TURBINE ENGINE SUPPORT ASSEMBLY INCLUDING SELF ANTI-ROTATING BUSHING

• US 20140056704A1
• Filed: 08/23/2012
• Published: 02/27/2014
• Est. Priority Date: 08/23/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Harris, Meggan, Farah, Jorge I., Treat, Christopher, Dale, Timothy
• Granted Patent: US 9,482,115 B2
• Time in Patent Office: Days
• US Class Current: 415/214.1
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 25/28 Supporting or mounting arrangements, e.g. for turbine casing
• CPC Class Codes: F16B 9/054 the intermediate member being threaded
• CPC Class Codes: F16B 9/056 the intermediate member extending through the flat surface; the rod or tubular part extending through the flat surface
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49323 Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles

Abstract

A turbine engine includes multiple tierod supports. Each of the tierod supports is connected to an inner frame case of the turbine engine via multiple fasteners and at least one self anti-rotating bushing component.

Claims

1. A self anti-rotating bushing component comprising:

a first threaded bushing portion having a first threaded fastener hole;

a second threaded bushing portion having a second threaded fastener hole; and

a material tie portion connecting said first threaded bushing portion and said second threaded bushing portion.

2. The self anti-rotating bushing component of claim 1, wherein each of said first threaded bushing portion, said second threaded bushing portion, and said material tie portion are constructed of a single block of material.

3. The self anti-rotating bushing component of claim 1, wherein said first threaded bushing portion comprises a first extended threading bushing and said second threaded bushing portion comprises a second extended threading bushing such that each of said first and second bushing portions have a greater length along an axis defined by said first bushing portion than said material tie.

4. The self anti-rotating bushing component of claim 3, wherein said first extended threading bushing has a first radial wall width, said second extended threading bushing has a second radial wall width, and wherein said first radial wall width is larger than said second radial wall width.

5. The self anti-rotating bushing component of claim 3, wherein said first extended threading bushing has a first radial wall width, said second extended threading bushing has a second radial wall width, and wherein said first radial wall width and said second radial wall width are the same.

6. The self anti-rotating bushing component of claim 1, wherein threading in said first and second threaded holes is non-deforming threading.

7. The self anti-rotating bushing component of claim 1, wherein threading in said first and second threaded holes is self-locking threading.

8. The self anti-rotating bushing component of claim 1, wherein each of said first and second bushing portions include a lip portion partially circumferentially surrounding each of said threaded fastener holes, and wherein each of said lip portions has a length along an axis defined by the fastener holes equal to a thickness the material tie along an axis of either of the first or second threaded holes.

9. A turbine engine comprising:

an inner frame case and an outer frame case;

at least one support assembly connecting said inner frame case to said outer frame case, wherein said support assembly comprises a plurality of tierod support members arranged circumferentially about the inner frame case, wherein each of said tierod support members comprises an inner base portion, an outer base portion, and a stem portion, such that each tierod has a generally I-shaped cross section, and each of said inner base portions comprises a plurality of base portion fastener holes; and

wherein each of said tierod support members is connected to said inner frame case via a case connection assembly including a self anti-rotating bushing component having a first threaded bushing portion with a first threaded fastener hole, a second threaded bushing portion with a second threaded fastener hole, and a material tie portion connecting said first threaded bushing portion and said second threaded bushing portion.

10. The turbine engine of claim 9, wherein said first threaded bushing portion comprises a first extended threaded bushing and said second threaded bushing portion comprises a second extended threaded bushing such that each of said first and second bushing portions have a greater length along an axis defined by said first bushing portion than the material tie, and wherein said first extended threaded bushing portion extends into one of the plurality of base portion fastener holes and wherein said second extended threaded bushing portion extends into another of said plurality of base portion fastener holes, such that threading is extended into said base portion fastener holes.

11. The turbine engine of claim 10, wherein said first extended threaded bushing has a first radial wall width, said second extended threaded bushing has a second radial wall width, and wherein said first radial wall width is larger than said second radial wall width.

12. The turbine engine of claim 11, wherein said first extended threaded bushing is press fit in a base portion fastener hole and wherein said second extended threaded bushing is loose fit in a base portion fastener hole.

13. The turbine engine of claim 10, wherein said first extended threaded bushing extends into a base portion fastener hole having a first radius and said second extended threaded bushing extends into a second base portion hole having a second radius such that one of said first and second extended threaded bushings is press fit into a base portion fastener hole and the other of said first and second extended threaded bushings is loose fit into a base portion fastener hole.

14. The turbine engine of claim 9, wherein threading in said first and second threaded fastener holes is non-deforming threading.

15. The turbine engine of claim 9, wherein threading in said first and second threaded fastener holes is self-locking threading.

16. The turbine engine of claim 9, wherein said material tie portion of said self anti-rotating bushing component prevents rotation of said self anti-rotating bushing component during installation of a fastener.

17. A method of connecting a tierod support to a frame case comprising the steps of:

extending a first fastener through an inner frame case, through an tierod base portion, and into a first threaded bushing of a self anti-rotating bushing component;

extending a second fastener through the inner frame case, through the tierod base portion, and into a second threaded bushing of a self anti-rotating bushing component;

screwing said fasteners into the threaded bushings; and

preventing said first threaded bushing and said second threaded bushing from rotating during any of said previous steps using a material tie connecting said first threaded bushing to said second threaded bushing.

18. The method of claim 17, further comprising the step of:

press fitting one of said first threaded bushing or said second threaded bushing into a corresponding tierod base portion hole, and loose fitting the other of said first threaded bushing or said second threaded bushing into another corresponding tierod base portion hole.