Method for manufacturing a preform for composite materials

Patent metadata

Field	Value
Publication number	US-10913181-B2
Application number	US-202016793523-A
Country	US
Kind code	B2
Filing date	Feb 18, 2020
Priority date	Jul 6, 2016
Publication date	Feb 9, 2021
Grant date	Feb 9, 2021

Abstract

A method for manufacturing a preform has a non-developable end shape having, about a longitudinal axis (A), an end overall radius of curvature (R 2 ), and, in at least a longitudinal section, curved segments forming bending radii linking straight segments. The method includes a step of depositing successive layers giving the preform an initial substantially rotational shape having, about the longitudinal axis (A), an initial overall radius of curvature, then a step of deploying the preform by increasing the initial overall radius of curvature until the end overall radius of curvature is reached (R 2 ), in order to close the bending radii of the curved segments.

First claim

What is claimed is:

1. A preform of a composite material part having a final shape with a final global radius of curvature about a longitudinal axis and curved segments forming folding radii connecting substantially straight segments in at least one longitudinal section, the preform comprising:
a non-developable shape formed from a plurality of superposed reinforcing layers of fibers having an initial shape substantially of revolution, wherein the initial shape has an initial global radius of curvature less than the final global radius of curvature of the final shape and an open contour about the longitudinal axis, and the plurality of superposed reinforcing layers of fibers having the initial shape are configured to form the final shape of the composite material part and close the folding radii of the curved segments connecting the substantially straight segments in the at least one longitudinal section after baking an impregnating resin of the preform.

2. The preform according to claim 1 , wherein each curved segment has an average developed length in at least one longitudinal section or in a transversal section substantially equal to a developed length of an associated boundary layer in that section.

3. The preform according to claim 1 further comprising, about the longitudinal axis in the initial shape, a conical portion connected by curved segments to straight segments, the conical portion straightening to give a substantially planar portion in the final shape.

4. The preform according to claim 1 further comprising a thickness between 1 and 8 mm, and the folding radii of curved segments is between 5 and 30 mm.

5. The preform according to claim 1 further comprising local geometrical singularities.

6. The preform according to claim 5 , wherein the local geometrical singularities are bosses.

7. The preform according to claim 1 , wherein the initial shape includes a closed circular contour about the longitudinal axis such that the final shape forms an area less than or equal to 180° about the longitudinal axis.

8. The preform according to claim 1 , wherein a number of fiber reinforcing layers is variable.

9. The preform according to claim 1 , wherein at least one layer among the plurality of reinforcing layers comprises fibers oriented longitudinally or transversely.

10. The preform according to claim 1 , wherein fibers of the superposed reinforcing layers have orientations of 90°, +30° and −30°, compared to an orientation of 0° which is an angle of a plane passing through the longitudinal axis.

11. A turbojet engine nacelle part comprising a preform according to claim 1 .

12. A turbojet engine nacelle part comprising partial or total superposition of at least two preforms according to claim 1 .

13. The turbojet engine nacelle part according to claim 12 , wherein at least one of the preforms among the at least two preforms has a thickness decreasing towards an end of an overlap zone with the other preform.

14. A method for manufacturing the preform of the composite material part having the final shape with the final global radius of curvature about the longitudinal axis and curved segments forming folding radii connecting substantially straight segments in the at least one longitudinal section according to claim 1 , the method comprising:
depositing successive layers of fibers on a surface of a draping tool giving the non developable shape formed from the plurality of superposed reinforcing layers of fibers having the initial shape substantially of revolution, the initial shape having the initial global radius of curvature and the open contour about the longitudinal axis; and
deploying the preform by increasing the initial global radius of curvature up to the final global radius of curvature of the final shape in order to close the folding radii of the curved segments.

Assignees

• Safran Nacelles

Inventors

• Provost Benjamin
• Desjoyeaux Bertrand
• Louchard Sébastien
• Depeux Fabien

Classifications

• B29C70/302

  Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination · CPC title

• B64C7/02

  Nacelles · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• B29K2105/0872

  Prepregs · CPC title

• Y02T50/40

  Weight reduction · CPC title