Boundary-layer-influencing aerodynamic part and method for producing the same

Patent metadata

Field	Value
Publication number	US-10723443-B2
Application number	US-201715458505-A
Country	US
Kind code	B2
Filing date	Mar 14, 2017
Priority date	Mar 15, 2016
Publication date	Jul 28, 2020
Grant date	Jul 28, 2020

Abstract

A boundary-layer-influencing aerodynamic part comprises a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element, an air guiding layer disposed on the carrier element and a cover layer constituting at least a part of a flow surface and being configured to have air flow there through at least in sections. The air guiding layer is configured to have air flow there through with an air flow supplied to the part, at least in certain operating phases of the part, through the cover layer and flowing in the direction of the carrier element or through the air passage aperture of the carrier element and flowing in the direction of the cover layer. The cover layer is applied directly to the air guiding layer via an additive manufacturing method.

First claim

The invention claimed is:

1. A boundary-layer-influencing aerodynamic part, comprising:
a carrier element provided with at least one air passage aperture for guiding an air flow through the carrier element,
an air guiding layer arranged on the carrier element, and
a cover layer forming at least a part of a flow surface and being configured to have an air flow there through at least in sections,
the air guiding layer is configured to
have an air flow there through with an air flow supplied to the boundary-layer-influencing aerodynamic part, at least in certain operating phases of the boundary-layer-influencing aerodynamic part, through the cover layer and flowing in the direction of the carrier element, and
have an air flow there through with an air flow supplied to the boundary-layer-influencing aerodynamic part, at least in certain operating phases of the boundary-layer-influencing aerodynamic part, through the air passage aperture of the carrier element and flowing in the direction of the cover layer, and

the cover layer is applied directly to the air guiding layer via an additive manufacturing method.

2. The boundary-layer-influencing aerodynamic part according to claim 1 , wherein at least one of
the air guiding layer is applied directly to the carrier element by means of an additive manufacturing method, or
the carrier element is produced by means of an additive manufacturing method.

3. The boundary-layer-influencing aerodynamic part according to claim 1 , wherein the carrier element is provided with a recess, which takes up at least the air guiding layer.

4. The boundary-layer-influencing aerodynamic part according to claim 3 , wherein the cover layer has at least one airtight edge section.

5. The boundary-layer-influencing aerodynamic part according to claim 4 , wherein the edge section of the cover layer is mounted on an edge section of the carrier element or a section of a basic structure.

6. The boundary-layer-influencing aerodynamic part according to claim 1 , wherein the cover layer is at least one of
perforated at least in sections, or
comprises a porous material configured to have an air flow there through.

7. The boundary-layer-influencing aerodynamic part according to claim 1 , wherein the air guiding layer comprises a porous material.

8. The boundary-layer-influencing aerodynamic part according to claim 1 , wherein the air passage aperture of the carrier element is connected to an air conveying device for at least one of the suction or ejection of air flowing through the boundary-layer-influencing aerodynamic part.

9. The boundary-layer-influencing aerodynamic part according to claim 1 , which comprises a plurality of regions with at least one of
different air volume flow removal capacities from an air layer adjacent to the cover layer, or
different air volume flow supply capacities to the air layer adjacent to the cover layer.

10. The boundary-layer-influencing aerodynamic part according to claim 9 , wherein the regions have different cross-sectional areas of at least one of
the cover layer,
the air guiding layer, or
the air passage aperture of the carrier element,

which are configured to have an air flow there through, and wherein in the respective regions a cross-sectional area of the air guiding layer which is configured to have an air flow there through is larger than a cross-sectional area of the cover layer which is configured to have an air flow there through.

11. The boundary-layer-influencing aerodynamic part according to claim 9 , wherein at least one of
the regions have a different density of perforation openings provided in the cover layer,
the regions have perforation openings of different sizes provided in the cover layer,
the cover layer has different open porosities in the regions,
the regions have air guiding layer sections with different open porosities,
the regions have a different number of air passage apertures provided in the carrier layer, or
the regions have air passage apertures of different sizes provided in the carrier layer.

12. The boundary-layer-influencing aerodynamic part according to claim 11 , wherein the regions are sealed off from one another by an air-impermeable partition wall.

13. An aircraft component which comprises a boundary-layer-influencing aerodynamic part according to claim 1 .

14. The aircraft component according to claim 1 , wherein the component comprises a wing unit.

15. The aircraft component according to claim 1 , wherein the component comprises a tail unit.

16. A method for producing a boundary-layer-influencing aerodynamic part, comprising the following steps:
providing a carrier element, which is provided with at least one air passage aperture, applying an air guiding layer to the carrier element, wherein the air guiding layer is configured
to have an air flow there through with an air flow supplied to the boundary-layer-influencing aerodynamic part, at least in certain operating phases of the boundary-layer-influencing aerodynamic part, through the cover layer and flowing in the direction of the carrier element, and
to have an air flow there through with an air flow supplied to the boundary-layer-influencing aerodynamic part, at least in certain operating phases of the boundary-layer-influencing aerodynamic part, through the air passage aperture of the carrier element and flowing in the direction of the cover layer, and

applying a cover layer constituting at least a part of a flow surface and being configured to have an air flow there through at least in sections, directly to the air guiding layer by means of an additive manufacturing method.

17. The method according to claim 16 , wherein at least one of
the air guiding layer is applied directly to the carrier element via an additive manufacturing method, or
the carrier element is produced via an additive manufacturing method.

Assignees

• Airbus Operations Gmbh

Inventors

• Ruppert Bernd
• Robrecht Volker

Classifications

• Y02T50/10

  Drag reduction · CPC title

• B64C2230/20

  by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct · CPC title

• B64C2230/22

  by using a surface having multiple apertures of relatively small openings other than slots · CPC title

• B64C21/025 Primary

  for simultaneous blowing and sucking · CPC title

• Y02T50/166

  Cross-Sectional Technologies · mapped topic