Turbine engine comprising an actuator and aircraft comprising such a turbine engine, and corresponding actuation method

1 . Turbine engine comprising an actuator comprising a cylinder comprising a rod provided with a piston defining at least partially within the cylinder a first chamber and a second chamber, the actuator comprising a first fluid line and a second fluid line both fluidly connected to the first chamber, a resilient return means in a predetermined position disposed in one of the first chamber or the second chamber and configured to exert a force on the piston, the first fluid line comprising a calibrated port, the actuator comprising a two-way servo-valve fluidly connected to the second fluid line, a cross-sectional area of the two-way servo-valve being greater than or equal to ten times a cross-sectional area of the calibrated port or a head loss in the first fluid line being greater than or equal to ten times a head loss in the second fluid line, the turbine engine comprising a first fluid source and a second fluid source, wherein an element chosen from among the first fluid line and the second fluid line is configured to receive a first fluid from the first fluid source, and wherein a remaining element chosen among the first fluid line and the second fluid line is configured to take a second fluid from the second fluid source, a pressure of the first fluid being greater than a pressure of the second fluid, wherein the first fluid source comprises a compressor of the turbine engine, the second fluid comprising air under atmospheric pressure.

2 . Turbine engine according to claim 1 , wherein the actuator comprises a common line opening into the first chamber, the first fluid line and the second fluid line both being fluidly connected to the common line.

3 . Turbine engine according to claim 1 , wherein the two-way servo-valve comprises an electromagnetic control.

4 . Turbine engine according to claim 1 , wherein the two-way servo-valve is configured to have at least one passing state so that a fluid can flow in the second fluid line through the two-way servo-valve and a blocking state so that a fluid cannot flow in the second fluid line through the two-way servo-valve.

5 . Turbine engine according to claim 1 , wherein the two-way servo-valve comprises a proportional control configured to position the piston in an intermediate position of a stroke of the piston.

6 . Turbine engine according to claim 1 , wherein the piston is associated with a sealed rolling membrane to sealingly separate the first chamber and the second chamber.

7 . Turbine engine according to claim 1 , wherein the cross-sectional area of the two-way servo-valve is greater than twenty times the cross-sectional area of the calibrated port.

8 . Aircraft comprising the turbine engine according to claim 1 .

9 . Actuation method implemented by the actuator included in a turbine engine according to claim 1 , comprising the following steps of:

changing the state of the two-way servo-valve so that the two-way servo-valve is in a first state;

moving the piston and the rod in a first direction at a first speed, said movement being due to a first difference in forces acting on the piston depending at least on the pressure in the first chamber and the force exerted by the resilient return means on the piston;

and/or

changing the state of the two-way servo-valve so that the two-way servo-valve is in a second state; and

moving 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 due to a second difference in forces acting on the piston depending at least on the pressure in the first chamber and the force exerted by the resilient return means on the piston.