Heat shield with axial retention lock

Patent metadata

Field	Value
Publication number	US-10837638-B2
Application number	US-201615097269-A
Country	US
Kind code	B2
Filing date	Apr 12, 2016
Priority date	Apr 12, 2016
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape and a groove formed circumferentially along an inner surface of the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The groove in the heat shield may be configured to retain the tab of the support lock.

First claim

What is claimed is:

1. A heat shield assembly for an engine case of a gas turbine engine, comprising:
a heat shield having an annular shape about an axis and a groove formed circumferentially about this same axis along an inner surface of the heat shield, the groove comprising a first axially facing surface and a second axially facing surface that are spaced from one another in a dimension corresponding with the axis, and wherein the groove extends partially through the heat shield in a direction of an outer surface of the heat shield and terminates prior to reaching the outer surface of the heat shield such that the groove fails to extend completely through the heat shield; and
a support lock having a tab extending radially outward from a distal surface of the support lock, the tab comprising a first axially facing surface and a second axially facing surface, the support lock comprising an opening extending axially through the support lock, wherein the groove in the heat shield is configured to retain the tab of the support lock, and wherein the first axially facing surface of the groove is configured to contact the first axially facing surface of the tab and the second axially facing surface of the groove is configured to contact the second axially facing surface of the tab to prevent axial movement of the heat shield relative to the support lock.

2. The heat shield assembly of claim 1 , wherein the distal surface of the support lock is configured to be coupled to the inner surface of the heat shield.

3. The heat shield assembly of claim 2 , wherein the tab comprises a distal surface that extends between the first axially facing surface and the second axially facing surface, wherein the distal surface of the tab is spaced from the outer surface of the heat shield in the direction of the inner surface of the heat shield.

4. The heat shield assembly of claim 3 , wherein the outer surface of the heat shield forms a seal with the engine case.

5. The heat shield assembly of claim 4 , wherein the outer surface of the heat shield and an inner surface of the engine case define a gap.

6. The heat shield assembly of claim 1 , wherein the engine case comprises a diffuser case.

7. A combustor section of a gas turbine engine, comprising:
a combustor;
a diffuser case disposed about the combustor;
a heat shield having an annular shape about an axis and a groove formed circumferentially about this same axis along an inner surface of the heat shield, the heat shield disposed between the combustor and the diffuser case, the groove comprising a first axially facing surface and a second axially facing surface that are spaced from one another in a dimension corresponding with the axis, and wherein the groove extends partially through the heat shield in a direction of an outer surface of the heat shield and terminates prior to reaching the outer surface of the heat shield such that the groove fails to extend completely through the heat shield; and
a support lock having a tab extending radially outward from a distal surface of the support lock, the tab comprising a first axially facing surface and a second axially facing surface, the support lock comprising an opening extending axially through the support lock, wherein the first axially facing surface of the groove is configured to contact the first axially facing surface of the tab and the second axially facing surface of the groove is configured to contact the second axially facing surface of the tab to prevent axial movement of the heat shield relative to the support lock.

8. The combustor section of claim 7 , wherein the combustor comprises a combustor wall, wherein the heat shield is disposed between the combustor wall and the diffuser case proceeding radially outwardly relative to the axis, and wherein there is a space between the combustor wall and the heat shield proceeding radially outwardly from the combustor wall, relative to the axis, and in the direction of the heat shield and the diffuser case.

9. The combustor section of claim 7 , wherein the heat shield is disposed circumferentially along an inner surface of the diffuser case.

10. The combustor section of claim 9 , wherein an outer surface of the heat shield forms a seal with the inner surface of the diffuser case.

11. The combustor section of claim 10 , wherein the outer surface of the heat shield and the inner surface of the diffuser case define a gap.

12. The combustor section of claim 7 , wherein the support lock is configured to couple to the diffuser case.

13. The combustor section of claim 12 , wherein the support lock and the groove are configured to retain the heat shield in an axial direction.

14. A gas turbine engine, comprising:
a combustor;
a diffuser case disposed about the combustor; and
a heat shield assembly disposed between the combustor and the diffuser case, the heat shield assembly comprising:
a heat shield having an annular shape about an axis and a groove formed circumferentially about this same axis along an inner surface of the heat shield, the groove comprising a first axially facing surface and a second axially facing surface that are spaced from one another in a dimension corresponding with the axis, and wherein the groove extends partially through the heat shield in a direction of an outer surface of the heat shield and terminates prior to reaching the outer surface of the heat shield such that the groove fails to extend completely through the heat shield; and
a support lock having a tab extending radially outward from a distal surface of the support lock, the tab comprising a first axially facing surface and a second axially facing surface, the support lock comprising an opening extending axially through the support lock, wherein the groove in the heat shield is configured to retain the tab of the support lock, and wherein the first axially facing surface of the groove is configured to contact the first axially facing surface of the tab and the second axially facing surface of the groove is configured to contact the second axially facing surface of the tab to prevent axial movement of the heat shield relative to the support lock.

15. The gas turbine engine of claim 14 , wherein the heat shield is disposed circumferentially along an inner surface of the diffuser case, and wherein an outer surface of the heat shield forms a seal with the inner surface of the diffuser case.

16. The gas turbine engine of claim 15 , wherein the outer surface of the heat shield and the inner surface of the diffuser case define a gap.

17. The gas turbine engine of claim 14 , wherein the combustor comprises a combustor wall, wherein the heat shield is disposed between the combustor wall and the diffuser case proceeding radially outwardly relative to the axis, and wherein there is a space between the combustor wall and the heat shield proceeding radially outwardly from the combustor wall, relative to the axis, and in the direction of the heat shield and the diffuser case.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Sander David J
• Lemoine Jonathan

Classifications

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title

• F05D2260/31

  Retaining bolts or nuts · CPC title

• F01D25/145

  Thermally insulated casings · CPC title

• F01D25/243

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

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title