Abstract: A suction arrangement for drawing off a boundary layer on an aircraft comprises a suction arrangement including an outer skin having suction surfaces in critical flow areas, and at least one air breathing engine providing suction. Bleed air is drawn from a comparatively high-pressure region of the engine by means of a branch line and the bleed air is used for driving a turbine of at least one turbo-supercharger assembly. A compressor of the turbo-supercharger assembly or assemblies serves as the suction source for drawing off a boundary layer at the suction surfaces in critical flow areas.

Abstract: An aircraft, aircraft system and air fractionization device are provided. The air fractionization device is provided for use on board an aircraft. The air fractionization installation functions according to the principle of pressure swing adsorption and is supplied by the air conditioning and pressurization system with which also the aircraft cabin may be supplied with air.

Abstract: The method serves for operating an air fractionization installation for obtaining oxygen on board an aircraft, with at least two molecular sieve chambers. A part mass flow of the oxygen obtained in the respective adsorbing molecular sieve chamber is supplied for flushing a desorbing molecular sieve chamber. The quantity of the flushing oxygen led to the desorbing molecular sieve chamber is controlled by way of this.

Abstract: A suction arrangement for drawing off a boundary layer on an aircraft comprises a suction arrangement including an outer skin having suction surfaces in critical flow areas, and at least one air breathing engine providing suction. Bleed air is drawn from a comparatively high-pressure region of the engine by means of a branch line and the bleed air is used for driving a turbine of at least one turbo-supercharger assembly. A compressor of the turbo-supercharger assembly or assemblies serves as the suction source for drawing off a boundary layer at the suction surfaces in critical flow areas.

Abstract: 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.

Abstract: 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.