Composite material and method

1. A containment casing of a turbomachine, the containment casing comprising a composite material comprising:

a plurality of plies layered one on top of the other; and

a plurality of through-thickness fibres which join one or more of the plurality of plies to one another, wherein

the plurality of through-thickness fibres form a boundary which delineates one or more discrete regions of the composite material,

the one or more regions do not contain any through-thickness fibres, and

the one or more regions are substantially triangular or hexagonal with the sides of the triangle or hexagon being aligned in circumferential, helical, and axial directions of the containment casing to provide stiffness in said direction in case of delamination of said one or more regions.

2. The containment casing as claimed in claim 1 , wherein the plurality of through-thickness fibres forms a continuous or broken line.

3. The containment casing as claimed in claim 1 , wherein the plurality of through-thickness fibres joins one or more of the plurality of plies to one another by tufting, stiching, Z-pinning, or 3D weaving.

4. The containment casing as claimed in claim 1 , wherein the plurality of through-thickness fibres extends through the plies at an angle which is orthogonal or oblique to the plies.

5. A turbomachine comprising the containment casing as claimed in claim 1 .

6. A method of manufacturing the containment casing as claimed in claim 1 , the method comprising:

layering the plurality of plies one on top of the other; and

passing the one or more through-thickness fibres through the plies to join the one or more of the plurality of plies to one; another,

wherein the one or more through-thickness fibres forms the boundary which delineates the one or more discrete regions of the composite material.