Air discharge system for an aeronautical turbine engine compressor

1. An air discharge system for a compressor of an aviation turbomachine, comprising:

a discharge valve disposed between a primary channel of the turbomachine and a secondary channel of the turbomachine, the primary channel being level with the compressor, and an outer shroud of the compressor including an air bleed orifice opening out into the secondary channel via the discharge valve, the discharge valve comprising:

an air passage extending between the primary channel and the secondary channel;

a valve body which moves inside the air passage between an open position, in which a fraction of air flowing in the primary channel is taken off and injected into the secondary channel by flowing along the air passage, corresponding to the discharge valve being open and a closed position, in which the valve body closes the air passage and prevents the air flowing in the primary channel to be injected into the secondary channel corresponding to the discharge valve being closed, the valve body presenting a body of revolution which is centered on a longitudinal axis of the air passage;

a camshaft including a cylindrical rod provided with a cam, said cam being mounted to press against the valve body in such a manner that rotating the camshaft causes the valve body to move between the open and closed positions; and

a device which maintains the cam to permanently press against the valve body;

a main electric motor having a rotor which drives the camshaft of the discharge valve in rotation;

a secondary electric motor having a rotor in common with the rotor of the main electric motor; and

an electronic control system configured to control the main and secondary electric motors, wherein each discharge valve further includes a ball bushing slidably mounted inside a stationary structure and having a head that is mounted to bear against the cam, the ball bushing including a return spring which maintains the head permanently pressing against the cam such that the cam remains permanently bearing against the valve body, wherein the cam presents a notch, and the head rests in the notch when the discharge valve is in the closed position.

2. The system according to claim 1 , including a plurality of discharge valves and a single main electric motor, the camshafts of the discharge valves being connected together by a movement transmission cable.

3. The system according to claim 1 , including a plurality of discharge valves and a plurality of main electric motors associated with each discharge valve to drive the camshaft of each of the discharge valves in rotation.

4. The system according to 1 , wherein the electronic control system includes a device for each electric motor which measures a current needed to actuate the motor before starting, and which compares the measured current value with a predetermined threshold value.

5. The system according to claim 1 , wherein the electronic control system is an electronic module of a full authority digital engine control system of the turbomachine.

6. The system according to claim 1 , wherein a first end of the valve body abuts a wall provided at a first end of the air passage in the closed position.

7. The system according to claim 6 , wherein the cam presses against a second end of the valve body.

8. The system according to claim 1 , wherein a first end of the return spring is fastened to the ball bushing and a second end of the return spring is fastened to an end wall of the stationary structure.

9. The system according to claim 8 , wherein the stationary structure includes walls extending radially from the end wall and surrounding the ball bushing and the return spring.

10. An aviation turbomachine compressor including an air discharge system, the air discharge system comprising:

a discharge valve disposed between a primary channel of the turbomachine and a secondary channel of the turbomachine, the primary channel being level with the compressor, and an outer shroud of the compressor including an air bleed orifice opening out into the secondary channel via the discharge valve, the discharge valve comprising:

an air passage extending between the primary channel and the secondary channel;

a valve body which moves inside the air passage between an open position, in which a fraction of air flowing in the primary channel is taken off and injected into the secondary channel by flowing along the air passage, corresponding to the discharge valve being open and a closed position, in which the valve body closes the air passage and prevents the air flowing in the primary channel to be injected into the secondary channel corresponding to the discharge valve being closed, the valve body presenting a body of revolution which is centered on a longitudinal axis of the air passage;

a camshaft including a cylindrical rod provided with a cam, said cam being mounted to press against the valve body in such a manner that rotating the camshaft causes the valve body to move between the open and closed positions; and

a device which maintains the cam to permanently press against the valve body;

a main electric motor having a rotor which drives the camshaft of the discharge valve in rotation;

a secondary electric motor having a rotor in common with the rotor of the main electric motor; and

an electronic control system configured to control the main and secondary electric motors, wherein each discharge valve further includes a ball bushing slidably mounted inside a stationary structure and having a head that is mounted to bear against the cam, the ball bushing including a return spring which maintains the head permanently pressing against the cam such that the cam remains permanently bearing against the valve body, wherein the cam presents a notch, and the head rests in the notch when the discharge valve is in the closed position.

11. An aviation turbomachine including an air discharge system, the air discharge system comprising:

a discharge valve disposed between a primary channel of the turbomachine and a secondary channel of the turbomachine, the primary channel being level with the compressor, and an outer shroud of the compressor including an air bleed orifice opening out into the secondary channel via the discharge valve, the discharge valve comprising:

an air passage extending between the primary channel and the secondary channel;

a valve body which moves inside the air passage between an open position, in which a fraction of air flowing in the primary channel is taken off and injected into the secondary channel by flowing along the air passage, corresponding to the discharge valve being open and a closed position, in which the valve body closes the air passage and prevents the air flowing in the primary channel to be injected into the secondary channel corresponding to the discharge valve being closed, the valve body presenting a body of revolution which is centered on a longitudinal axis of the air passage;

a camshaft including a cylindrical rod provided with a cam, said cam being mounted to press against the valve body in such a manner that rotating the camshaft causes the valve body to move between the open and closed positions; and

a device which maintains the cam to permanently press against the valve body;

a main electric motor having a rotor which drives the camshaft of the discharge valve in rotation;

a secondary electric motor having a rotor in common with the rotor of the main electric motor; and

an electronic control system configured to control the main and secondary electric motors, wherein each discharge valve further includes a ball bushing slidably mounted inside a stationary structure and having a head that is mounted to bear against the cam, the ball bushing including a return spring which maintains the head permanently pressing against the cam such that the cam remains permanently bearing against the valve body, wherein the cam presents a notch, and the head rests in the notch when the discharge valve is in the closed position.