Integral textile structure for 3-D CMC turbine airfoils

Patent metadata

Field	Value
Publication number	US-9664053-B2
Application number	US-201414179289-A
Country	US
Kind code	B2
Filing date	Feb 12, 2014
Priority date	Feb 12, 2014
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

An integral textile structure for 3-D CMC turbine airfoils includes top and bottom walls made from an angle-interlock weave, each of the walls comprising warp and weft fiber tows. The top and bottom walls are merged on a first side parallel to the warp fiber tows into a single wall along a portion of their widths, with the weft fiber tows making up the single wall interlocked through the wall's thickness such that delamination of the wall is inhibited. The single wall suitably forms the trailing edge of an airfoil; the top and bottom walls are preferably joined along a second side opposite the first side and parallel to the radial fiber tows by a continuously curved section in which the weave structure remains continuous with the weave structure in the top and bottom walls, the continuously curved section being the leading edge of the airfoil.

First claim

We claim:

1. A ceramic matrix composite (CMC) structure formed from an integral 3-D preform of reinforcing fibers, comprising:
a top wall made from an angle-interlock weave; and
a bottom wall made from an angle-interlock weave, each of said walls comprising warp and weft fiber tows;
said top and bottom walls merged on a first side parallel to the warp fiber tows into a single wall along a portion of their widths, said weft fiber tows making up said single wall interlocked through the thickness of said single wall such that delamination of said single wall is inhibited, said warp and weft fiber tows being radial and circumferential fiber tows, respectively;
wherein said top and bottom walls are joined along a second side opposite said first side and parallel to the radial fiber tows by a continuously curved section in which the weave structure remains continuous with the weave structure in the top and bottom walls.

2. The structure of claim 1 , wherein said top and bottom walls are made from a multi-layer, layer-to-layer angle-interlock weave.

3. The structure of claim 2 , wherein said multi-layer, layer-to-layer angle-interlock weave is a four-layer, layer-to-layer angle-interlock weave.

4. The structure of claim 3 , wherein said warp and weft fiber tows are arranged in columns, with three weaving ends in each warp column and four weft picks in each weft column.

5. The structure of claim 1 , wherein said structure is a turbine airfoil having leading and trailing edges, said single wall forming the trailing edge of said turbine airfoil.

6. The structure of claim 1 , wherein each of said top and bottom walls comprise at least two layers of said warp fiber tows and said single wall comprises at least four layers of said warp fiber tows.

7. The structure of claim 1 , wherein said warp and weft fiber tows comprise SiC.

8. The structure of claim 7 , further comprising a SiC matrix.

9. The structure of claim 1 , further comprising one or more metal rods that extend through the middle of said single wall parallel to said circumferential fiber tows making up said single wall.

10. The structure of claim 5 , further comprising at least one hollow core region between said top and bottom walls.

11. The structure of claim 10 , further comprising channels formed within said trailing edge which run parallel to the circumferential fiber tows between said hollow core region and the outer edge of said trailing edge.

12. The structure of claim 5 , wherein said trailing edge is tapered.

13. The structure of claim 12 , wherein said radial fiber tows include warp fill tows, said trailing edge comprising columns of said warp fill tows, said trailing edge taper effected by varying the number of warp fill tows in said columns.

14. The structure of claim 5 , wherein said structure is arranged such that said trailing edge is formed without cutting said circumferential fiber tows.

15. A ceramic matrix composite (CMC) structure formed from an integral 3-D preform of reinforcing fibers, comprising:
a top wall made from an angle-interlock weave; and
a bottom wall made from an angle-interlock weave, each of said walls comprising warp and weft fiber tows;
said top and bottom walls merged on a first side parallel to the warp fiber tows into a single wall along a portion of their widths, said weft fiber tows making up said single wall interlocked through the thickness of said single wall such that delamination of said single wall is inhibited;
wherein said structure is a turbine airfoil having leading and trailing edges, said single wall forming the trailing edge of said turbine airfoil, said warp and weft fiber tows being radial and circumferential fiber tows, respectively; and
wherein said top and bottom walls are joined along a second side opposite said first side and parallel to the radial fiber tows by a continuously curved section in which the weave structure remains continuous with the weave structure in the top and bottom walls, said continuously curved section being the leading edge of said turbine airfoil.

16. A ceramic matrix composite (CMC) structure formed from an integral 3-D preform of reinforcing fibers, comprising:
a top wall made from an angle-interlock weave; and
a bottom wall made from an angle-interlock weave, each of said walls comprising warp and weft fiber tows;
said top and bottom walls merged on a first side parallel to the warp fiber tows into a single wall along a portion of their widths, said weft fiber tows making up said single wall interlocked through the thickness of said single wall such that delamination of said single wall is inhibited;
wherein said structure is a turbine airfoil having leading and trailing edges, said single wall forming the trailing edge of said turbine airfoil, said warp and weft fiber tows being radial and circumferential fiber tows, respectively;
wherein said structure is arranged such that said trailing edge is formed without cutting said circumferential fiber tows; and
wherein said circumferential fiber tows form continuous closed paths in the circumferential direction.

17. A ceramic matrix composite (CMC) turbine airfoil formed from an integral 3-D preform of reinforced fibers, said airfoil having an associated airfoil axis and a circumferential direction which is perpendicular to said airfoil axis, comprising:
a top wall made from a multi-layer, layer-to-layer angle-interlock weave; and
a bottom wall made from a multi-layer, layer-to-layer angle-interlock weave, said top and bottom walls located above and below at least one hollow core region, each of said walls comprising radial (warp) fiber tows that run parallel to the axis of the airfoil and circumferential (weft) fiber tows that form continuous closed paths in the circumferential direction;
said top and bottom walls merged on a first side into a single wall along a portion of their widths to form the trailing edge of said airfoil, said circumferential fiber tows making up said trailing edge interlocked through the thickness of said trailing edge such that delamination of said trailing edge is inhibited.

18. The structure of claim 17 , wherein said multi-layer, layer-to-layer angle-interlock weave is a four-layer, layer-to-layer angle-interlock weave, wherein said warp and weft fiber tows are arranged in columns, with three weaving ends in each warp column and four weft picks in each weft column.

19. The structure of claim 17 , wherein said trailing edge is tapered.

20. The structure of claim 19 , wherein said radial fiber tows comprise warp tows including warp fill tows, and said circumferential fiber tows comprise weft tows, said trailing edge comprising columns of said warp fill tows, said trailing edge taper effected by varying the number of warp fill tows in said columns.

21. The structure of claim 17 , wherein said top and bottom walls are joined along a second side opposite said first side and parallel to the radial (warp) fiber tows so as to form a continuously curved section in which the weave structure remains continuous, said continuously curved section being the leading edge of said turbine airfoil.

22. A ceramic matrix composite (CMC) structure formed from an integral 3-D preform of reinforcing fibers, comprising:
a top wall made from an angle-interlock weave;
a bottom wall made from an angle-interlock weave, each of said walls comprising warp and weft fiber tows;
at least one hollow core region between said top and bottom walls, said at least one hollow core region for

Assignees

• Teledyne Scient & Imaging Llc

Inventors

• Marshall David B
• Cox Brian N
• Sudre Olivier H

Classifications

• B29B11/16

  comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F01D5/147

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title