Low-thickness thermostructural composite material part, and manufacture method

Patent metadata

Field	Value
Publication number	US-9784217-B2
Application number	US-201615062646-A
Country	US
Kind code	B2
Filing date	Mar 7, 2016
Priority date	Oct 30, 2009
Publication date	Oct 10, 2017
Grant date	Oct 10, 2017

Abstract

A thermostructural composite material part including carbon or ceramic fiber reinforcement densified by a matrix having at least one thin portion in which: the thickness of the part is less than 2 mm, or indeed less than 1 mm; the fiber reinforcement is made as a single thickness of multilayer fabric made of spread yarns having a weight of not less than 200 tex; the fiber volume ratio lies in the range 25% to 45%; and the ratio between the number of layers of the multilayer fabric and the thickness in millimeters of the part is not less than four.

First claim

The invention claimed is:

1. A part made of thermostructural composite material comprising carbon or ceramic fiber reinforcement densified by a matrix, wherein, in at least a portion of the part:
the thickness of the part is less than 2 mm;
the fiber reinforcement is constituted by a single thickness of multilayer fabric made up of spread yarns weighing at least 200 tex;
the fiber reinforcement having a total multilayer thickness of less than 2 mm;
the fiber volume ratio lies in the range 25% to 45%; and
the ratio between the number of layers of warp yarns of the multilayer fabric and the thickness in millimeters of the part is not less than four.

2. A part according to claim 1 , wherein, in at least said portion of the part, the part has a thickness of less than 1 mm.

3. A part according to claim 1 , wherein the number of layers of warp yarns of the multilayer fabric is not less than three.

4. A part according to claim 1 , wherein the multilayer fabric has a multi-plain, multi-serge, or multi-satin type weave.

5. A part according to claim 1 , wherein the matrix is made at least partially of ceramic.

6. A part according to claim 5 , constituting an afterbody part of a gas turbine aeroengine.

7. A part according to claim 1 , constituting at least a portion of a rocket engine nozzle exhaust cone.

Assignees

• Herakles

Inventors

• Charleux François
• Coupe Dominique
• Philippe Eric

Classifications

• C04B2235/483

  Si-containing organic compounds, e.g. silicone resins, (poly)silanes, (poly)siloxanes or (poly)silazanes · CPC title

• F05D2300/6012

  Woven fabrics · CPC title

• C04B35/62868

  Boron nitride · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• C04B2235/5248

  Carbon, e.g. graphite · CPC title