An acoustic panel for an aircraft propulsion unit, comprises a core and an entry layer in contact with the core, the entry layer comprising lower elements and upper elements, each comprising an inner face, an outer face and at least one through-hole, the inner faces of the lower elements and upper elements being in contact with each other and forming a channel defining a baffle and opening into a cell of the core.

An acoustic panel for an aircraft propulsion unit, comprises a core and an entry layer in contact with the core, the entry layer comprising lower elements and upper elements, each comprising an inner face, an outer face and at least one through-hole, the inner faces of the lower elements and upper elements being in contact with each other and forming a channel defining a baffle and opening into a cell of the core.

An air supply device, a gas turbine system and a using method thereof are disclosed. In the air supply device, an air intake compartment includes a connection end; a combustion air intake filter is located in the air intake compartment and connected with the combustion air intake filter; a combustion air intake interface is located on a tail plate and is connected with the combustion air silencer; and a sound insulation turnover mechanism includes a sound insulation flap and a turnover mechanism, the air intake compartment includes a first bottom plate and the tail plate that is located at the connection end, the sound insulation flap is located at the connection end, and the turnover mechanism is connected with the sound insulation flap, and is configured to drive the sound insulation flap to rotate relative to the tail plate.

An air supply device, a gas turbine system and a using method thereof are disclosed. In the air supply device, an air intake compartment includes a connection end; a combustion air intake filter is located in the air intake compartment and connected with the combustion air intake filter; a combustion air intake interface is located on a tail plate and is connected with the combustion air silencer; and a sound insulation turnover mechanism includes a sound insulation flap and a turnover mechanism, the air intake compartment includes a first bottom plate and the tail plate that is located at the connection end, the sound insulation flap is located at the connection end, and the turnover mechanism is connected with the sound insulation flap, and is configured to drive the sound insulation flap to rotate relative to the tail plate.

A method of a coating by additive manufacturing on a turbomachine casing includes depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments. A filamentary material deposition system is positioned from the internal surface of the casing; a first layer of the coating is deposited over 360′; a rotation of the filamentary material deposition system is carried out by a first predetermined angle and the filamentary material deposition system is positioned from the deposited layer; a second layer of coating is deposited on the first coating layer, on a sector of the casing; a displacement is carried out corresponding to the first sector already covered, then for the following sectors until 360° is covered; and after having carried out a rotation of the filamentary material deposition system.

A gas turbine has blades. A blade may have a leading edge; a trailing edge; a pressure side and a suction side, which extend between the leading edge and the trailing edge. The blade has, along the leading edge, a leading edge profile with profile portions, each of which, along its profile portion length, transitioning, proceeding from a depression, into an elevation via a first transition portion and back into a next depression via a second transition portion. An apex of the elevation of a profile portion is arranged in an asymmetric manner in relation to the profile portion length, in such a way that the first transition portion has a first transition length and the second transition portion has a second transition length. The first transition length and the second transition length are different lengths.

A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

An airflow profile structure having a leading and/or trailing edge profiled with a serrated profile having a succession of teeth and depressions. Along the leading and/or trailing edge, from a first location to a second location, the teeth of the serrated profile are individually inclined towards the second location.

The invention relates to an intake device for a compressor. The intake device comprises a support structure having a plurality of struts which are arranged in the circumferential direction about an axis of the support structure and extend in the radial direction. Furthermore, the intake device comprises a plurality of first sound-damping elements which are arranged in the radial continuation of the plurality of struts. In addition, the intake device comprises a plurality of second sound-damping elements, each of which is arranged between adjacent first sound-damping elements. The invention furthermore relates to an exhaust-gas turbocharger having the intake device according to the invention, and an internal combustion engine having an exhaust-gas turbocharger of this kind.