Method, injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, and leading edge section with hybrid laminar flow control obtained thereof

Patent metadata

Field	Value
Publication number	US-10377464-B2
Application number	US-201715457499-A
Country	US
Kind code	B2
Filing date	Mar 13, 2017
Priority date	Mar 14, 2016
Publication date	Aug 13, 2019
Grant date	Aug 13, 2019

Abstract

This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection molding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles to close the tool. Further, the injection molding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demolded.

First claim

What is claimed is:

1. A method for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, the method comprising the steps of:
providing a plurality of elongated modules;
providing an inner mandrel shaped with an inner surface of an aerodynamic leading edge profile;
providing an outer hood shaped with an outer surface of the aerodynamic leading edge profile;
providing first and second C-shaped profiles comprising a plurality of passing-through cavities configured to receive the modules;
assembling an injection moulding tool by a method comprising:
placing the first profile on a first end of the inner mandrel, and the second profile on a second end of the inner mandrel, both profiles contacting the inner mandrel;
arranging a first extreme of each elongated module in one cavity of the first profile, and a second extreme of said module in another cavity of the second profile, both cavities positioned in a same radial direction, and such arrangement leaving a lower gap defining the thickness of the inner surface of the leading edge section; and
placing the hood on the first and second profiles to close the tool, leaving an upper gap defining the thickness of the outer surface of the leading edge section;

closing the injection moulding tool;
filling the closed injection moulding tool with an injection compound comprising resin and a reinforcing additive;
demoulding after the hardening of the injection compound to obtain a leading edge section; and
perforating the outer and the inner surface of said leading edge section to finally obtain a leading edge section with hybrid laminar flow control.

2. The method of claim 1 , wherein assembling an injection moulding tool further comprises allocating a plurality of protuberances on the inner mandrel to retain the modules along its radial directions.

3. The method of claim 2 , wherein the protuberances are placed in consecutive positions of different radial directions of the inner mandrel between its first and second ends, and wherein the protuberances are dimensioned to perforate the inner surface of the leading edge section to create suction holes for the venture effect.

4. The method of claim 2 , wherein the protuberances are fixedly allocated on the inner mandrel.

5. The method of claim 2 , wherein the protuberances are removable allocated on the inner mandrel, and wherein the demoulding step further comprises removing the protuberances from the hardened injection compound.

6. The method of claim 2 , wherein the inner mandrel comprises notches for the allocation of the protuberances.

7. The method of claim 1 , wherein the resin is a thermoplastic resin or a thermoset resin.

8. The method of claim 1 , wherein the reinforcing additive comprises at least one of the following: glass fiber, short-fiber carbon fiber, medium fiber carbon fiber, large fiber carbon fiber, ceramic flakes, metal flakes, nanoparticles, nanotubes, and nanofibers.

9. A leading edge section with hybrid laminar flow control for an aircraft, the leading edge section comprising an outer surface, an inner surface, and obtained by injecting a compound comprising thermoplastic and short-fiber in a closed injection moulding tool, and said injection moulding tool comprising:
an inner mandrel shaped with an inner surface of an aerodynamic leading edge profile and having first and second ends;
an outer hood shaped with an outer surface of an aerodynamic leading edge profile;
a plurality of elongated modules having a first and second extremes; and
first and second C-shaped profiles comprising a plurality of passing-through cavities configured to receive the modules;
wherein the first profile is placed on the first end of the inner mandrel, and the second profile is placed on the second end of the inner mandrel;
wherein the first extreme of each elongated module is arranged in one cavity of the first profile, and the second extreme of the module in another cavity of the second profile, both cavities positioned in a same radial direction;
wherein a lower gap is formed between both first and second profiles and the inner mandrel, said lower gap defining the thickness of the inner surface of the leading edge section; and
wherein the outer hood is placed on the first and second profiles forming an upper gap between said first and second profiles and the outer hood, said upper gap defining the thickness of the outer surface of the leading edge section.

10. An injection moulding tool for manufacturing a leading edge section with hybrid laminar flow control for an aircraft, comprising:
an inner mandrel having a first and second ends, and being shaped with an inner surface of an aerodynamic leading edge profile;
an outer hood shaped with an outer surface of an aerodynamic leading edge profile;
a plurality of elongated modules having a first and second extremes; and
first and second C-shaped profiles comprising a plurality of passing-through cavities configured to receive the modules;
wherein the first profile is placed on the first end of the inner mandrel, and the second profile on the second end of the inner mandrel;
wherein the first extreme of each elongated module is arranged in one cavity of the first profile, and the second extreme of the module in another cavity of the second profile, wherein both cavities are positioned in the same radial direction, and wherein a lower gap between both the first and second profiles and the inner mandrel is formed, said lower gap defining the thickness of the inner surface of the leading edge section; and
wherein the outer hood is placed on the first and second profiles forming an upper gap between both first and second profiles and the outer hood, said upper gap defining the thickness of the outer surface of the leading edge section.

11. The injection moulding tool of claim 10 , wherein the inner mandrel further comprises a plurality of protuberances on the inner mandrel to retain the modules.

12. The injection moulding tool of claim 11 , wherein the protuberances are placed in consecutive positions of different radial directions of the inner mandrel between its first and second ends, and wherein the protuberances are dimensioned to perforate the inner surface of the leading edge section to create suction holes for the venture effect.

13. The injection moulding tool of claim 11 , wherein the protuberances are fixedly allocated on the inner mandrel.

14. The injection moulding tool of claim 11 , wherein the protuberances are removable allocated on the inner mandrel.

15. The injection moulding tool of claim 11 , wherein the inner mandrel comprises notches for the allocation of the protuberances.

Assignees

• Airbus Operations Sl

Inventors

• Cebolla Garrofe Pablo
• Calero Casanova Álvaro
• Crespo Peña Soledad
• Garcïa Nieto Carlos
• Vélez De Mendizábal Alonso Iker
• Guinaldo Fernandez Enrique
• Honorato Ruiz Francisco Javier
• Torres Salas Alvaro

Classifications

• B64C2230/22

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

• B29L2031/3085

  Wings · CPC title

• B29K2105/12

  of short lengths, e.g. chopped filaments, staple fibres or bristles · CPC title

• B29C45/0055

  Shaping · CPC title

• B29C33/48

  with means for collapsing or disassembling · CPC title