Ceramic matrix composite structure

1. A composite structure comprising:

a first body made of a ceramic matrix composite material comprising fibers defining a first in-plane direction;

a second body made of a ceramic matrix composite material comprising fibers defining a second in-plane direction, the second body comprising: a first leg; a first bolting surface extending from the first leg; and at least one aperture formed in the first bolting surface substantially normal to the second in-plane direction; and

the first body connected with the second body so that the first in-plane direction is substantially normal to the second in-plane direction.

2. The composite structure of claim 1 further comprising:

a first recess formed within the first body sized to receive the first leg; and

a filament wound over a portion of the first recess to retain the first leg within the first recess.

3. The composite structure of claim 2 further comprising:

a slot formed within the first leg; and

a key fitted within the slot and affixed to the first body.

4. The composite structure of claim 1 further comprising the first body and the second body fabricated from a 2-dimensional ceramic matrix composite material and forming a component within a combustion turbine.

5. The composite structure of claim 4 further comprising:

a first recess formed within the first body sized to received a portion of the second body so that the second body may move relative to the first body; and

a filament wound over a portion of the first recess to retain the portion of the second body within the first recess.

6. The composite structure of claim 1 further comprising:

the first body fabricated from a 2-dimensional ceramic matrix composite material and forming a component within a combustion turbine;

the second body fabricated from a 2-dimensional ceramic matrix composite material forming a bolt flange, the bolt flange comprising a first leg connected with the first body and a bolting surface extending from the first leg; and

at least one aperture formed within the bolting surface in a direction substantially normal to the second in-plane direction.

7. The composite structure of claim 6 further comprising a thermal barrier coating deposited on a surface of the first body.

8. An assembly for installation in a gas turbine engine, the assembly comprising:

a component fabricated from a ceramic matrix composite material forming a first fiber direction; and

a bolt flange fabricated from a ceramic matrix composite material forming a second fiber direction, the bolt flange comprising: a leg affixed to the component: a bolting surface extending from the leg wherein the first fiber direction is substantially normal to the second fiber direction; and at least one aperture formed in the bolting surface substantially normal to the second fiber direction.

9. The assembly of claim 8 further comprising at least one aperture formed through the bolting surface and substantially normal to the second fiber direction.

10. The assembly of claim 9 further comprising an upper surface of the leg of the bolt flange positioned beneath an exterior surface of the component.

11. The assembly of claim 8 further comprising a recess formed within the component wherein the leg of the bolt flange is affixed within the recess.

12. The assembly of claim 11 further comprising a filament wound onto the component and over the leg.

13. The assembly of claim 11 further comprising:

a slot formed within the bolt flange; and

a key fitted within the slot and affixed to the component.