Heat shield for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-2025067438-A1
Application number	US-202318536610-A
Country	US
Kind code	A1
Filing date	Dec 12, 2023
Priority date	Aug 23, 2023
Publication date	Feb 27, 2025
Grant date	—

Abstract

A heat shield for a combustor of a gas turbine engine. The heat shield includes an annular ring having an axial direction, a radial direction, and a circumferential direction. The annular ring includes a plurality of circumferential segments. Each circumferential segment of the plurality of circumferential segments is disconnected from an adjacent circumferential segment of the plurality of circumferential segments to allow for thermal growth of each circumferential segment during operation of the combustor.

First claim

1 . A heat shield for a combustor of a gas turbine engine, the heat shield comprising:
an annular ring having an axial direction, a radial direction, and a circumferential direction, the annular ring including a plurality of circumferential segments, each circumferential segment of the plurality of circumferential segments being disconnected from an adjacent circumferential segment of the plurality of circumferential segments to allow for thermal growth of each circumferential segment during operation of the combustor.

2 . The heat shield of claim 1 , wherein the annular ring includes a plurality of radial slots, adjacent circumferential segments of the plurality of circumferential segments being disconnected from each other by one of the radial slots of the plurality of radial slots.

3 . The heat shield of claim 2 , wherein the annular ring has a width in the radial direction and includes a radially outer edge, each radial slot extending inward from the radially outer edge a distance that is less than the width of the annular ring in the radial direction.

4 . The heat shield of claim 3 , wherein the annular ring includes an inner ring portion, the inner ring portion being an inner portion of the annular ring that is free from the plurality of radial slots, each circumferential segment of the plurality of circumferential segments extending radially outward from the inner ring portion.

5 . A fuel nozzle for a gas turbine engine, the fuel nozzle comprising:
a fuel nozzle tip including a distal end; and the heat shield of claim 2 attached to the distal end of the fuel nozzle tip, wherein the distal end of the fuel nozzle tip includes a hot-side surface that has a plurality of projections extending therefrom, each projection of the plurality of projections extending into a corresponding one of the plurality of radial slots.

6 . The fuel nozzle of claim 5 , wherein each projection of the plurality of projections includes a proximal portion proximal to the hot-side surface of the fuel nozzle tip and a distal portion, each projection of the plurality of projections being tapered such that the proximal portion is wider than the distal portion, and
wherein the annular ring includes a hot-side surface and a cold-side surface, each radial slot of the plurality of radial slots being tapered such that the width of the radial slot at the hot-side surface of the annular ring is narrower than the width of the radial slot at the cold-side surface of the annular ring.

7 . The fuel nozzle of claim 5 , wherein the annular ring includes a hot-side surface that is a planar surface, and
wherein each projection of the plurality of projections includes a hot-side surface, each projection of the plurality of projections extending into the corresponding one of the plurality of radial slots such that the hot-side surface of the projection is substantially coplanar with the hot-side surface of the annular ring.

8 . The fuel nozzle of claim 7 , further comprising a thermal barrier coating formed on the hot-side surface of the annular ring and the hot-side surfaces of the plurality of projections.

9 . The heat shield of claim 1 , further comprising a plurality of plates arranged to form the annular ring, wherein each circumferential segment of the plurality of circumferential segments is a plate of the plurality of plates.

10 . The heat shield of claim 9 , wherein each plate of the plurality of plates includes a plate hot-side surface that collectively form a hot-side surface of the annular ring and are substantially coplanar with each other, a thermal barrier coating being formed on the hot-side surface of the annular ring.

11 . The heat shield of claim 9 , wherein each plate of the plurality of plates includes an inner portion and an outer portion, the outer portion of each plate being free from attachment to the outer portions of adjacent plates.

12 . The heat shield of claim 11 , wherein each plate of the plurality of plates is L-shaped having a leg extending from the inner portion of each plate of the plurality of plates in the axial direction, the legs of each plate of the plurality of plates being bonded to a ring.

13 . The heat shield of claim 11 , wherein the inner portion of each plate of the plurality of plates is bonded.

14 . The heat shield of claim 13 , further comprising an inner ring, wherein the inner portion of each plate of the plurality of plates is bonded to the inner ring.

15 . The heat shield of claim 14 , wherein each plate of the plurality of plates includes an inner surface and the inner ring includes an outer surface, the inner surface of each plate of the plurality of plates being brazed to the outer surface of the inner ring.

16 . A method of forming an annular heat shield for a combustor, the method comprising:
stacking a plurality of plates together to form an annular ring having a hole; machining an inner portion of the plurality of plates to form an inner diameter of the hole of the annular ring; placing an inner ring into the hole of the annular ring; and bonding an inner portion of each plate of the plurality of plates to the inner ring.

17 . The method of claim 16 , further comprising:
bonding an outer portion of each plate to each other prior to machining the inner portion of the plurality of plates; and machining the outer portion of each plate to remove a bond on the outer portion of each plate after machining the inner portion of the plurality of plates.

18 . The method of claim 16 , wherein machining an inner portion of the plurality of plates forms an inner surface of each plate of the plurality of plates, and bonding the inner portion of each plate of the plurality of plates to the inner ring includes brazing the inner surface of each plate of the plurality of plates to the inner ring.

19 . The method of claim 16 , wherein stacking the plurality of plates together includes positioning a plate hot-side surface of each plate of the plurality of plates such that the plate hot-side surfaces collectively form a hot-side surface of the annular ring.

20 . The method of claim 19 , further comprising coating the hot-side surface of the annular ring with a thermal barrier coating.

Assignees

• Gen Electric

Inventors

• Ganiger Ravindra Shankar
• Nath Hiranya
• Benjamin Michael A
• Clark Michael David

Classifications

• F23R3/283 Primary

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/007 Primary

  constructed mainly of ceramic components · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R3/002

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

• F23R2900/00017

  Assembling combustion chamber liners or subparts · CPC title