Air acceleration at leading edge of wing

Patent metadata

Field	Value
Publication number	US-2022111951-A1
Application number	US-202117378532-A
Country	US
Kind code	A1
Filing date	Jul 16, 2021
Priority date	Oct 8, 2020
Publication date	Apr 14, 2022
Grant date	—

Abstract

Air acceleration at leading edge of aircraft wing. In one embodiment, a slat disposed along a leading edge of a wing of an aircraft. The slat includes a skin structure having an aerodynamic shape, and a hollow space within the skin structure. The slat further includes a nozzle disposed on the skin structure to accelerate air collected in the hollow space into an external environment outside the slat to increase lift and reduce drag for the wing.

First claim

1 . A slat disposed along a leading edge of a wing of an aircraft, the slat comprising:
a skin structure having an aerodynamic shape; a hollow space within the skin structure; and a nozzle disposed on the skin structure to accelerate air collected in the hollow space into an external environment outside the slat to increase lift and reduce drag for the wing.

2 . The slat of claim 1 wherein:
the nozzle is disposed on an aft surface of the slat and oriented to eject the air into a cove region between the slat and the wing.

3 . The slat of claim 2 wherein:
the nozzle is angled upward to eject the air to counter recirculating airflow in the cove region and reduce drag for the wing.

4 . The slat of claim 2 wherein:
the nozzle is angled to eject the air through a gap between the slat and the wing to energize airflow along an upper surface of the wing and increase lift for the wing.

5 . The slat of claim 2 wherein:
the nozzle is angled downward to eject the air in a circular direction in the cove to energize a wake turbulence off a trailing edge of the slat and reduce drag for the wing.

6 . The slat of claim 2 wherein:
the nozzle is oriented at an angle relative to the aft surface of the slat, and an absolute value of the angle is in a range between ten degrees and thirty degrees.

7 . The slat of claim 1 wherein:
the nozzle is disposed on a lower lip of the slat and oriented to eject the air into a cove region between the slat and the wing.

8 . The slat of claim 1 wherein:
the nozzle is disposed on an underside surface of the slat and oriented to eject the air in an aft direction.

9 . The slat of claim 1 further comprising:
an air duct to transport air from an air supply source of the aircraft to the hollow space, wherein the air supply source is one of a wing anti-ice system, an auxiliary power unit, an engine anti-ice system, an engine bleed, and a cabin air compressor.

10 . The slat of claim 1 further comprising:
a pair of air ducts including a first air duct to transport air from a first air supply source to the hollow space, and a second air duct to receive air from a second air supply source of the aircraft;
a first nozzle disposed on an underside surface of the slat and oriented to eject the air collected in the hollow space into the external environment in an aft direction; and
a second nozzle disposed on an aft surface of the slat to eject the air collected in the second air duct into a cove region between the slat and the wing.

11 . The slat of claim 1 further comprising:
a plurality of nozzles spaced from each other in a spanwise direction along the slat, the plurality of nozzles each configured to eject the air from the hollow space into the external environment.

12 . An aircraft comprising:
a wing including a leading edge; and a slat mounted at the leading edge of the wing, wherein at least one of the wing and the slat includes a nozzle to accelerate air collected inside the at least one of the wing and the slat to an external environment of the aircraft to increase lift and reduce drag for the wing.

13 . The aircraft of claim 12 further comprising:
a wing anti-ice system to heat the slat via an air duct disposed in a spanwise direction in a hollow space of the slat,
wherein the air duct transports air exhaust of the wing anti-ice system into the hollow space, and
wherein the nozzle is disposed on the slat to accelerate the air exhaust of the wing anti-ice system into the external environment.

14 . The aircraft of claim 12 further comprising:
an air supply source to supply air to the wing via an air duct disposed in a spanwise direction of the wing,
wherein the nozzle is disposed on the wing to accelerate the air in the air duct from the leading edge of the wing forward into a cove region between the wing and the slat.

15 . The aircraft of claim 12 further comprising:
a first air supply source to supply air to the slat via a first air duct in the slat;
a second air supply source to supply air to the wing via a second air duct disposed in the wing;
a first nozzle disposed on the slat to eject the air collected in the slat into a cove region between the slat and the wing; and
a second nozzle disposed on the wing to eject the air collected in the wing in the cove region between the slat and the wing.

16 . The aircraft of claim 15 wherein:
the wing includes one or more indentations extending forward and aft along an upper surface of the leading edge of the wing, the one or more indentations being covered by the slat when the slat is stowed against the wing and being exposed when the slat is deployed forward from the wing, and
the first nozzle and the second nozzle have respective orientations to accelerate air through a gap between the slat and the wing to energize airflow along the one or more indentations and increase lift for the wing.

17 . A method of improving aerodynamic airflow for a wing of an aircraft, the method comprising:
transporting air from an air supply source of the aircraft to a hollow space within a slat of the wing; and ejecting the air collected in the hollow space with a nozzle to an external environment in front of a leading edge of the wing.

18 . The method of claim 17 wherein the method further comprises:
deploying the slat forward from the leading edge of the wing to create a gap between the slat and the wing; and
ejecting the air via the nozzle through the gap between the slat and the wing.

19 . The method of claim 17 wherein transporting the air from the air supply source to the hollow space comprises:
collecting air exhaust in the hollow space from a wing anti-ice system of the aircraft.

20 . The method of claim 19 wherein the method further comprises:
ejecting the air exhaust of the anti-ice system from the hollow space of the slat to a cove region between the slat and the wing.

Assignees

• Boeing Co

Inventors

• Shmilovich Arvin
• Ziebart John Alexander
• Gally Daniel H

Classifications

• Y02T50/30

  Wing lift efficiency · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C2003/146

  comprising leading edges of particular shape · CPC title

• B64C2003/148

  comprising protuberances, e.g. for modifying boundary layer flow · CPC title

• B64D15/04

  Hot gas application · CPC title