Device for boundary layer suction and composite component therefor
A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.
1. A composite component comprising a surface for boundary layer suction on the outer skin of an aircraft where drawing off by boundary layer suction can take place, the composite component comprising:
a base body, the base body comprising an extruded profile made of a light metal,
a plurality of stringers extruded from the base body and forming a plurality of open suction channels arranged next to one another on the base body, and
a micro-perforated metal cover sheet made of titanium or a stainless steel as a corrosion-resistant metal applied to stringer heads thereby forming the surface where drawing off by boundary layer suction can take place.
2. The composite component according to claim 1 , wherein the micro-perforated metal cover sheet is bonded or vulcanized onto the extruded profile thereby producing a firm integral connection.
3. The composite component according to claim 1 , wherein the extruded profile comprises aluminum or an aluminum alloy.
4. An aerodynamic component of an aircraft comprising a composite component comprising a surface for boundary layer suction on the outer skin of an aircraft, the component comprising:
a base body, the base body comprising an extruded profile made of a light metal,
a plurality of stringers extruded from the base body and forming a plurality of open suction channels arranged next to one another on the base body,
a micro-perforated metal cover sheet made of titanium or a stainless steel as a corrosion-resistant metal applied to stringer heads thereby forming the surface where drawing off by boundary layer suction can take place, and
a suction source connected to the surface by the suction channels and at least one suction line;
wherein the micro-perforated metal cover sheet is bonded or vulcanized onto the extruded profile thereby producing a firm integral connection; and
wherein the stringer heads have planar support surfaces and chamfered first and second flanks.
5. The aerodynamic component according to claim 4 , wherein the suction channels extend in the direction of a wingspan.
6. The aerodynamic component according to claim 5 , wherein the aerodynamic component is an engine nacelle or a wing or a vertical stabilizer of a commercial aircraft.
7. The aerodynamic component according to claim 4 , wherein the suction line comprises an aperture for balancing the air mass flow.