Installation for assembling a panel core and associated method

Abstract

The invention relates to an installation for assembling a core of a panel of an aircraft turbomachine, comprising a bonding system (100) including: - an adhesive storage and distribution unit (102), and - an adhesive ejection nozzle (104), the nozzle (104) extending between a first open end (106) connected to the storage and distribution unit (102) and a second opposite open end (108) for the adhesive (25), the nozzle (104) further comprising an internal passage (105) for the adhesive (25) extending between the first and second ends (106, 108). Abbreviated figure: Figure 4

Claims

Claims

1. Installation for assembling a core (18) of a panel (17) of an aircraft turbomachine (1), the core (18) comprising at least first and second structures (21, 22), the first structure (21) comprising a first joining edge (23) bonded by an adhesive (25) to a second joining edge (24) of the second structure (22), the first and second structures (21, 22) respectively having first and second honeycomb cells (21a, 22a), the installation comprising: - a station for storing the first and second structures (21, 22), and - a station for bonding the first and second structures (21, 22), characterized in that the bonding station comprises a bonding system (100) comprising: - a storage and distribution member (102) for the adhesive (25), and - a nozzle (104) for ejecting the adhesive (25),the nozzle (104) extending between a first open end (106) connected to the dispensing storage member (102) and a second open opposite end (108) for dispensing the adhesive (25), the nozzle (104) further comprising an internal passage (105) for the adhesive (25) extending between the first and second ends (106, 108).,

2. Installation according to the preceding claim, characterized in that the second end (108) is beveled.

3. Installation according to the preceding claim, characterized in that the nozzle (104) extends along an elongation axis (X) which forms an angle (a) with a plane (P) containing the second end (108) less than 45°, preferably less than 25°.

4. Installation according to any one of the preceding claims, characterized in that the second end (108) has a circular or elliptical section.

5. Installation according to any one of the preceding claims, characterized in that the internal passage (105) has a first channel (110) and at least one second channel (112) for the passage of the adhesive (25).

6. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a device (114) for heat treatment of the adhesive (25).

7. Installation according to the preceding claim, characterized in that the heat treatment device (114) comprises a device for heating the nozzle (104) and / or an adhesive cooling device (25) connected to the storage and dispensing member (102).

8. Installation according to any one of the preceding claims, characterized in that the system (100) comprises a device (120) for applying the adhesive (25) mounted on the nozzle (102).

9. Installation according to the preceding claim, characterized in that the application device (120) comprises a squeegee (120a) mounted on the second end (108) of the nozzle (104) and configured to guide and apply the adhesive (25) to the first and / or second joining edge (23, 24).

10. A method of assembling a core (18) for a panel (17) of an aircraft turbomachine (1), the core (18) comprising at least a first and a second structure (21, 22), the first structure (21) comprising a first joining edge (23) bonded by an adhesive (25) to a second joining edge (24) of the second structure (22), the first and second structures (21, 22) respectively having first and second honeycomb cells (21a, 22a), the assembly method implementing the installation according to any one of the preceding claims and comprising the following steps: (a) providing the first structure (21), (b) providing the second structure (22), characterized in that the method further comprises the following step: (e) applying an adhesive (25) to the first edge and / or the second joining edge (23, 24) so ​​as to bond the first and second structures (21, 22) between them, the adhesive (25) being applied using the system (100).

11. Method according to the preceding claim, characterized in that before step (e), the method comprises the following steps: (c) providing a first skin (19, 20), (d) placing the first and second structures on the first skin (19, 20) so that the first joining edge (23) is opposite the second joining edge (24).

12. Method according to any one of claims 10 to 11, characterized in that it comprises between steps (d) and (e), a step of spacing the first and second joining edges (23, 24).

13. Method according to claim 10, characterized in that it comprises the following steps carried out before step (e): (c') providing a first skin (19, 20), (d') placing the first structure (21) on the first skin (19, 20), and the following step carried out after step (e): (f') placing the second structure (22) on the first skin (19, 20) and edge to edge with the first structure (21) so that the first joining edge (23) is opposite the second joining edge (24).

14. Method according to any one of claims 10 to 13, characterized in that it further comprises the following step: (g) polymerize the adhesive (25).

15. A method according to any one of claims 10 to 14, characterized in that the adhesive (25) comprises an intumescent material.

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