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EP-4735744-A1 - INSTALLATION FOR ASSEMBLING THE CORE OF A PANEL AND ASSOCIATED METHOD

EP4735744A1EP 4735744 A1EP4735744 A1EP 4735744A1EP-4735744-A1

Abstract

The invention relates to an installation for assembling the core of a panel of an aircraft turbine engine, comprising a bonding system (100) comprising: - a member (102) for storing and dispensing 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 storing and dispensing member (102) and a second open opposite end (108) for discharging 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).

Inventors

  • DESJOYEAUX, Bertrand Léon Marie
  • MOUTIER, JOHN
  • ROLLAND, Clément
  • LEBEGUE, Maxime
  • PROVOST, BENJAMIN
  • MESMIN, Mattias

Assignees

  • Safran Nacelles

Dates

Publication Date
20260506
Application Date
20240627

Claims (14)

  1. 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 alveolar cells (21a, 22a), the installation comprising: - a storage station for the first and second structures (21, 22), and - a station for gluing the first and second structures (21, 22), characterized in that the gluing station comprises a gluing 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 ejecting 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), the second end (108) being beveled.
  2. 2. 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°.
  3. 3. Installation according to any one of the preceding claims, characterized in that the second end (108) has a circular or elliptical section.
  4. 4. 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).
  5. 5. 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).
  6. 6. Installation according to the preceding claim, characterized in that the heat treatment device (114) comprises a nozzle heating device (104) and/or an adhesive cooling device (25) connected to the storage and distribution member (102).
  7. 7. 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).
  8. 8. 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) on the first and/or the second joining edge (23, 24).
  9. 9. Method for assembling a core (18) for a panel (17) of an aircraft turbomachine (1), the core (18) comprising at least a first and 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) together, the adhesive (25) being applied using the system (100).
  10. 10. Method according to the preceding claim, characterized in that before step (e), the method comprises the following steps: (c) provide 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).
  11. 11. Method according to any one of claims 9 to 10, characterized in that it comprises between steps (d) and (e), a step of spacing the first and second joining edges (23, 24).
  12. 12. Method according to claim 9, characterized in that it comprises the following steps carried out before step (e): (c’) provide 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).
  13. 13. Method according to any one of claims 9 to 12, characterized in that it further comprises the following step: (g) polymerize the adhesive (25).
  14. 14. Method according to any one of claims 9 to 13, characterized in that the adhesive (25) comprises an intumescent material.

Description

DESCRIPTION TITLE: INSTALLATION FOR ASSEMBLING A CORE OF A PANEL AND ASSOCIATED METHOD Technical field of the invention The invention relates to the field of installations for assembling a core of a panel for aircraft turbomachines. The invention relates in particular to installations for the assembly, by gluing, of cores having a honeycomb structure. The invention also relates to the field of methods of assembling a core for a panel of an aircraft turbomachine. Technical background The state of the art is illustrated by document EP-A1-4122695. An aircraft turbomachine comprises, for example, from upstream to downstream in the direction of gas flow along a longitudinal axis, a fan, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine, a low-pressure turbine and a gas exhaust nozzle. The blower allows the suction of an air flow dividing into a primary flow and a secondary flow. The primary flow passes through a primary vein of the turbomachine while the secondary flow is directed towards a secondary vein surrounding the primary vein. The primary flow is compressed within the compressors. The compressed air is then mixed with fuel and burned within the combustion chamber. The gases resulting from the combustion pass through the turbines and then escape through the nozzle, the section of which allows the acceleration of these gases to generate propulsion. The blower typically comprises a movable disk rotating about the longitudinal axis and blades mounted on the disk. The blades are surrounded by a fan casing centered on the longitudinal axis and intended to retain the blades in the event of damage, for example, to the blades. The fan casing is typically surrounded by a nacelle that protects the fan. Such a fan is called a shrouded fan as opposed to unshrouded fans whose blades are not surrounded by a casing. Turbomachinery, and in particular fans, are a significant source of noise pollution and there is a strong demand to reduce this type of pollution. To this end, it has been proposed to equip fan casings, for example, with acoustic panels in order to reduce the noise generated by the fans. A panel, such as an acoustic panel, typically has a sandwich structure comprising first and second skins, and between which is arranged a core having a cellular structure, for example a honeycomb structure, intended to attenuate sound waves. In the case of an acoustic panel, the second skin typically has holes allowing sound waves to propagate in the core through which they are absorbed. The core typically comprises at least first and second structures, at least one of which may comprise alveolar cells, organised for example in a honeycomb pattern, the structures being connected together by gluing during assembly of the core as part of the manufacture of the panel. According to known techniques for assembling such a core, the first structure is deposited on the first skin and an adhesive strip is manually deposited on one edge of the first structure. Then, the second structure is deposited on the first skin, edge to edge with the first structure, thus forming the core of the panel. Such a core manufacturing process has drawbacks. Indeed, the step of manually depositing the adhesive strip is tedious, long and therefore expensive. In addition, this manual deposit step is not very precise and leads to many non-conformities. Therefore, there is a need to provide a solution that enables the fabrication of a core of a panel for an aircraft turbomachine, quickly, simply and accurately. Summary of the invention For this purpose, the invention proposes an installation for assembling a core of a panel of an aircraft turbomachine, the core comprising at least first and second structures, the first structure comprising a first joining edge bonded by an adhesive to a second joining edge of the second structure, the first and second structures respectively having first and second honeycomb cells, the installation comprising: - a storage station for the first and second structures, and - a station for gluing the first and second structures. The invention is remarkable in that the gluing station comprises a gluing system comprising: - an adhesive storage and distribution device, and - an adhesive ejection nozzle, the nozzle extending between a first open end connected to the dispensing storage member and a second open opposite end for ejecting the adhesive, the nozzle further comprising an internal adhesive passage extending between the first and second ends, the second end of the nozzle being beveled. Thanks to the gluing system of the invention, it is now possible to deposit the adhesive simply, precisely and quickly. The assembly rates of the panel core are more sustained, thus allowing a considerable economic gain. The invention may comprise one or more of the following features, taken individually or in combination with each other: - the nozzle extends along an elongation axis which