Thermal barrier washer

Patent metadata

Field	Value
Publication number	US-10883385-B2
Application number	US-201615249589-A
Country	US
Kind code	B2
Filing date	Aug 29, 2016
Priority date	Aug 29, 2016
Publication date	Jan 5, 2021
Grant date	Jan 5, 2021

Abstract

An attachment mechanism for a gas turbine engine component includes an elongated body having at least first and second ends. A first attachment feature is formed at the first end. A second attachment feature is formed at the second end. The first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component. A fan section for a gas turbine engine and a gas turbine engine are also disclosed.

First claim

The invention claimed is:

1. An attachment mechanism for a gas turbine engine component comprising:
an elongated body having at least first and second ends, wherein the elongated body comprises a rigid, straight and flat bar that extends between the first and second ends and two straight parallel sides connecting the first and second ends;
a first attachment feature formed at the first end; and
a second attachment feature formed at the second end, wherein the elongated body is solid between the first and second attachment features and the two straight parallel sides, and wherein the first and second attachment features define attachment points configured to attach a first gas turbine engine component to a second gas turbine engine component.

2. The attachment mechanism according to claim 1 , wherein the elongated body is comprised of a rigid metallic material.

3. The attachment mechanism according to claim 2 , wherein the rigid metallic material comprises aluminum.

4. The attachment mechanism according to claim 1 , wherein the first and second attachment features comprise first and second washers that are integrally formed with the elongated body as a single-piece structure.

5. The attachment mechanism according to claim 4 , wherein each washer comprises a ring-shaped body.

6. The attachment mechanism according to claim 5 , wherein the ring-shaped body includes a split.

7. The attachment mechanism according to claim 6 , wherein the split separates the ring-shaped body into first and second curved portions with respective first and second upper surfaces, and wherein the first and second upper surfaces are non-coplanar when the washers are in an uninstalled configuration.

8. The attachment mechanism according to claim 4 , wherein the first and second washers comprise split lock washers.

9. The attachment mechanism according to claim 4 , wherein the first and second washers each include a center opening, and including a first fastener extending through the center opening of the first washer and a second fastener extending through the center opening of the second washer, wherein the first and second fasteners are configured to fix the first gas turbine engine component to the second gas turbine engine component.

10. The attachment mechanism according to claim 9 , wherein the first gas turbine engine component comprises a hot duct structure and the second gas turbine engine component comprises a fan case.

11. The attachment mechanism according to claim 4 including a thermal isolation barrier that surrounds the elongated body and the first and second washers.

12. A fan section for a gas turbine engine comprising:
a fan case configured to surround a fan, wherein the fan case includes at least one mount interface;
a component configured to be attached to the mount interface; and
an attachment mechanism to attach the component to the fan via the mount interface, the attachment mechanism comprising an elongated body having at least first and second ends and two straight parallel sides connecting the first and second ends, a first attachment feature formed at the first end, and a second attachment feature formed at the second end, wherein the elongated body comprises a rigid, straight and flat bar that is solid between the first and second attachment features and the two straight parallel sides, and wherein the first and second attachment features comprise ring-shaped bodies that are integrally formed with the elongated body as a single-piece structure.

13. The fan section according to claim 12 , wherein the first and second attachment features comprise first and second washers.

14. The fan section according to claim 13 , wherein the first and second washers comprise split lock washers.

15. The fan section according to claim 13 , wherein the mount interface comprises a fan case boss that extends outwardly from an external surface of the fan case, and wherein the attachment mechanism is configured to attach the component to the fan case boss via a bracket.

16. The fan section according to claim 15 , including a thermal isolation barrier that surrounds the elongated body and the first and second washers such that the bracket directly contacts the thermal isolation barrier on one side of the attachment mechanism and the fan case boss directly contacts the thermal isolation barrier on an opposite side of the attachment mechanism.

17. The fan section according to claim 16 , wherein the first and second washers each include a center opening, and including a first fastener extending through the center opening of the first washer and a second fastener extending through the center opening of the second washer, wherein the first and second fasteners fix the component to the fan case boss.

18. The fan section according to claim 13 , wherein the fan case is comprised of a composite material, and wherein the elongated body is comprised of a rigid metallic material.

19. A gas turbine engine comprising:
a fan section that drives air along a bypass flow path via a bypass duct defined within a fan case;
a compressor section that drives air along a core flow path for compression and communication into a combustor section and subsequent expansion through a turbine section; and
a component attached to the fan case via an attachment mechanism that comprises an elongated body comprising a rigid, straight and flat bar that extends between first and second ends and two straight parallel sides connecting the first and second ends, and including a first washer formed at the first end and a second washer formed at the second end, wherein the elongated body is solid between the first and second washers and the two straight parallel sides, and wherein the first and second washers are integrally formed with the elongated body as a single-piece structure.

20. The gas turbine engine according to claim 19 , wherein the fan case includes a fan case boss and wherein the attachment mechanism is configured to attach the component to the fan case boss via a bracket, and including
a thermal isolation barrier that surrounds the elongated body and the first and second washers such that the bracket directly contacts the thermal isolation barrier on one side of the attachment mechanism and the fan case boss directly contacts the thermal isolation barrier on an opposite side of the attachment mechanism,
a first fastener extending through a center opening of the first washer, and
a second fastener extending through a center opening of the second washer, wherein the first and second fasteners fix the component to the fan case boss.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Strait Mathieu
• Islam Mainul M

Classifications

• F01D25/145 Primary

  Thermally insulated casings · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F01D25/28 Primary

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F16L59/12

  Arrangements for supporting insulation from the wall or body insulated, e.g. by means of spacers between pipe and heat-insulating material; Arrangements specially adapted for supporting insulated bodies · CPC title