Combustor wall assembly for a turbine engine

Patent metadata

Field	Value
Publication number	US-9909761-B2
Application number	US-201514680649-A
Country	US
Kind code	B2
Filing date	Apr 7, 2015
Priority date	Apr 9, 2014
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

A wall assembly of a combustor for a turbine engine includes a shell and a liner and a sealing interface structure. A cooling cavity is defined between the shell and liner and the sealing interface structure functions to minimize leakage out of the cooling cavity. The sealing interface structure may have a sealing width that is equal to or greater than twice the thickness of the liner and/or may include a chamber located between longitudinal segments of the sealing interface structure that inhibits leakage.

First claim

What is claimed is:

1. A combustor wall assembly comprising:
a shell;
a liner having a thickness with a cooling cavity defined between the shell and the liner; and
an elongated rail sealingly engaged with and carried between the shell and the liner for resisting cooling air leakage out of the cooling cavity;
the elongated rail and the liner being integrally formed and the elongated rail comprising an inner sealing segment and an outer sealing segment with a re-circulation chamber located between the inner and outer sealing segments; and
the shell comprising an inner surface, the inner surface facing the cooling cavity and converging towards the liner as the inner surface extends towards the elongated rail.

2. The combustor wall assembly set forth in claim 1 , wherein the cooling cavity tapers toward the elongated rail.

3. The combustor wall assembly set forth in claim 1 , wherein the shell is concentric to an axis, the liner includes and extends axially between opposite first and second edges both extending circumferentially, and the elongated rail is proximate one of the first and second edges.

4. The combustor wall assembly set forth in claim 1 , wherein a plurality of cooling holes are spaced circumferentially from one-another, communicate through the liner, and are proximate the elongated rail.

5. The combustor wall assembly set forth in claim 4 , wherein a plurality of impingement holes communicate through the shell and with the cooling cavity.

6. The combustor wall assembly set forth in claim 1 , wherein a gap is defined between the liner and shell at the elongated rail that falls within the range of zero mils to ten mils.

7. A combustor wall assembly, comprising:
a shell and a liner defining a cooling cavity therebetween;
the liner comprising a rail and a surface;
the rail integrally formed with the liner and projecting out from the surface to a face; and
the face including an inner segment and an outer segment in sealing association with the shell and a mid segment spanning laterally between the inner and outer segments, wherein the inner segment, mid segment and outer segment define a recirculation chamber;
wherein the recirculation chamber is configured for selective fluid communication with the cooling cavity when the shell and the inner segment define a gap therebetween.

8. The combustor wall assembly set forth in claim 7 , wherein the rail is at a peripheral edge of the liner.

9. A combustor comprising:
a wall assembly including at least a portion having a shell, a liner, and a cooling cavity defined between the shell and liner, wherein a plurality of impingement holes in the shell are in fluid communication with the cooling cavity and a plurality of cooling holes in the liner are in fluid communication with the cooling cavity and a combustion chamber defined at least in-part by the liner; and
a sealing structure carried by and formed as an integral member of the liner in sealing association with the shell for limiting cooling air leakage out of the cooling cavity, the sealing structure having a face including an inner segment, a mid segment and an outer segment, and
wherein the mid segment and the shell define a recirculation chamber, the inner segment is in sealing association with the shell generally between the cooling cavity and the recirculation chamber, and the outer segment is in sealing association with the shell generally between the recirculation chamber and the combustion chamber.

10. The combustor set forth in claim 9 further comprising:
a bulkhead; and
wherein the wall assembly includes the portion being a forward portion engaged to the bulkhead and an aft portion.

11. The combustor set forth in claim 10 , wherein the wall assembly portion is a convergent wall assembly portion that converges toward opposite edges of the liner.

12. The combustor set forth in claim 11 , wherein the sealing structure is located at at least one of the opposite edges.

Assignees

• United Technologies Corp

Inventors

• Cunha Frank J
• Kostka Stanislav
• Snyder Timothy S

Classifications

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F02C7/28

  Arrangement of seals · CPC title

• F23R3/005 Primary

  Combined with pressure or heat exchangers · CPC title

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title