeline 22, and the flow rate of the fluid flowing in the second fluid pipeline 24.
[0060] In Figure 3In the example, when the two-way servo valve 30 changes to the passing state, the movement of the piston 12 towards the first wall 18 is faster than the movement of the piston 12 towards the second wall 20 when the two-way servo valve 30 changes to the blocking state. When the two-way servo valve 30 changes to the passing state, since the cross-sectional area of the two-way servo valve 30 is greater than or equal to ten times the cross-sectional area of the calibration port 28, the highest speed of the piston 12 moving towards the first wall 18 is ensured. Simultaneously or alternatively, in order to ensure the desired speed difference between these two movements, it can be stipulated that the head loss in the first fluid line 22 is greater than or equal to ten times the head loss in the second fluid line 24. The head loss in the common line 48 will preferably be comparable to or lower than the head loss in the second fluid line 24. Optionally, the cross-sectional area of the two-way servo valve 30 is greater than twenty times the cross-sectional area of the calibration port 28 to ensure that when the two-way servo valve 30 changes to the passing state, the movement of the piston 12 towards the first wall 18 is much faster than the movement of the piston 12 towards the second wall 20 when the two-way servo valve 30 changes to the blocking state.
[0061] Advantageously, the two-way servo valve 30 includes a proportional control member 50 that can position the piston 12 at the middle position of the piston 12 stroke. For example, the control unit 46 of the actuator 6 controls the proportional control member 50 of the two-way servo valve 30 in the intermediate flow state to control the flow of air through the two-way servo valve 30 and thus through the second fluid line 24.
[0062] The control unit 46 is configured to servo-control the piston 12 of the cylinder 8 in place. The control unit 46 includes a control algorithm for servo-controlling the position of the piston 12, particularly servo-controlling the position of the piston according to the position data of the position sensor 44. The control unit 46 enables the piston 12 to be quickly positioned at the middle position of the piston 12 stroke.
[0063] The two-way servo valve 30 cooperates with the first fluid line 22 and the second fluid line 24, and cooperates with the elastic return device 26 to place the piston 12 at the middle position of the piston 12 stroke when the two-way servo valve 30 is in the intermediate flow state.
[0064] When the two-way servo valve 30 is in the intermediate flow state, the middle position corresponds to the balance of the forces applied to the piston 12, and this balance of the forces applied to the piston depends on the stiffness of the elastic return device 26, the flow velocity of the fluid flowing in the first fluid line 22, and the flow velocity of the fluid flowing in the second fluid line 24.
[0065] Figure 4 The actuation method implemented by the actuator 6 is schematically shown.
[0066] During the first state change step 52 of the two-way servo valve 30, the operating state of the two-way servo valve 30 is modified such that the two-way servo valve 30 is in the first state.
[0067] The first state includes, for example, the passing state, or the blocking state, or the intermediate flow state of the two-way servo valve 30.
[0068] Subsequently, during the first step 54 of moving the piston 12, the piston 12 and the rod 10 of the cylinder 8 move in the first direction at a first speed, for example, to move the piston 12 closer to the first wall 18 or closer to the second wall 20. The movement of the piston 12 during step 54 is caused by a first difference in the forces acting on the piston 12, which depends at least on the pressure in the first chamber 14 and the force exerted on the piston 12 by the elastic return device 26. External acting forces should also be considered, for example, the external acting forces of the members controlled by the actuator 6. Preferably, when the forces acting on the piston 12 reach equilibrium, the movement of the piston 12 during step 54 ends.
[0069] As a result, during the second state change step 56 of the two-way servo valve 30, the operating state of the two-way servo valve 30 is modified such that the two-way servo valve 30 is in the second state.
[0070] The second state includes, for example, the passing state, or the blocking state, or the intermediate flow state of the two-way servo valve 30.
[0071] Finally, during the second step 58 of moving the piston 12, the piston 12 and the rod 10 of the cylinder 8 move in the second direction opposite to the first direction at a second speed, for example, to move the piston 12 closer to the second wall 20 or closer to the first wall 18. The movement of the piston 12 during step 58 is caused by a second difference in the forces acting on the piston 12, which depends at least on the pressure in the first chamber 14 and on the force exerted on the piston 12 by the elastic return device 26, not to mention the external forces. Preferably, when the forces acting on the piston 12 reach equilibrium, the movement of the piston 12 during step 58 ends.
[0072] For example, step 52 includes, in Figure 2 the case of the example of the embodiment, when the piston 12 is in the established passing state position corresponding to the end of the first instantaneous speed of the piston 12 movement, changing the two-way servo valve 30 from the passing state to the blocking state. Then, step 54 includes moving the piston 12 from the established passing state position towards the first wall of the cylinder 18, and when the piston 12 is in the established blocking state position corresponding to the end of the second instantaneous speed of the piston 12 movement, the movement of the piston 12 ends.
