Axisymmetric components and methods for forming axisymmetric components

Patent metadata

Field	Value
Publication number	US-10401030-B2
Application number	US-201615207814-A
Country	US
Kind code	B2
Filing date	Jul 12, 2016
Priority date	Jul 12, 2016
Publication date	Sep 3, 2019
Grant date	Sep 3, 2019

Abstract

Components and methods for forming components are provided. For example, a method for forming a component includes laying up a plurality of plies to form a component preform that defines an axis of symmetry and a circumferential direction. Laying up the plurality of plies includes overlapping ends of the plurality of plies to define overlap regions and offsetting the overlap regions along the circumferential direction such that any radial line drawn from the axis of symmetry through the plies passes through only one overlap region. In another embodiment, a component includes a body that is symmetric about an axis of symmetry and that defines a circumferential direction and a radial direction. The body is formed from a plurality of plies and has a substantially uniform thickness. Ends of the plurality of plies are overlapped to define a plurality of overlap regions, which are offset along the circumferential direction.

First claim

What is claimed is:

1. A method for forming a component, the method comprising:
laying up a plurality of plies to form a component preform, the component preform defining an axis of symmetry, a radial direction, and a circumferential direction that extends about the axis of symmetry, wherein laying up the plurality of plies includes
defining a plurality of layers along the radial direction, each layer formed by overlapping ends of a plurality of first plies with ends of a plurality of second plies, each overlapped end defining an overlap region, each first ply and each second ply comprising a plurality of fibers extending along the circumferential direction such that the fibers in the plurality of first plies extend in the same direction as the fibers in the plurality of second plies, and
offsetting the overlap regions along the circumferential direction such that any radial line drawn from the axis of symmetry through the plurality of plies passes through only one overlap region.

2. The method of claim 1 , wherein a row of axial plies is disposed between each layer, wherein each axial ply comprises a plurality of fibers extending along the axis of symmetry.

3. The method of claim 2 , wherein any radial line drawn from the axis of symmetry through the plies passes through the same number of first, second, and axial plies.

4. The method of claim 2 , further comprising:
butting adjacent axial plies in the row of axial plies against one another along their edges such that one axial ply does not overlap an adjacent axial ply in the row of axial plies.

5. The method of claim 2 , wherein each axial ply is an axial ceramic matrix composite ply such that the plurality of fibers is a plurality of ceramic fibers.

6. The method of claim 1 , wherein defining a plurality of layers comprises defining at least five layers.

7. The method of claim 1 , wherein laying up the plurality of plies comprises laying up the plurality of plies on a generally cylindrical layup tool.

8. The method of claim 7 , wherein the plurality of plies is laid up on an inner surface of the layup tool.

9. The method of claim 1 , wherein the component is an outer liner of a combustor assembly.

10. The method of claim 1 , wherein the plurality of first plies is a plurality of first ceramic matrix composite (CMC) plies and the plurality of second plies is a plurality of second CMC plies such that the plurality of fibers is a plurality of ceramic fibers.

11. A composite component, comprising:
a body, the body symmetric about an axis of symmetry, the body defining a circumferential direction about the axis of symmetry and a radial direction orthogonal to the axis of symmetry,
wherein the body is formed from a plurality of first ceramic matrix composite (CMC) plies, a plurality of second CMC plies, and a plurality of axial CMC plies,
wherein ends of the plurality of first CMC plies are overlapped with ends of the plurality of second CMC plies to define a plurality of overlap regions,
wherein the overlap regions in radially successive layers of the first and second CMC plies are offset along the circumferential direction,
wherein each first CMC ply and each second CMC ply comprises a plurality of ceramic fibers extending along the circumferential direction such that the fibers in the plurality of first CMC plies extend in the same direction as the fibers in the plurality of second CMC plies,
wherein a layer of axial CMC plies is disposed between each layer of the first and second CMC plies,
wherein any radial line drawn from the axis of symmetry through the CMC plies passes through only one overlap region and through the same number of first, second, and axial CMC plies, and
wherein the body has a substantially uniform thickness.

12. The composite component of claim 11 , wherein ends of the plurality of first CMC plies are overlapped with ends of the plurality of second CMC plies to form a continuous ring of ceramic fibers in the circumferential direction.

13. A method for forming a component, the method comprising:
laying up a plurality of ceramic matrix composite (CMC) plies to form a component preform, the component preform defining an axis of symmetry, a radial direction, and a circumferential direction that extends about the axis of symmetry, wherein laying up the plurality of CMC plies includes
defining a plurality of layers along the radial direction, each layer formed by overlapping each end of a plurality of first CMC plies with an end of a plurality of second CMC plies such that each first CMC ply in a layer overlaps two second CMC plies in the layer and each second CMC ply in the layer overlaps two first CMC plies in the layer, each overlapped end of a first CMC ply in contact with one end of a second CMC ply over a contact length,
laying up a plurality of axial CMC plies such that an axial CMC ply is disposed between each layer, and
offsetting the overlapped ends along the circumferential direction such that any radial line drawn from the axis of symmetry through the plurality of CMC plies passes through only one contact length and through the same number of first, second, and axial CMC plies,
wherein each first CMC ply and each second CMC ply comprises a plurality of ceramic fibers extending along the circumferential direction such that the fibers in the plurality of first CMC plies extend in the same direction as the fibers in the plurality of second CMC plies.

14. The method of claim 13 , further comprising processing the plurality of CMC plies to form a green state component.

15. The method of claim 14 , further comprising firing the green state component to produce a fired component.

16. The method of claim 15 , further comprising densifying the fired component to produce a final CMC component.

17. The method of claim 16 , wherein the final CMC component is generally cylindrical.

18. The method of claim 17 , wherein the final CMC component is an outer liner of a combustor assembly.

Assignees

• Gen Electric

Inventors

• Stieg Michael Alan
• Towle Brian Christopher
• Senile Darrell Glenn
• Phelps Gregory Scott
• Johnson Jeffrey Douglas

Classifications

• B29C70/386

  Automated tape laying [ATL] · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/286

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• B32B5/12

  characterised by the relative arrangement of fibres or filaments of {different layers, e.g. the fibres or filaments being parallel or perpendicular to each other} · CPC title