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A method of manufacturing a carbon composite duct assembly includes providing a first carbon composite fabric layer having a first section. The first section is formed into a first portion and a second portion. The first portion is separately moveable relative to the second portion. The first portio

A method of manufacturing a carbon composite duct assembly includes providing a first carbon composite fabric layer having a first section. The first section is formed into a first portion and a second portion. The first portion is separately moveable relative to the second portion. The first portion overlaps the second portion to define a first corner of the first carbon composite fabric layer. The first carbon composite fabric layer is formed into at least a portion of a duct extending along an axis.

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1. A method of manufacturing a carbon composite turbine engine duct assembly, comprising: a) providing a first carbon composite fabric layer having a first section;b) forming the first section into a first portion and a second portion, the first portion separately movable relative to the second port

1. A method of manufacturing a carbon composite turbine engine duct assembly, comprising: a) providing a first carbon composite fabric layer having a first section;b) forming the first section into a first portion and a second portion, the first portion separately movable relative to the second portion;c) overlapping the first portion onto the second portion to define a first corner of the first carbon composite fabric layer;d) forming the first carbon composite fabric layer into at least a first portion of a duct extending along an axis; ande) connecting the first portion to a second portion of the duct to form the carbon composite turbine engine duct assembly. 2. The method of claim 1, wherein the duct is a turbine engine duct body. 3. The method of claim 1, wherein the step of forming the first section includes cutting the first section along a line between the first portion and the second portion to create first and second tabs. 4. The method of claim 1, comprising rotating the second portion, then rotating the first portion, and then performing the step of overlapping. 5. The method of claim 1, wherein the first portion is adhered to the second portion using an adhesive to form the first corner. 6. The method of claim 1, wherein the first corner is made from a first axial flange and a first peripheral flange. 7. The method of claim 1, comprising layering a second carbon composite fabric layer onto the first carbon composite fabric layer within a mold. 8. The method of manufacturing of claim 1 wherein at least one of the first portion and the second portion form a flange of the duct. 9. The method of manufacturing of claim 8 wherein the flange extends along the axis. 10. The method of manufacturing of claim 8 wherein the flange extends transverse to the axis. 11. The method of manufacturing of claim 10 wherein the duct defines an opening, the flange extending transverse to the axis around the opening. 12. The method of manufacturing of claim 1 including the steps of: e) providing a second carbon composite fabric layer having a second section;forming the second section into a third portion and a fourth portion, the third portion separately movable relative to the fourth portion;g) overlapping the third portion onto the fourth portion to define a second corner of the second composite fabric layer; andh) layering the second carbon composite fabric layer onto the first carbon composite fabric layer so that the second corner overlaps the first corner. 13. The method of claim 12 wherein the first carbon composite fabric layer has a first plurality of carbon strands generally extending along a first carbon strand axis and the second carbon composite fabric layer has a second plurality of carbon strands generally extending along a second carbon strand axis wherein the second carbon composite fabric layer is layered onto the first carbon composite fabric layer so that the first carbon strand axis is transverse to the second carbon strand axis. 14. The method of claim 12 wherein the first portion and the second portion form a first overlap and the third portion and the fourth portion form a second overlap, wherein the second corner overlaps the first corner so that the first overlap is displaced from the second overlap. 15. The method of claim 14 including the step of: i) eliminating at least a portion of one of the first overlap and the second overlap. 16. The method of claim 14, wherein the first overlap extends along a first axis and the second overlap extends along a second axis that is transverse to the first axis. 17. The method of claim 14, comprising alternating overlaps between the first overlap and the second overlap. 18. A method of manufacturing a carbon composite turbine engine duct assembly, comprising: a) providing a first duct body with a first carbon composite fabric layer;b) extending a first axial flange from the first carbon composite fabric layer;c) extending a first peripheral flange from the first carbon composite fabric layer;d) overlapping the first axial flange onto the first peripheral flange to form a first corner of the first carbon composite fabric layer; ande) connecting the first duct body to a second duct body to from the carbon composite turbine engine duct assembly. 19. The method of claim 18 wherein the first axial flange extends from the duct body along an axis and the first peripheral flange radially extends from the duct body. 20. A method of manufacturing a carbon composite duct assembly, comprising: creating a first carbon composite fabric layer that includes a first corner made from a first axial flange and a first peripheral flange that intersects the first axial flange at the first corner;creating a second carbon composite fabric layer that includes a second corner made from a second axial flange and a second peripheral flange that intersects the second axial flange at the second corner;layering the first carbon composite fabric layer onto a mold;layering the second carbon composite fabric layer onto the first carbon composite fabric layer within the mold to form a first turbine engine duct body portion; andconnecting the first turbine engine duct body portion to a second turbine engine duct body portion to form the carbon composite duct assembly, wherein each of the first turbine engine duct body portion and the second turbine engine duct body portion represents half of the carbon composite duct assembly.