Gas turbine engine having a heat shield

Patent metadata

Field	Value
Publication number	US-10837637-B2
Application number	US-201615076769-A
Country	US
Kind code	B2
Filing date	Mar 22, 2016
Priority date	Mar 22, 2016
Publication date	Nov 17, 2020
Grant date	Nov 17, 2020

Abstract

A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.

First claim

The invention claimed is:

1. A gas turbine engine, comprising:
a first case having a first case first end and a first case second end, the first case second end defining a first flange;
a second case having a second case first end and a second case second end, the second case first end defining a second flange that abuts the first flange;
a turbine vane support extending between a turbine vane and the first case;
a heat shield disposed adjacent to the turbine vane support, the heat shield having an exterior surface disposed proximate an inner surface of the first case and an interior surface facing towards a combustor; and
a combustor vane support lock disposed adjacent to the turbine vane support, wherein the heat shield includes a rib engaged into a slot formed in a surface of the combustor vane support lock such that the rib is disposed radially between the slot and the inner surface of the first case, the rib extending radially inwardly from the interior surface of the heat shield.

2. The gas turbine engine of claim 1 , wherein the inner surface of the first case defines a first protrusion and defines a second protrusion spaced apart from the first protrusion.

3. The gas turbine engine of claim 2 , wherein the first protrusion engages the exterior surface of the heat shield proximate a first heat shield end and the second protrusion engages the exterior surface of the heat shield proximate a second heat shield end.

4. A gas turbine engine, comprising:
a first case having an inner surface that extends between a first case first end and a first case second end;
a combustor vane support lock coupled to a turbine vane support by a fastener that extends through the combustor vane support lock and is received within the turbine vane support disposed adjacent to the combustor vane support lock; and
a heat shield having a first heat shield end, a second heat shield end, an exterior surface that extends between the first heat shield end and the second heat shield end, and an interior surface disposed opposite the exterior surface that extends between the first heat shield end and the second heat shield end, the exterior surface of the heat shield disposed radially inboard of the first case inner surface and the interior surface of the heat shield facing towards a combustor; and
a rib extending radially inwardly from the interior surface of the heat shield;
wherein the rib is engaged into a slot formed in a surface of the combustor vane support lock such that the rib is disposed radially between the slot and the inner surface of the first case.

5. The gas turbine engine of claim 4 , wherein the rib is disposed proximate the second heat shield end.

6. The gas turbine engine of claim 4 , wherein the interior surface of the heat shield defines a ramped region that extends from the first heat shield end towards the second heat shield end.

7. The gas turbine engine of claim 4 , wherein the exterior surface of the heat shield defines a heat shield protrusion that is disposed proximate the first heat shield end.

8. The gas turbine engine of claim 4 , wherein the inner surface of the first case defines a first protrusion disposed proximate the first case first end and a second protrusion disposed proximate the first case second end.

9. The gas turbine engine of claim 8 , wherein the first protrusion engages the exterior surface of the heat shield proximate the first heat shield end and the second protrusion engages the exterior surface of the heat shield proximate the second heat shield end.

10. A heat shield provided with a gas turbine engine, comprising:
a heat shield body extending between a first heat shield end and a second heat shield end, the heat shield body having:
an exterior surface disposed radially inboard of an inner surface of a first case,
an interior surface disposed opposite the exterior surface and the interior surface facing towards a combustor; and
a rib extending radially inwardly from the interior surface of the heat shield;

wherein the rib is configured for engagement into a slot formed in a surface of a combustor vane support lock such that the rib is disposed radially between the slot and the inner surface of the first case.

11. The heat shield of claim 10 , wherein the rib is disposed proximate the second heat shield end.

12. The heat shield of claim 10 , wherein the rib inhibits axial movement of the heat shield relative to the first case.

13. The heat shield of claim 10 , wherein the interior surface defines a ramped region that extends from the first heat shield end towards the second heat shield end.

14. The heat shield of claim 10 , wherein the interior surface is at least partially provided with a thermal barrier coating.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Sander David J
• Lemoine Jonathan
• Lee Harvey C
• Petrillo Dalton C

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D11/005

  Sealing means between non relatively rotating elements · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F05D2240/15

  Heat shield · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title