Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite structure

• US 8,247,062 B2
• Filed: 05/12/2009
• Issued: 08/21/2012
• Est. Priority Date: 05/12/2009
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Morrison, Jay A., Merrill, Gary B.
• Primary Examiner(s): Loney, Donald J
• Application Number:
  US12/464,543
• Publication Number:
  US 20100291348A1
• Time in Patent Office: 1,197 Days
• Field of Search: 428/111, 428/113, 428/114, 428/156, 428/172, 428/210, 428/293.4, 607/53, 607/55, 608/06, 415/38, 415/197, 415/200, 416/97.R, 416/229.R, 416/236.A, 416/236.R, 416/241.B
• US Class Current: 428/156
• CPC Class Codes: B32B 18/00 Layered products essentially comprising ceramics, e.g. refractory products
• CPC Class Codes: C04B 2235/945 Products containing grooves, cuts, recesses or protusions
• CPC Class Codes: C04B 2237/38 Fiber or whisker reinforced
• CPC Class Codes: C04B 2237/64 Forming laminates or joined articles comprising grooves or cuts
• CPC Class Codes: C04B 35/80 Fibres, filaments, whiskers, platelets, or the like
• CPC Class Codes: Y10T 156/1039 Surface deformation only of sandwich or lamina [e.g., embossed panels]
• CPC Class Codes: Y10T 156/1044 of parallel stacked sheets only
• CPC Class Codes: Y10T 428/24124 Fibers
• CPC Class Codes: Y10T 428/24132 including grain, strips, or filamentary elements in different layers or components parallel
• CPC Class Codes: Y10T 428/24479 including variation in thickness
• CPC Class Codes: Y10T 428/24529 and conforming component on an opposite nonplanar surface
• CPC Class Codes: Y10T 428/249928 Fiber embedded in a ceramic, glass, or carbon matrix

Abstract

Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite (CMC) structure are provided. The CMC structure may be formed by a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure. A plurality of surface recesses are formed on the surfaces of the structure. For example, each of the surfaces of the composite structure may be urged against corresponding top and bottom surfaces of a tool having a plurality of asperities. The plurality of surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, and the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure.

Claims

1. A ceramic matrix composite structure in a turbine engine component, the structure comprising:

a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure; and

a plurality of surface recesses formed on the surfaces of the structure, wherein the plurality of the surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, wherein the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure in a high-temperature combustion environment of the turbine engine component.

2. The structure of claim 1, wherein a depth of the surface recesses is based on a thickness of the structure, wherein the depth of the surface recesses comprises from 10 to 50 percent of a thickness of the CMC structure.

3. The structure of claim 1, wherein a depth of the surface recesses ranges from approximately 0.5 mm to approximately 5 mm.

4. The structure of claim 1, wherein a distance spacing between adjacent surface recesses is based on a thickness of the structure, wherein the distance spacing between adjacent surface recesses comprises 150 to 500 percent of a thickness of the CMC structure.

5. The structure of claim 1, wherein the distance spacing between adjacent surface recesses is further based on a depth of the surface recesses, wherein the distance spacing between adjacent surface recesses comprises 300 to 1000 percent of the depth of said adjacent surface recesses.

6. The structure of claim 1, wherein a distance spacing between adjacent surface recesses ranges from approximately 3 mm to approximately 15 mm.

7. The structure of claim 1, wherein the surface recesses comprise discrete surface recesses.

8. The structure of claim 1, wherein the surface recesses comprise respective linearly extending recesses.

9. The structure of claim 1, wherein the surface recesses comprise respective serpentinely extending recesses.

10. The structure of claim 1, wherein the plurality of top and bottom surface recesses are arranged with respect to one another to establish a staggered arrangement configured to produce a sinusoidal out-of-plane fiber displacement.