Thermal barrier seal

Patent metadata

Field	Value
Publication number	US-10697325-B2
Application number	US-201615249547-A
Country	US
Kind code	B2
Filing date	Aug 29, 2016
Priority date	Aug 29, 2016
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A thermal barrier attachment seal for a gas turbine engine component includes a spine having a first surface and a second surface facing opposite the first surface. A first layer of insulation is provided on the first surface. A second layer of insulation is provided on the second surface to provide a thermal barrier seal between a first gas turbine engine component and a second gas turbine engine component. A fan section for a gas turbine engine is also disclosed.

First claim

The invention claimed is:

1. A thermal barrier seal for a gas turbine engine component comprising:
a spine having a first surface and a second surface facing opposite the first surface, wherein the spine comprises a rigid elongated bar having a first fastener opening at a first end of the rigid elongated bar and a second fastener opening at a second end of the rigid elongated bar;
a first layer of insulation provided on the first surface; and
a second layer of insulation provided on the second surface to provide a thermal barrier seal between a first gas turbine engine component and a second gas turbine engine component.

2. The thermal barrier seal according to claim 1 wherein the first and second layers of insulation comprise an insulation material.

3. The thermal barrier seal according to claim 1 including a third layer of insulation material provided over the first layer of insulation and a fourth layer of insulation material provided over the second layer of insulation.

4. The thermal barrier seal according to claim 3 wherein the third and fourth layers of insulation material comprise a silicone impregnated cloth that is wrapped around the spine and the first and second layers of insulation such that outwardly facing edges of the spine and the first and second layers of insulation are covered by the silicone impregnated cloth to provide the thermal barrier seal.

5. The thermal barrier seal according to claim 3 wherein the spine has a first thickness extending between the first and second surfaces, the first and second layers each have a second thickness, and the third and fourth layers each have a third thickness, and wherein the second thickness is at least two times the third thickness.

6. The thermal barrier seal according to claim 3 wherein the spine has a first thickness extending between the first and second surfaces, the first and second layers each have a second thickness, and the third and fourth layers each have a third thickness, and wherein the first thickness is at least one and a half times the third thickness.

7. The thermal barrier seal according to claim 6 wherein the second thickness is at least two times the third thickness.

8. The thermal barrier seal according to claim 1 wherein the rigid elongated bar is flat and straight between the first and second ends, the rigid elongated bar having a first washer integrally formed at the first end of the rigid elongated bar to provide first outer peripheral curved portions that includes the first fastener opening and a second washer integrally formed at the second end of the rigid elongated bar to provide second outer peripheral curved portions that include the second fastener opening.

9. The thermal barrier seal according to claim 8 wherein the elongated bar and the first and second washers are formed from an aluminum material.

10. The thermal barrier seal according to claim 8 wherein the first and second washers comprise split lock washers.

11. The thermal barrier seal according to claim 1 wherein the thermal barrier seal has a first surface that is configured to abut directly against the first gas turbine engine component and a second surface that is configured to abut directly against the second gas turbine engine component.

12. The thermal barrier seal according to claim 1 wherein the first gas turbine engine component comprises a heated component and the second gas turbine engine component comprises a fan case, and wherein the first fastener opening is configured to receive a first fastener to attach the heated component to the fan case and the second fastener opening is configured to receive a second fastener to attach the heated component to the fan case.

13. The thermal barrier seal according to claim 12 wherein an outer surface of the thermal barrier seal is recessed to fit over a fan case boss extending outwardly from the fan case.

14. 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
thermal barrier seal to attach the component to the fan case via the mount interface, the thermal barrier seal comprising
an elongated spine body having a first surface and a second surface facing opposite the first surface, the elongated spine body comprising a rigid bar with a first washer integrally formed at a first end of the elongated spine body and a second washer integrally formed at a second end of the elongated spine body,
a first layer of insulation provided on the first surface, and
a second layer of insulation provided on the second surface to provide a thermal barrier at the mount interface between the component and the fan case.

15. The fan section according to claim 14 , wherein the mount interface comprises a fan case boss that extends outwardly from an external surface of the fan case, and wherein the thermal barrier seal is configured to attach the component to the fan case boss via a bracket.

16. The fan section according to claim 14 , including a third layer of insulation material provided on top of the first layer of insulation and a fourth layer of insulation material provided on top of the second layer of insulation.

17. The fan section according to claim 16 , wherein the first and second layers of insulation comprise an insulation material, and wherein the third and fourth layers of insulation material comprise a silicone impregnated cloth that is wrapped around the elongated spine body and the first and second layers of insulation such that outwardly facing edges of the elongated spine body and the first and second layers of insulation are covered by the silicone impregnated cloth.

18. The fan section according to claim 17 , wherein the fan case is comprised of a composite material, and wherein the elongated spine body is comprised of a rigid metallic material.

19. The fan section according to claim 16 , wherein the elongated spine body has a first thickness extending between the first and second surfaces, the first and second layers each have a second thickness, and the third and fourth layers each have a third thickness, and wherein the first thickness is at least one and a half times the third thickness, and wherein the second thickness is at least two times the third thickness.

20. The fan section according to claim 16 , wherein the rigid bar is flat and straight between the first and second washers, and wherein the first and second washers each include outer peripheral curved portions with 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 a fan case boss extending outwardly from the fan case.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Strait Mathieu
• Islam Mainul M

Classifications

• F01D25/145 Primary

  Thermally insulated casings · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F16B39/24

  by means of washers, spring washers, or resilient plates that lock against the object (locking to the screw-thread F16B39/14 {, F16B39/34}, F16B39/36) · CPC title

• F05D2300/603

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

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title