Daimlerchrysler Aerospace Airbus Gmbh

Juergen Pfennig

Juergen Meister

Werner Held

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 (,) arranged in the bypass engine (,) of the aircraft, and a system of suction conduits (,) connecting the jet pumps (,) to suction channels (,A) communicating with the perforated or porous suction areas (,). Each jet pump (,) includes an ejector pipe (,) that is driven by an external surrounding driving jet (,) or by an internal driving jet (,) flowing through an internal jet pipe (,). The jet pumps (,) are arranged at selected locations in the air intake upstream of the fan, in the bypass channel (,) just downstream of the fan, in the bypass channel near the outlet end thereof, in the core hot gas channel (,) upstream of a compressor assembly, and/or in the core channel downstream of a turbine assembly. The jet pumps (,) provide an efficient, maintenance-free, reliable, and easily installable suction generator system.

Suction device for boundary layer control in an aircraft

The boundary layer flow along the surface of an aircraft rudder assembly is controlled by suction applied through perforations primarily installed in the leading edge of the rudder assembly. The control is such that a laminar flow is enforced or at least such that any turbulent flow is displaced so that it begins downstream of the rudder assembly leading edge. Suction air chambers are arranged along the leading edge inside a nose box of the rudder assembly and these boxes are connected through air ducts and a valve system to an exhaust fan. The valve system and the exhaust fan are controlled by a central processing unit providing a flow controller for the suction in response to control signals produced from rated values and sensed actual valves to provide a uniform distribution of the suction along the leading edge of the rudder assembly. The suction system may be switched over to a de-icing mode by blowing warm air out through the perforations in a controlled manner.

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Munich, Georgia

Juergen Pfennig