Cooling assembly for an aircraft provided with a fan

1. A cooling assembly including:

a conduit including a side wall, an air intake and an air outlet allowing circulation of an air flow in the conduit, and

a fan comprising:

a rotating electric machine comprising:

a rotary shaft,

a ventilation wheel secured to the shaft,

a power supply module able to connect the rotating electric machine to an electric power supply network providing a three-phase electric network, the power supply module including a transformation device able to adapt the three-phase electric current provided by the three-phase electric network for powering the rotary electric machine and including:

three input terminals, the three input terminals being connected to the three-phase electric network,

at least three output terminals, the at least three output terminals being connected to the rotating electric machine,

three distinct single-phase self-transformers which are magnetically decoupled from one another, each single- phase self-transformer being connected to one of the input terminals and at least to one of the output terminals and being able to modify the voltage values of an input single-phase alternating current on the corresponding input terminal for obtaining a modified output current on said or each output terminal corresponding to the single-phase self-transformer, each self-transformer surrounding the side wall of the conduit.

2. The cooling assembly according to claim 1 , wherein each single-phase self-transformer has an inner diameter and the side wall of the conduit has an outer diameter, the inner diameter of each single-phase self-transformer being greater than or equal to the outer diameter of the side wall.

3. The cooling assembly according to claim 2 , wherein the inner diameter of each single-phase self-transformer is identical.

4. The cooling assembly according to claim 1 , wherein each single-phase self-transformer includes an inner surface, the inner surface being in contact with the side wall of the conduit.

5. The cooling assembly according to claim 4 , wherein the totality of the inner surface of each single-phase self-transformer is in contact with the side wall of the conduit.

6. The cooling assembly according to claim 1 , wherein each single-phase self-transformer includes:

a ferromagnetic core of a torus shape and

a primary winding wound around at least one portion of the core and connected to the input terminal of the single-phase self-transformer.

7. The cooling assembly according to claim 1 , wherein each single-phase self-transformer is at the same distance from the closest single-phase self-transformer.

8. The cooling assembly according to claim 1 , wherein the conduit further includes:

a heat exchanger.

9. An aircraft including an assembly according to claim 1 .