[0073] For example, step 56 includes, in Figure 2In the case of an example of an embodiment, when the piston 12 is in a given blocked state position, the two-way servo valve 30 is changed from the blocked state to the passing state. Then, step 58 includes moving the piston 12 from the given blocked state position towards the second wall of the cylinder 20, and the movement of the piston 12 ends when the piston 12 is in the given passing state position. In this example, the movement of the piston 12 during step 54 is slower than the movement of the piston during step 58.
[0074] Of course, step 54 and step 58 may include moving the piston 12 from an intermediate position of the stroke of the piston 12 to another position, or moving the piston 12 from another position to the intermediate position of the stroke of the piston 12, or include any other movement of the piston 12.
[0075] This actuation method sequentially includes steps 52, 54, 56, and 58. Alternatively, such an actuation method may only include steps 52 and 54 or 56 and 58. Alternatively, the method may also sequentially include steps 56, 58, 52, and 54.
Claims
1. A turbine engine (4), the turbine engine comprising an actuator (6), the actuator comprising a cylinder (8), the cylinder comprising a rod (10) provided with a piston (12), the piston at least partially defining a first chamber and a second chamber (14, 16) within the cylinder (8), the actuator (6) comprising a first fluid line and a second fluid line (22, 24) fluidly connected to the first chamber (14), an elastic return device (26) being disposed in one of the first chamber and the second chamber (14, 16) in a predetermined position and configured to apply a force to the piston (12), the first fluid line (22) comprising a calibration port (28), the actuator (6) comprising a two-way servo valve (30) fluidly connected to the second fluid line (24), the cross-sectional area of the two-way servo valve (30) being greater than or equal to ten times the cross-sectional area of the calibration port (28), or the head loss in the first fluid line (22) being greater than or equal to ten times the head loss in the second fluid line (24), the turbine engine (4) comprising a first fluid source (40) and a second fluid source (42), one of the first fluid line and the second fluid line (22, 24) being configured to obtain a first fluid from the first fluid source (40), the other fluid line (24, 22) being configured to obtain a second fluid from the second fluid source (42), the pressure of the first fluid being greater than the pressure of the second fluid, characterized in that, The first fluid source (40) includes a compressor of the turbomachine (4), and the second fluid includes air at atmospheric pressure.
2. The turbine engine (4) according to claim 1, wherein, The actuator (6) includes a common line (48) leading to the first chamber (14), and the first fluid line and the second fluid line (22, 24) are fluidly connected to the common line (48).
3. A turbine engine (4) according to one of claims 1 and 2, wherein, The two-way servo valve (30) includes an electromagnetic control member (36).
4. The turbomachine (4) according to any one of claims 1 to 3, wherein, The two-way servo valve (30) is configured to have: at least one passage state and a blocked state, the at least one passage state enabling fluid to flow through the two-way servo valve (30) into the second fluid line (24), and the blocked state preventing fluid from flowing through the two-way servo valve (30) into the second fluid line (24).
5. A turbomachine (4) according to any one of claims 1 to 4, wherein, The two-way servo valve (30) includes a proportional control member (50) configured to position the piston (12) at an intermediate position of the stroke of the piston (12).
6. The turbomachine (4) according to any one of claims 1 to 5, wherein, The piston (12) is associated with a sealed rolling diaphragm (38) to sealably separate the first chamber and the second chamber (14, 16).
7. The turbomachine (4) according to any one of claims 1 to 6, wherein, The cross-sectional area of the two-way servo valve (30) is more than twenty times the cross-sectional area of the calibration port (28).
8. An aircraft (2) comprising a turbomachine (4) according to any one of the preceding claims.
9. An actuation method implemented by an actuator (6) included in a turbomachine (4) according to any one of claims 1 to 7, or by an actuator (6) included in a turbomachine (4) included in an aircraft (2) according to claim 8, the actuation method comprising the following steps: - Changing the state of the two-way servo valve (30) such that the two-way servo valve (30) is in a first state; - Moving the piston (12) and the rod (10) in a first direction at a first speed, the movement being caused by a first difference in the forces acting on the piston (12), the first difference depending at least on the pressure in the first chamber (14) and the force exerted on the piston (12) by the elastic return device (26); and / or - Changing the state of the two-way servo valve (30) such that the two-way servo valve (30) is in a second state; and - Moving the piston (12) and the rod (10) in a second direction opposite to the first direction at a second speed different from the first speed, the movement being caused by a second difference in the forces acting on the piston (12), the second difference depending at least on the pressure in the first chamber (14) and the force exerted on the piston (12) by the elastic return device (26).