초록 ▼

An aircraft component, such as a wing, has perforations through an outer wall for boundary layer suction. In the space between the outer wall and an inner wall partition walls form pressure channels and suction channels that are adjacent to each other and alternate, which channels communicate with t

An aircraft component, such as a wing, has perforations through an outer wall for boundary layer suction. In the space between the outer wall and an inner wall partition walls form pressure channels and suction channels that are adjacent to each other and alternate, which channels communicate with the perforations. For example, alternating channels may be formed by a corrugated structure having trapezoidal corrugations providing a larger area for the suction channels than for the pressure channels. The pressure channels may be coupled to a hot-air reservoir by a control device, lines and valves, and the suction channels may be coupled to a vacuum reservoir, unless a short-circuit valve is used to cross connect the lines.

대표청구항 ▼

The invention claimed is: 1. An aircraft component being exposed to streaming surrounding air, comprising an inner wall; an outer wall, the outer wall being displaced a distance from the inner wall, the distance defining a space between the inner wall and the outer wall; a plurality of partition wa

The invention claimed is: 1. An aircraft component being exposed to streaming surrounding air, comprising an inner wall; an outer wall, the outer wall being displaced a distance from the inner wall, the distance defining a space between the inner wall and the outer wall; a plurality of partition walls being inserted within the space between the inner wall and the outer wall, the plurality of partition walls are formed by an integral sheet with trapezoidal corrugations having a plurality of base areas, the base areas alternately in contact with the outer wall and the inner wall and having openings in fluid communication with a plurality of perforations through the outer wall such that a plurality of sections form a plurality of pressure channels, each adjacent to a respective one of a plurality of suction channels, the plurality of sections extending from the inner wall to the outer wall, such that: the plurality of suction channels are adapted for sucking surrounding air from a plurality of first regions of the outer wall; the plurality of pressure channels are adapted for feeding hot pressurized air to a plurality of second regions of the outer wall; the plurality of first regions of the outer wall have a significantly larger area than the plurality of second regions of the outer wall; and a control device controllably coupling the plurality of pressure channels to a hot air reservoir and the plurality of suction channels to a vacuum reservoir. 2. The aircraft component of claim 1, wherein open sides of the trapezoidal corrugations have longer areas than closed side of the trapezoidal corrugations. 3. The aircraft component of claim 1, further comprising a first controllable valve coupling the pressure channels to the hot air reservoir and a second control valve coupling the suction channels to the vacuum reservoir, such that a negative pressure in the suction channels is controllable by the control device. 4. The aircraft component of claim 3, wherein one of the first valve or the second valve is a pressure valve and the other of the first valve or second valve is a check valve, such that the control device is capable of alternately coupling the plurality of pressure channels to the hot air reservoir and the plurality of suction channels to the vacuum reservoir. 5. The aircraft component of claim 4, further comprising a third controllable valve coupling a pressure line in fluid communication with the plurality of pressure channels, with a suction line in fluid communication with the plurality of suction channels, such that the third controllable valve operates as a short circuit valve and the control device is capable of coupling the plurality pressure channels to the vacuum reservoir and the plurality of suction channels to the hot air reservoir. 6. The aircraft component of claim 5, wherein the first valve and the second valve are attuned by the control device operably controlling the third controllable valve.