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US 6,216,982 B1Granted
Suction device for boundary layer control in an aircraft
AssigneeDaimlerChrysler Aerospace Airbus GmbH
InventorsJuergen Pfennig, Juergen Meister
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AssigneeDaimlerChrysler Aerospace Airbus GmbH
InventorsJuergen Pfennig, Juergen Meister
Estimating the term…
A system for achieving a boundary layer control by sucking at least a portion of the boundary layer air flow through perforated or porous suction areas on the outer skin of the wings or other areas of the aircraft, includes one or more jet pumps (7) arranged in the bypass engine (5) of the aircraft, and a system of suction conduits (4) connecting the jet pumps (7) to suction channels (3A) communicating with the perforated or porous suction areas (3). Each jet pump (7) includes an ejector pipe (101) that is driven by an external surrounding driving jet (8) or by an internal driving jet (8) flowing through an internal jet pipe (15). The jet pumps (7) are arranged at selected locations in the air intake upstream of the fan, in the bypass channel (18) just downstream of the fan, in the bypass channel near the outlet end thereof, in the core hot gas channel (19) upstream of a compressor assembly, and/or in the core channel downstream of a turbine assembly. The jet pumps (7) provide an efficient, maintenance-free, reliable, and easily installable suction generator system.
In an aircraft including an aircraft body having an outer skin with at least one suction area thereon, and an air-breathing engine that is connected to said aircraft body and that has an air flow passage therein, wherein said suction area is adapted to have air sucked therethrough;
Dependencies are inferred from the claim text.