Method of manufacturing a composite sandwich panel for an aircraft propulsion unit

Patent metadata

Field	Value
Publication number	US-10239227-B2
Application number	US-201816008208-A
Country	US
Kind code	B2
Filing date	Jun 14, 2018
Priority date	Dec 14, 2015
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

The present disclosure provides a method of manufacturing a composite sandwich panel having a core formed of a plurality of cells extending vertically between a first skin and a second skin. The method includes creating at least one first strip and a second strip from a temporary material, each strip having at least one cavity having a succession of aligned half-cells, lining the cavity of the first strip with a fibrous ply, assembling the first strip and the second strip by interlocking the cavity of the first strip with the cavity of the second strip and trapping the fibrous ply therebetween, and trimming excess temporary material of the entirety of the strips formed during the preceding assembly step so as to form a new cavity which forms a succession of aligned half-cells.

First claim

What is claimed is:

1. A method for manufacturing a sandwich panel made of a ceramic-matrix composite-material, the sandwich panel including a core formed of a plurality of cells which extend vertically between a first skin and a second skin, the method comprising:
producing at least a first strip and a second strip made of a fugitive material, each strip having at least one cavity comprising a succession of aligned half-cells;
lining at least one fibrous ply on the at least one cavity of the first strip,
assembling the first strip and the second strip by interlocking the at least one cavity of the first strip with the at least one cavity of the second strip by trapping said fibrous ply;
trimming excess fugitive material of the first and second strips formed during the assembling step to form a new cavity which forms a succession of aligned half-cells; and
repeating said producing, lining, assembling and trimming steps until the cellular core of the panel is formed.

2. The method for manufacturing a composite sandwich panel according to claim 1 further comprising a closing step including draping the first skin on a first face of the cellular core and draping the second skin on a second face of the cellular core that is formed during the production, lining, assembling and trimming steps.

3. The method for manufacturing a composite sandwich panel according to claim 2 , wherein after the closing step, the first skin and the second skin are sintered on the cellular core to assemble the cellular core and said first skin and second skin to form the composite panel.

4. The method for manufacturing a composite sandwich panel according to claim 1 , wherein each fibrous ply is made of ceramic fibers and is impregnated with slurry containing metal or mineral oxide powder to produce a ceramic matrix during a sintering operation.

5. The method for manufacturing a composite sandwich panel according to claim 4 further comprising drying the fibrous ply after each lining step.

6. The method for manufacturing a composite sandwich panel according to claim 1 , wherein during the lining step, the at least one fibrous ply is lined on the at least one cavity of an associated strip by a toothed wheel, the toothed wheel defining a shape complementary to a shape of said at least one cavity.

7. The method for manufacturing a composite sandwich panel according to claim 6 , wherein the toothed wheel is a heating wheel operable to heat and dry the at least one fibrous ply.

8. The method for manufacturing a composite sandwich panel according to claim 1 , wherein each cell of the core of the sandwich panel defines a hexagonal shape.

9. The method for manufacturing a composite sandwich panel according to claim 1 , wherein each cell of the core of the sandwich panel defines a circular shape.

10. The method for manufacturing a composite sandwich panel according to claim 1 , wherein each strip made of fugitive material defines a curved shape such that the sandwich panel defines a curved shape.

11. The method for manufacturing a composite sandwich panel according to claim 1 , wherein each fibrous ply comprises at least a first protrusion and a second protrusion folded on each side of an associated strip and adapted to cooperate with the first skin and second skin respectively.

12. The method for manufacturing a composite sandwich panel according to claim 1 , wherein the sandwich panel is adapted to equip a nacelle of an aircraft propulsion unit.

Assignees

• Safran Nacelles

Inventors

• Caruel Pierre
• Hurlin Hervé

Classifications

• B28B11/005

  Using heat to allow reshaping, e.g. to soften ceramic articles · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• B32B3/12

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title

• F02K1/822

  Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors · CPC title

• F02K1/827

  Sound absorbing structures or liners · CPC title