Attachment for ceramic matrix composite component

• US 7,874,059 B2
• Filed: 01/12/2006
• Issued: 01/25/2011
• Est. Priority Date: 01/12/2006
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Energy Incorporated (Siemens AG)
• Inventors: Lane, Jay E., Morrison, Jay A.
• Primary Examiner(s): Omgba; Essama
• Application Number:
  US11/330,559
• Publication Number:
  US 20100263194A1
• Time in Patent Office: 1,839 Days
• Field of Search: 295/250.2, 295/251.1, 295/251.3, 294/46, 298/89, 416/229.R, 416/229.A, 416/241.B
• US Class Current: 29/525.02
• CPC Class Codes: F16B 5/0266 using springs
• CPC Class Codes: Y10T 29/49316 Impeller making
• CPC Class Codes: Y10T 29/49323 Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
• CPC Class Codes: Y10T 29/49863 with prestressing of part
• CPC Class Codes: Y10T 29/49948 Multipart cooperating fastener [e.g., bolt and nut]
• CPC Class Codes: Y10T 29/49952 At least one part is nonmetallic
• CPC Class Codes: Y10T 29/49966 with supplemental joining
• CPC Class Codes: Y10T 29/53 Means to assemble or disassemble

Abstract

A bushing (30, 31) in a hole (26) through a ceramic matrix composite structure (20) with a flange (34, 38) on each end of the bushing (30, 31) extending beyond and around the hole and pressing against opposed surfaces (22,24) of the CMC structure (20) with a preload that resists buckling of the composite structure fibers and resists internal CMC fiber separation. A connecting element (40), such as a bolt or pin, passes through the bushing (30, 31) for engagement with a supporting element (50). The bushing (31) may be formed in place as a single piece of ceramic, and cured along with the CMC structure (20), or it may be formed as two ceramic or metal parts (32, 36) that are joined together and preloaded by threads (33). The connecting element (40) may be a pin, or it may be a bolt with a shaft threaded into one part (32) of the bushing and a head (42) that pushes the second flange (38) toward the first flange (34).

Claims

1. An attaching method comprising:

forming a ceramic matrix composite structure comprising first and second opposed surfaces and ceramic fibers disposed between the surfaces and oriented in substantial alignment with the surfaces and with a hole extending through the ceramic matrix composite structure;

disposing a bushing in the hole, the bushing comprising a first end with a first flange extending radially beyond the hole against the first surface and a second end with a second flange extending radially beyond the hole against the second surface; and

compressively bracketing the fibers of the ceramic matrix composite structure proximate the hole between the first and second flanges with a preload interlaminar compressive stress of less than five times the interlaminar tensile strength of the ceramic matrix composite structure (<

5σ

_IL^TENS).

2. The attaching method of claim 1, wherein the disposing step comprises forming the bushing in place in the hole as a single piece of a refractory material, and further comprising curing the bushing in place.

3. The attaching method of claim 1, wherein prior to the disposing step the bushing is formed as first and second parts, with the first and second flanges formed on the respective first and second parts.

4. The attaching method of claim 3, wherein first and second parts of the bushing each comprise a tubular portion for centering the respective part in the hole.

5. The attaching method of claim 4, wherein the first and second parts of the bushing are formed with mating threads on the respective tubular portions, and the disposing step comprises threading the respective tubular portions together within the hole.

6. The attaching method of claim 3, wherein the first part of the bushing comprises a tubular portion with internal threads, and the second part comprises a bolt comprising a head and a shaft with external threads, and the disposing step comprises threading the bolt into the first part of the bushing with the bolt head compressing the second flange against the second surface of the ceramic composite matrix structure.

7. The attaching method of claim 6, wherein the bolt further comprises a pin extending beyond the shaft threads opposite the head for engagement with a corresponding pin hole in an adjacent structure.

8. The attaching method of claim 6, further comprising a spring member disposed between the bolt head and the second flange.

9. The attaching method of claim 1, further comprising forming the first and second flanges to comprise a diameter of 1.5-2.5 times a diameter of the hole.

10. The attaching method of claim 1, further comprising compressively bracketing the fibers of the ceramic matrix composite structure proximate the hole between the first and second flanges with a preload interlaminar compressive stress of less than two times the interlaminar tensile strength of the ceramic matrix composite structure (<

2σ

_IL^TENS).

11. An attaching method comprising:

forming a ceramic matrix composite structure comprising first and second opposed surfaces and ceramic fibers disposed between the surfaces and oriented in substantial alignment with the surfaces and with a hole extending through the ceramic matrix composite structure;

disposing a bushing in the hole, the bushing comprising a first end with a first flange extending radially beyond the hole against the first surface and a second end with a second flange extending radially beyond the hole against the second surface;

compressively bracketing the fibers of the ceramic matrix composite structure proximate the hole between the first and second flanges; and

forming the ceramic matrix composite structure to additionally comprise a ceramic 3D reinforcing fiber weaved among the ceramic fibers oriented in substantial alignment with the surfaces, the hole interrupting the 3D reinforcing fiber to define a fiber end;

wherein the 3D reinforcing fiber end is compressively bracketed between the first flange and the second flange to secure the fiber end relative to the ceramic fibers oriented in substantial alignment with the surfaces.

12. The attaching method of claim 11, wherein the disposing step comprises forming the bushing in place in the hole as a single piece of a refractory material, and further comprising curing the bushing in place.

13. The attaching method of claim 11, wherein prior to the disposing step, the bushing is formed as first and second parts, with the first and second flanges formed on the respective first and second parts.

14. The attaching method of claim 13, wherein first and second parts of the bushing each comprise a tubular portion for centering the respective part in the hole.

15. The attaching method of claim 14, wherein the first and second parts of the bushing are formed with mating threads on the respective tubular portions, and the disposing step comprises threading the respective tubular portions together within the hole.

16. The attaching method of claim 13, wherein the first part of the bushing comprises a tubular portion with internal threads, and the second part comprises a bolt comprising a head and a shaft with external threads, and the disposing step comprises threading the bolt into the first part of the bushing with the bolt head compressing the second flange against the second surface of the ceramic composite matrix structure.

17. The attaching method of claim 16, wherein the bolt further comprises a pin extending beyond the shaft threads opposite the head for engagement with a corresponding pin hole in an adjacent structure.

18. The attaching method of claim 16, further comprising a spring member disposed between the bolt head and the second flange.

19. The attaching method of claim 11, further comprising forming the first and second flanges to comprise a diameter of 1.5-2.5 times a diameter of the hole.

20. The attaching method of claim 11, further comprising compressively bracketing the fibers of the ceramic matrix composite structure proximate the hole between the first and second flanges with a preload interlaminar compressive stress of less than five times the interlaminar tensile strength of the ceramic matrix composite structure (<

5σ

_IL^TENS).