Heated leading-edge structure for an aircraft
AssigneeAirbus Operations GmbH
InventorsBernhard Schlipf, Florian Lorenz
Life of this patent
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Abstract
A heated leading-edge structure for an aircraft includes a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface, a rear panel arranged at least partially arranged at a distance to the inner surface, a closed chamber inside the leading-edge structure, a heating device attached inside the chamber, and an air conveying device in fluid communication with the heating device. The air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber.
Claims15
A heated leading-edge structure for an aircraft, comprising:
- a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface,
- a rear panel at least partially arranged at a distance to the inner surface,
- a closed chamber inside the leading-edge structure,
- a heating device attached inside the chamber, and
- an air conveying device in fluid communication with the heating device,
- wherein the air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber,
- wherein:
- the heating device comprises an electrical heater,
- the air conveying device comprises a fan and an electric motor, or
- both.
A heated leading-edge structure for an aircraft, comprising:
- a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface,
- a rear panel at least partially arranged at a distance to the inner surface,
- a closed chamber inside the leading-edge structure,
- a heating device attached inside the chamber,
- an air conveying device in fluid communication with the heating device,
- wherein the air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber, and
- an internal shield extending along a substantially spanwise direction from an upper part of the inner surface to a lower part of the inner surface to form the chamber at a leading-edge region of the heated leading-edge structure,
- wherein the heating device and the air conveying device are configured to convey heated air in a substantially spanwise direction inside the chamber.
A heated leading-edge structure for an aircraft, comprising:
- a leading-edge panel having an outer surface configured to be contacted by an ambient flow, and an inner surface opposite the outer surface,
- a rear panel at least partially arranged at a distance to the inner surface,
- a closed chamber inside the leading-edge structure,
- a heating device attached inside the chamber,
- an air conveying device in fluid communication with the heating device,
- wherein the air conveying device is configured to convey air from inside the chamber through the heating device to be heated and returned to the chamber, such that a circulating flow of heated air is created inside the chamber, and
- an internal flow guiding device, which extends along at least a part of the inner surface in a distance thereto to form a flow channel between the inner surface and the internal flow guiding device,
- wherein air conveying device and the heating device are arranged to convey heated air into the flow channel transverse to a spanwise direction, and
- wherein the air conveying device is sealed against the rear panel and the internal flow guiding device to urge an airflow into the flow channel.
Dependencies are inferred from the claim text.