System for dual management of anti-icing and boundary layer suction on an aerofoil of an aircraft, including a function of collecting the anti-icing air

1. An anti-icing and boundary layer suction system, configured to equip an aerofoil of an aircraft, the system comprising:

at least one anti-icing channel;

at least one suction channel partly delimited by a multi-punched wall enabling a boundary layer to be sucked on the aerofoil;

a boundary layer suction control device;

an anti-icing control device;

a duct for collecting the suction air communicating with the suction channel;

an anti-icing air supplying duct connected to the anti-icing control device and communicating with the anti-icing channel through an anti-icing air intake pipe;

wherein the boundary layer suction control device includes a three-way valve on which the suction air collecting duct, a suction duct, and an anti-icing air exhaust duct are respectively connected;

the system further comprising an anti-icing air collecting pipe connected to the anti-icing channel and to the suction air collecting duct.

2. The system according to claim 1 , wherein the suction air collecting duct and the anti-icing air supplying duct are arranged substantially in parallel to each other, or along a span direction of the aerofoil.

3. The system according to claim 1 , further comprising at least one dual function channel in which air for the anti-icing function and air for the boundary layer suction can alternately circulate, the dual function channel being partly delimited by the multi-punched wall enabling the boundary layer to be sucked on the aerofoil, and wherein the dual function channel:

communicates with the anti-icing air intake pipe; and

communicates with a suction air collecting pipe connected to the suction air collecting duct, via a controlled valve.

4. The system according to claim 1 , further comprising at least one suction air collecting secondary pipe allowing communication between each boundary layer suction channel and the suction air collecting duct.

5. The system according to claim 1 , further comprising plural anti-icing channels and plural boundary layer suction channels substantially parallel to each other, and wherein at least some of the anti-icing channels and of the boundary layer suction channels are alternately arranged.

6. An aerofoil for an aircraft comprising at least one anti-icing and boundary layer suction system according to claim 1 .

7. An aircraft comprising least one anti-icing and boundary layer suction system according to claim 1 .

8. The system according to claim 3 , configured such that the anti-icing air circulating through the dual function channel does not penetrate the anti-icing air collecting pipe.

9. The system according to claim 3 , further comprising a plurality of dual function channels in which air for the anti-icing function and air for the boundary layer suction can alternately circulate, including:

a dual function primary channel, directly communicating with the anti-icing air intake pipe; and

dual function secondary channels, communicating with the dual function primary channel and with the anti-icing air collecting pipe, the dual function secondary channels being arranged substantially in parallel to each other and substantially orthogonal to the dual function primary channel and to the anti-icing air collecting pipe.

10. The system according to claim 4 , further comprising a suction air collectin pipe connected to the suction air collecting duct and wherein the anti-icing air intake pipe, the suction air collecting pipe, each suction air collecting secondary pipe, and the anti-icing air collecting pipe each follow the aerodynamic profile of the aerofoil, by being arranged in parallel planes, spaced from each other along a span direction of this aerofoil.

11. The system according to claim 5 , successively comprising, in a chord direction from a leading edge of the aerofoil:

a dual function channel;

a plurality of the anti-icing channels; and then

an alternation between the air suction channels and the other anti-icing channels,

the anti-icing channels, the suction channels, and the dual function channel extending in parallel to each other, along a span direction of the aerofoil.

12. The system according to claim 9 , wherein the dual function secondary channels are arranged in parallel planes, spaced from each other along a span direction of the aerofoil.

13. The system according to claim 9 , wherein the suction air collecting duct, the anti-icing air supplying duct, the dual function primary channel, and the anti-icing air collecting pipe are arranged substantially parallel to each other along a span direction of the aerofoil.

14. The system according to claim 9 , wherein the suction air collecting duct and the anti-icing air collecting pipe communicate together through at least one junction pipe.

15. The aerofoil according to claim 6 , which is a wing or a tail unit.

16. An aircraft comprising at least one aerofoil according to claim 6 .