Aircraft turbomachine equipped with a thermoacoustic system
A turbomachine for an aircraft, comprising a thermoacoustic system associated with a fluid circuit that serves to supply the engine of the turbomachine with fluid. The thermoacoustic system comprises an exchanger which is connected to the fluid circuit and in which there flows a fluid that is to be cooled, an acoustic attenuation structure which is distinct from the exchanger and which forms all or part of a wall of the fan duct, and at least one heat-duct tube comprising a portion that is entirely received in the acoustic structure and a portion with an end that is received in the exchanger, and a single curved elbow with a non-zero angle between the two portions.
1. A bypass turbomachine for an aircraft, comprising:
an engine provided for turning a fan;
an annular inter-duct element concentric with the engine;
a nacelle concentric with the inter-duct element, the inter-duct element and the nacelle defining between them a fan duct in which there flows an air flow;
at least one fluid circuit configured to make a fluid move towards or out of the engine;
a thermoacoustic system associated with the at least one fluid circuit,
the thermoacoustic system comprising:
an exchanger connected to the fluid circuit and in which there flows the fluid that is to be cooled,
an acoustic attenuation structure distinct from the exchanger and which forms all or part of a wall of the fan duct, and
at least one heat-duct tube comprising a first portion entirely received in the acoustic structure and a second portion with an end received in the exchanger, and a single curved elbow with a non-zero angle between the first and second portions,
wherein the acoustic attenuation structure comprises:
a first panel in contact with the air flow flowing in the fan duct and having perforations;
a second panel comprising at least one orifice through which the at least one heat-duct tube is to pass; and
a core;
the core comprising:
a plurality of structural partitions forming, with the two panels, a network of acoustic cavities extending between the first and second panels, and where each acoustic cavity communicates with the fan duct via the perforations.
2. The turbomachine according to claim 1 , wherein the angle of the curved elbow is 90°.
3. The turbomachine according to claim 1 , wherein the heat-duct tube comprises a capillary network.
4. The turbomachine according to claim 1 , wherein at least one structural partition, termed support partition, has an orifice through which the heat-duct tube passes.
5. The turbomachine according to claim 1 , wherein the exchanger is formed as a hollow solid, parallelepipedal in shape, having a bottom wall, and a wall forming a lid, the bottom wall and the lid wall being mutually parallel and connected to one another by four lateral walls in parallel pairs, all perpendicular to the bottom wall and to the lid wall, the exchanger comprising a sheath arranged at a level of the lid wall and into which part of the second portion of each heat-duct tube is inserted.
6. The turbomachine according to claim 5 , wherein a finned exchanger is arranged around the sheath.
7. The turbomachine according to claim 1 , wherein the exchanger is formed as a hollow solid, parallelepipedal in shape, having a bottom wall, and a wall forming a lid, the bottom wall and the lid wall being mutually parallel and connected to one another by four lateral walls in parallel pairs, all perpendicular to the bottom wall and to the lid wall, the exchanger comprising a through-orifice arranged at a level of the lid and through which part of the second portion of each heat-duct tube is inserted.
8. The turbomachine according to claim 1 , wherein the thermoacoustic system is arranged in the inter-duct element.
9. The turbomachine according to claim 1 , wherein the exchanger is arranged in the inter-duct element and the acoustic attenuation structure is arranged in the nacelle.
10. The turbomachine according to claim 1 , wherein the thermoacoustic system is arranged in the nacelle.