Leading-edge device for an aircraft

Patent metadata

Field	Value
Publication number	US-11459087-B2
Application number	US-202016861714-A
Country	US
Kind code	B2
Filing date	Apr 29, 2020
Priority date	Apr 30, 2019
Publication date	Oct 4, 2022
Grant date	Oct 4, 2022

Abstract

A leading-edge device for an aircraft, the device comprising a flow body having a front skin, a back skin, a spar and an air inlet. The front skin is curved around a spanwise axis to form a bottom section and a top section.
A leading edge of the flow body is arranged between the bottom section and the top section. The spar extends from the bottom section to the top section. The front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet. An outlet portion is arranged at least directly adjacent to the bottom section of the front skin. The outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets.

First claim

The invention claimed is:

1. A leading-edge device for an aircraft, comprising a flow body having a front skin, a back skin, a spar and an air inlet,
wherein the front skin is curved around a spanwise axis to form a bottom section and a top section,
wherein a leading edge of the flow body is arranged between the bottom section and the top section,
wherein the spar extends from the bottom section to the top section,
wherein the front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet,
wherein an outlet portion is arranged at least directly adjacent to the bottom section of the front skin, and
wherein the outlet portion comprises a lower flange of the spar extending into the at least one air chamber and a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets,
wherein each of the plurality of air outlets comprises an aperture in the lower flange such that an airflow is routed from the at least one chamber through the air outlets.

2. The leading-edge device according to claim 1 , wherein the air outlets extend through the front skin in the bottom section.

3. A leading-edge device for an aircraft, comprising a flow body having a front skin, a back skin, a spar and an air inlet,
wherein the front skin is curved around a spanwise axis to form a bottom section and a top section,
wherein a leading edge of the flow body is arranged between the bottom section and the top section,
wherein the spar extends from the bottom section to the top section,
wherein the front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet,
wherein an outlet portion is arranged at least directly adjacent to the bottom section of the front skin,
wherein the outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets,
wherein the spar comprises a lower flange attached to the bottom section of the front skin,
wherein the back skin is attached to the lower flange, such that the back skin and the bottom section enclose the lower flange,
wherein the lower flange comprises a plurality of slots extending underneath the back skin as the air outlets.

4. A leading-edge device for an aircraft, comprising a flow body having a front skin, a back skin, a spar and an air inlet,
wherein the front skin is curved around a spanwise axis to form a bottom section and a top section,
wherein a leading edge of the flow body is arranged between the bottom section and the top section,
wherein the spar extends from the bottom section to the top section,
wherein the front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet,
wherein an outlet portion is arranged at least directly adjacent to the bottom section of the front skin,
wherein the outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets,
wherein the back skin is attached to the spar,
wherein a lower end edge of the back skin and the spar enclose a gap,
wherein the back skin comprises a plurality of dimples in fluid communication with the air inlet, wherein the dimples have lower openings that face into the gap and act as the air outlets.

5. The leading-edge device according to claim 4 , wherein the dimples extend between the back skin and a part of the spar and comprise upper openings facing into the at least one air chamber.

6. A leading-edge device for an aircraft, comprising a flow body having a front skin, a back skin, a spar and an air inlet,
wherein the front skin is curved around a spanwise axis to form a bottom section and a top section,
wherein a leading edge of the flow body is arranged between the bottom section and the top section,
wherein the spar extends from the bottom section to the top section,
wherein the front skin, the back skin and the spar enclose at least one air chamber that is in fluid communication with the air inlet,
wherein an outlet portion is arranged at least directly adjacent to the bottom section of the front skin,
wherein the outlet portion comprises a plurality of air outlets for letting air from the at least one air chamber exhaust through the air outlets, and
further comprising a girder attached to the spar and the back skin,
wherein the girder comprises an upper edge in a distance to the front skin and a lower edge adjacent to the bottom section of the front skin, and
wherein the girder comprises a plurality of slots extending between the upper edge and the lower edge, such that lower ends of the slots adjacent the bottom section form the air outlets.

7. The leading-edge device according to claim 6 , wherein flow directions of the lower ends are arranged transverse to the girder.

8. The leading-edge device according to claim 1 , wherein the air outlets are configured to form an exhaust flow that is attached to and runs along the front skin in the bottom section.

9. A wing for an aircraft, having a fixed leading edge and a leading-edge device according to claim 1 , wherein the leading-edge device is movable between a retracted position directly forward of the fixed leading edge and at least one extended position at a further distance to the fixed leading edge.

10. The wing of claim 9 , wherein the air outlets are configured to exhaust the air in a region in front of a lowermost part of the fixed leading edge in the retracted position the leading-edge device.

11. The wing of claim 9 , wherein the air outlets are arranged in front of the fixed leading edge.

12. An aircraft having at least one wing of claim 9 , wherein the air inlet is in fluid communication with a source of heated air.

13. The aircraft of claim 12 ,
further comprising at least one turbofan engine having at least one bleed air port,
wherein the air inlet is in fluid communication with the at least one bleed air port, such that bleed air delivered by the at least one turbofan engine is the source of heated air.

Assignees

• Airbus Operations Gmbh

Inventors

• Erban Marcus
• Fees Martin
• Bensmann Stefan

Classifications

• B64C9/24 Primary

  by single flap · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64D27/18

  within, or attached to, wings · CPC title

• B64D13/06

  the air being conditioned (pressurising B64D13/02) · CPC title

• B64D2013/0607

  providing hot air or liquid for deicing aircraft parts, e.g. aerodynamic surfaces or windows · CPC title