An evaporative cooling pack formed from first and second corrugated media sheets is provided. The evaporative cooling pack cools a flow of air using a cooling fluid. The first and second corrugated media sheets have flutes that extend at different angles relative to a reference line and at such relative angles and have flute pitches that inhibit nesting of the adjacent sheets.

A rotor blade system includes a blade root, a blade neck adjoining the blade root, an airfoil adjoining the blade neck, a radially outer partition wall, an axially forward partition wall and an axially rearward partition wall, connected to the radially outer partition wall such that the partition walls surround the blade neck on three sides, the partition walls projecting beyond the blade neck in the circumferential direction, and further including a blade root protection plate designed to be arranged on the blade root. It is provided that the blade root protection plate have at least one sealing portion that extends in the axial direction from the forward partition wall to the rearward partition wall and whose radially outer side is disposed opposite the radially outer partition wall when the blade root protection plate is arranged on the blade root.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) has an at least partially wavy inflow edge (4). The wavy inflow edge (4) forms a wave (W) with a specific three-dimensional waveform.

The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.

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 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 structure is provided that includes a perforated first skin, a second skin and a core. The core includes a first sidewall, a second sidewall, a first baffle and a second baffle. The core forms a plurality of cavities vertically between the perforated first skin and the second skin. The first baffle is connected to the perforated first skin at a first baffle first end. The first baffle is connected to the second skin at a first baffle second end by a first moveable joint. The second baffle is connected to the perforated first skin at a second baffle first end. The second baffle is connected to the second skin at a second baffle second end. A first of the cavities extends laterally between the first sidewall and the second sidewall. The first cavity extends longitudinally between the first baffle and the second baffle.

A component with a region to be cooled having a cooling channel which is arranged and designed so as to cool the region of the component during operation by a fluid flow, wherein the cooling channel is defined by a first channel side facing the region and by a second channel side facing away from the region. The first channel side forms a larger contact surface for the cooling channel than the second channel side. An additive manufacture process can produce the component.

A fan blade (1) has a front inflow edge (2) and a rear outflow edge (3). The fan blade (1) has an at least partially wavy inflow edge (4) that forms a wave (W) having a specific three-dimensional waveform.

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.