Panel for heat exchange and improved noise reduction for a turbomachine

A heat exchange and noise reduction panel for an aircraft turbine engine comprising:

• an outer surface which is intended for being swept over by an air flow and from which fins extend in a first predetermined main direction and a second predetermined main direction, wherein the first predetermined main direction is perpendicular to the second predetermined main direction,
• recesses and air-passage channels that cooperatively form Helmholtz resonators wherein each recess is connected to a first end of a corresponding one of the air-passage channels, a second end of which communicates with said air flow, such that said channels form necks of said Helmholtz resonators that extend through an interior of a corresponding one of the fins in the first direction of the fins and open on distal ends of the fins,
• at least one oil circulation chamber which extends between said outer surface and said recesses and is intended for discharging thermal energy from the oil,
• a stack consisting of said outer surface, said recesses and said at least one oil circulation chamber extending in the first direction,
• wherein said channels extend uninterrupted from a corresponding one of the recesses to the distal end of the fin without any intervening apertures.