Heat shield with axial retention lock

Patent metadata

Field	Value
Publication number	US-2017292702-A1
Application number	US-201615097269-A
Country	US
Kind code	A1
Filing date	Apr 12, 2016
Priority date	Apr 12, 2016
Publication date	Oct 12, 2017
Grant date	—

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 and a groove formed circumferentially along an inner surface of the heat shield; and a support lock having a tab extending radially outward from a distal surface of the support lock, wherein the groove in the heat shield is configured to retain the tab of 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 groove extends partially through the heat shield.

4 . The heat shield assembly of claim 3 , wherein an outer surface of the heat shield is continuous.

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

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

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

8 . A combustor section of a gas turbine engine, comprising:
a combustor; a diffuser case disposed about the combustor; and a heat shield having an annular shape and a groove formed circumferentially along an inner surface of the heat shield, the heat shield disposed between the combustor and the diffuser case.

9 . The combustor section of claim 8 , wherein the heat shield is configured to couple to the diffuser case.

10 . The combustor section of claim 8 , wherein the heat shield is disposed circumferentially along an inner surface of the diffuser case.

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

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

13 . The combustor section of claim 8 , wherein the groove extends partially through the heat shield and wherein an outer surface of the heat shield is continuous.

14 . The combustor section of claim 8 , further comprising a support lock having a tab extending radially outward from a distal surface of support lock, wherein the groove in the heat shield is configured to retain the tab of the support lock.

15 . The combustor section of claim 14 , wherein the support lock is configured to couple to the diffuser case.

16 . The combustor section of claim 15 , wherein the support lock and the groove are configured to retain heat shield in an axial direction.

17 . 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 and a groove formed circumferentially along an inner surface of the heat shield, and
a support lock having a tab extending radially outward from a distal surface of support lock, wherein the groove in the heat shield is configured to retain the tab of the support lock.

18 . The gas turbine engine of claim 17 , wherein the heat shield is disposed circumferentially along an inner surface of the diffuser case.

19 . The gas turbine engine of claim 18 , wherein an outer surface of the heat shield forms a seal with the inner surface of the diffuser case.

20 . The gas turbine engine of claim 19 , wherein the outer surface of the heat shield and the inner surface of the diffuser case define a gap.

Assignees

• United Technologies Corp

Inventors

• Sander David J
• Lemoine Jonathan

Classifications

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F05D2230/64

  using positioning or alignment devices for aligning or centring, e.g. pins · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2300/175

  Superalloys · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title