Combustor dome tiles

Patent metadata

Field	Value
Publication number	US-11408609-B2
Application number	US-201816171941-A
Country	US
Kind code	B2
Filing date	Oct 26, 2018
Priority date	Oct 26, 2018
Publication date	Aug 9, 2022
Grant date	Aug 9, 2022

Abstract

A tile for a combustor dome of a gas turbine engine includes a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface. The tile body extends in a radial direction from a radially inner surface to a radially outer surface. The radially inner and outer surfaces define circular arcs that are concentric with one another. The tile body extends circumferentially from a first end face to a second end face. The first end face follows a sigmoid profile and the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical tile body.

First claim

What is claimed is:

1. A the for a combustor dome of a gas turbine engine comprising: a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface, wherein the tile body extends in a radial direction from a radially inner surface to a radially outer surface, wherein the radially inner and outer surfaces define circular arcs that are concentric with one another, wherein the tile body extends circumferentially from a first end face to a second end face, wherein the first end face follows a sigmoid profile, wherein the second end face follows a sigmoid profile configured to interlock with the sigmoid profile of the first end face of another identical the body at a seam, wherein a plurality of feed arms extend radially inward from a manifold radially outboard of the tile bodies to an inner ring radially inboard of the tiles, wherein each of the feed arms include a plurality of nozzles, wherein the feed arms follow a sigmoid profile circumferentially offset from the seam between the bodies.

2. The tile as recited in claim 1 , wherein the tile body includes a ceramic matrix composite (CMC) material.

3. The tile as recited in claim 1 , wherein each of the first and second end faces of the tile body defines a pair of axially spaced apart channels, wherein each of the channels runs from the radially inner surface to the radially outer surface of the tile body.

4. The tile as recited in claim 3 , wherein each channel of at least one of the pairs of axially spaced apart channels includes a feather seal element seated therein for creating a gas seal between the tile body an identical adjacent tile body.

5. The tile as recited in claim 1 , wherein the at least one injection orifice includes six injection orifices, and wherein the first and second end faces are separated by an angular separation configured so that fifteen identical tile bodies can be circumferentially linked to form a complete annular combustor dome.

6. A combustor dome comprising: a plurality of tiles circumferentially linked to form a complete annular combustor dome wall, wherein each of the tiles includes: a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface, wherein the tile body extends in a radial direction from a radially inner surface to a radially outer surface, wherein the radially inner and outer surfaces define circular arcs that are concentric with one another, and wherein the tile body extends circumferentially from a first end face to a second end face, wherein the first end face follows a sigmoid profile, wherein the second end face follows a sigmoid profile interlocked with the sigmoid profile of the first end face of an adjacent tile body at a seam; and a plurality of feed arms extending radially inward from the manifold radially outboard of the file bodies to an inner ring radially inboard of the tiles, wherein each of the feed arms include a plurality of nozzles, wherein the feed arms follow a sigmoid profile circumferentially offset from the seam between each of the plurality of tiles.

7. The combustor dome as recited in claim 6 , wherein the plurality of tiles are sealed end to end with each other against gas flow in an axial direction except through the injection orifices.

8. The combustor dome as recited in claim 6 , wherein each tile body includes a ceramic matrix composite (CMC) material.

9. The combustor dome as recited in claim 6 , wherein each of the first and second end faces of each tile body defines a pair of axially spaced apart channels, wherein each of the channels runs from the radially inner surface to the radially outer surface of the tile body.

10. The combustor dome as recited in claim 9 , wherein each channel of at least one of the pairs of axially spaced apart channels includes a feather seal element seated therein for creating a gas seal between each tile body and an adjacent tile body.

11. The combustor dome as recited in claim 10 , wherein the sigmoid profiles radially trap the feather seal elements between each circumferentially adjacent pair of the tile bodies.

12. The combustor dome as recited in claim 6 , wherein the at least one injection orifice includes six injection orifices in each tile body, and wherein there are fifteen identical tile bodies circumferentially linked to form the complete annular combustor dome wall.

13. A multipoint injection system comprising: a manifold extending in a circumferential direction defining a plurality of flow passages each having a main portion defined through the manifold in the circumferential direction; a plurality of feed arms extending radially inward from the manifold, wherein feed arm portions of the flow passages extend through each of the feed arms; a plurality of injection nozzles, wherein each of the feed arm portions of the flow passages includes a respective outlet opening With a respective one of the injection nozzles in fluid communication with each of the outlets; a combustor dome mounted together with the manifold with the injection nozzles extending though the combustor dome, wherein the combustor dome includes: a plurality of tiles circumferentially linked to form a complete annular combustor dome wall, wherein each of the tiles includes: a tile body defining an upstream surface and an axially opposed downstream surface with at least one injection orifice defined through the tile body from the upstream surface to the downstream surface, wherein the tile body extends in a radial direction from a radially inner surface to a radially outer surface, wherein the radially inner and outer surfaces define circular arcs that are concentric with one another, and wherein the tile body extends circumferentially from a first end face to a second end face, wherein the first end face follows a sigmoid profile, wherein the second end face follows a sigmoid profile interlocked with the sigmoid profile of the first end face of an adjacent the body, at a seam; an outer combustor wall mounted to the manifold; and an inner combustor wall radially inward from the outer combustor wall, the inner combustor wall mounted to an inner ring supported from radially inward ends of the feed arms, wherein the combustor dome, injection nozzles, inner combustor wall, and outer combustor wall form an enclosure in which a majority of aft passing from a compressor side of the combustor dome must pass through the injection nozzles to reach a combustor space defined radially between the inner and outer combustor walls, wherein the plurality of feed arms extend radially inward from the manifold radially outboard of the tile bodies to an inner ring radially inboard of the tiles, wherein each of the feed arms include a plurality of nozzles, wherein the feed arms follow a sigmoid profile circumferentially offset from the seam between each of the plurality of tiles.

14. The system as recited in claim 13 , wherein the manifold and the inner ring each include bayonet flanges extending in an axial direction away from the first axial end of the manifold for interlocking the manifold with the combustor dome, the inner combustor wall, and the outer combustor wall.

15. The system as recited in claim 13 , wherein the plurality of tiles are sealed end to end with each other against gas flow in an axial direction except through the injection orifices.

16. The system as recited in claim 13 , wherein each tile body includes a ceramic matrix com

Assignees

• Delavan Inc
• Collins Engine Nozzles Inc

Inventors

• Prociw Lev Alexander
• Ryon Jason A
• Zink Gregory A

Classifications

• F23R3/005

  Combined with pressure or heat exchangers · CPC title

• F23R3/28

  characterised by the fuel supply (burners F23D) · CPC title

• F23R3/002 Primary

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

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title