An apparatus is provided for an aircraft propulsion system. This apparatus includes an acoustic panel and a mount. The acoustic panel includes a perforated face skin, a back skin, a perforated intermediate layer, a first cellular core and a second cellular core. The first cellular core includes a first section and a second section. The first section is between and is connected to the perforated face skin and the perforated intermediate layer. The second section is between and is connected to the perforated face skin and the back skin. The second cellular core is between and is connected to the perforated intermediate layer and the back skin. The mount is attached to the back skin along the second section.

A method for manufacturing a cellular core for an acoustic panel is provided. The cellular core includes at least one plurality of acoustic cells and a plurality of de-icing channels that extend longitudinally, each de-icing channel being transversely interposed between two successive cells, and the de-icing channels being adapted to channel a de-icing fluid. A manufacturing step includes producing the acoustic cells and the de-icing channels as a single piece such that the cellular core manufactured during the manufacturing step forms a monolithic part.

A method for manufacturing a cellular core for an acoustic panel is provided. The cellular core includes at least one plurality of acoustic cells and a plurality of de-icing channels that extend longitudinally, each de-icing channel being transversely interposed between two successive cells, and the de-icing channels being adapted to channel a de-icing fluid. A manufacturing step includes producing the acoustic cells and the de-icing channels as a single piece such that the cellular core manufactured during the manufacturing step forms a monolithic part.

An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.

An air inflow lip of a nacelle for a turbojet of an aircraft, including a cavity defined by a leading edge of the nacelle and by an annular wall, includes an inner wall, an acoustic treatment device, and a pneumatic de-icing device including a de-icing fluid supply device. The inner wall of the air inflow lip includes acoustic boreholes and the pneumatic de-icing device includes a honeycombed de-icing plate mounted inside the cavity on the inner wall of the air inflow lip. Also included are conduits for the circulation of a de-icing fluid and acoustic wells communicating with the acoustic boreholes.

Resonating patch for acoustic treatment comprising a resonant plate, a transducer and an electrical circuit electrically connected to the transducer, the resonant plate comprising a peripheral strip extending along the perimeter of the resonant plate.

The patch comprises cutouts together defining deformable lamellae having at least one end connected to the peripheral strip.

An acoustic panel includes a front skin comprising a plurality of apertures, a back skin, and a core positioned between the front skin and the back skin. The core includes at least one primary core portion including a honeycomb structure defining a plurality of cavities extending from the front skin to the back skin. The core further includes a secondary core portion external to the at least one primary core portion and including a foam structure extending from the front skin to the back skin.

The present invention discloses a soundproof cabin of a turbine engine. The soundproof cabin is sleeved on the turbine engine. The soundproof cabin includes a cabin body, an induction noise reduction unit and a ventilation noise reduction unit, wherein the induction noise reduction unit and the ventilation noise reduction unit are disposed on the cabin body, the surrounding of which is filled with soundproof materials, the induction noise reduction unit is used to reduce the induction noise of the turbine engine, the ventilation noise reduction unit is used to reduce the noise of the ventilation system of the turbine engine. Beneficial effects: an induction noise reduction unit is disposed at an air inlet of the turbine engine to reduce the induction noise of the turbine engine; a ventilation noise reduction unit is disposed on the transmission direction of the turbine engine to reduce the ventilation and cooling noise of the turbine engine; the surrounding of the turbine engine is filled with soundproof materials to achieve the overall noise reduction around the turbine engine.

The present invention discloses a soundproof cabin of a turbine engine. The soundproof cabin is sleeved on the turbine engine. The soundproof cabin includes a cabin body, an induction noise reduction unit and a ventilation noise reduction unit, wherein the induction noise reduction unit and the ventilation noise reduction unit are disposed on the cabin body, the surrounding of which is filled with soundproof materials, the induction noise reduction unit is used to reduce the induction noise of the turbine engine, the ventilation noise reduction unit is used to reduce the noise of the ventilation system of the turbine engine. Beneficial effects: an induction noise reduction unit is disposed at an air inlet of the turbine engine to reduce the induction noise of the turbine engine; a ventilation noise reduction unit is disposed on the transmission direction of the turbine engine to reduce the ventilation and cooling noise of the turbine engine; the surrounding of the turbine engine is filled with soundproof materials to achieve the overall noise reduction around the turbine engine.

An air inlet into a nacelle of an aircraft turbojet engine having a de-icing device and extends along an axis X, an air stream flowing in the air inlet from upstream to downstream, the inlet comprising an inner wall and an outer wall which are connected by a leading edge, the inner wall having a plurality of air delivery lines, each air delivery line having a plurality of through-holes designed to blow elementary streams from the hot air source in order to de-ice said inner wall, the air delivery lines being parallel to one another in a cylindrical projection plane, each air delivery line having a depth P3 defined along the axis X as well as a length L3 defined along the axis Y in the cylindrical projection plane, two adjacent air delivery lines being spaced apart by a distance D3, each position along the axis Y with no more than one through-hole, the ratio of the distances L3/D3 being between 0.8 and 1.