Leading edge with laminar flow control and manufacturing method thereof

Patent metadata

Field	Value
Publication number	US-10532807-B2
Application number	US-201715402520-A
Country	US
Kind code	B2
Filing date	Jan 10, 2017
Priority date	Jan 12, 2016
Publication date	Jan 14, 2020
Grant date	Jan 14, 2020

Abstract

A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.

First claim

The invention claimed is:

1. A leading edge section with laminar flow control system comprising:
a perforated outer skin shaped with an aerodynamic leading edge profile;
a perforated inner skin internally arranged with respect to the outer skin;
a plurality of suction chambers formed between the outer skin and the inner skin, such that an exterior region of the leading edge section is communicated with an interior region of the leading edge section through said plurality of suction chambers,
wherein,
the leading edge section further comprises a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin,
the inner skin is joined to the stringers, such that each of the plurality of suction chambers is defined by a part of the outer skin, a part of the inner skin and a pair of consecutive stringers of the plurality of stringers, and
the inner skin comprises a set of individual U-shaped members, each of the set of individual U-shaped members having a perforated central side and two sides extending from the perforated central side such that each of the two sides overlap an adjacent one of the plurality of stringers when the inner skin is joined to the plurality of stringers, wherein the U-shaped members are consecutively arranged one after another to configure an inner skin shape, and wherein a free edge of each of the plurality of stringers is placed between two sides of two consecutive U-shaped members and is fastened to said two sides, and
for each of the set of individual U-shaped members, the perforated central side is proximal to the perforated outer skin and the two sides extend away from the perforated outer skin.

2. The leading edge section according to claim 1 , wherein the outer skin and the plurality of stringers are metallic, and wherein the plurality of stringers are welded to the outer skin.

3. The leading edge section according to claim 1 , wherein the outer skin and the plurality of stringers includes a Fiber Reinforced Composite material, and wherein the outer skin and the plurality of stringers are co-cured together.

4. The leading edge section according to claim 1 , wherein the inner skin is metallic, and is fastened to the plurality of stringers.

5. The leading edge section according to claim 1 , wherein the inner skin includes a Fiber Reinforced Composite material, and is bonded, secondary bonded or co-cured with the plurality of stringers.

6. A method for manufacturing a leading edge section integrating a laminar flow control system, in which an exterior region of the leading edge section is communicated with an interior region of the leading edge section through a plurality of suction chambers, the method comprising:
providing an outer skin having a plurality of stringers integrally formed with the outer skin, such that the stringers are span-wise arranged internally at the leading edge;
providing a perforated inner skin by conforming a plurality of individual U-shaped members, each of the plurality of individual U-shaped members having a central side and two sides extending from the central side such that each of the two sides overlap an adjacent one of the plurality of stringers when the inner skin is joined with the plurality of stringers, and arranging the U-shaped members consecutively one after another and joining the U-shaped members with the stringers by fastening means, such that a free edge of each of the plurality of stringers is placed between two sides of two consecutive U-shaped members; and
joining the inner skin with the plurality of stringers, such that each of the plurality of suction chambers is defined by a part of the outer skin, a part of the inner skin and a pair of consecutive stringers of the plurality of stringers,
wherein, for each of the set of individual U-shaped members, the central side is proximal to the perforated outer skin and the two sides extend away from the outer skin.

7. The method according to claim 6 , further comprising perforating the outer skin before joining the inner skin, or after joining the inner skin.

8. The method according to claim 6 , wherein the outer skin and the stringers are metallic, and wherein the outer skin is provided by laser welding the plurality of stringers on a surface of a substantially flat metallic panel, perforating the panel and conforming the panel with the plurality of integrated stringers to configure the outer skin with an aerodynamic leading edge profile.

9. The method according to claim 6 , wherein the outer skin and the plurality of stringers have been obtained from a Fiber Reinforced Composite material, and wherein the outer skin and the plurality of stringers are co-cured together.

Assignees

• Airbus Operations Sl

Inventors

• García Nieto Carlos
• Guinaldo Fernández Enrique
• Cebolla Garrofe Pablo
• Vélez De Mendizabal Alonso Iker
• Crespo Peña Soledad
• Honorato Ruiz Francisco Javier
• Torres Salas Álvaro
• Calero Casanova Álvaro

Classifications

• B64C3/28

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C21/06 Primary

  for sucking (BLI propulsion B64C21/01) · CPC title

• B64C2001/0081

  from metallic materials · CPC title

• B64C3/00 Primary

  Wings (ornithopter wings B64C33/02) · CPC title