Combustor heat shield sealing

Patent metadata

Field	Value
Publication number	US-11268697-B2
Application number	US-201916537836-A
Country	US
Kind code	B2
Filing date	Aug 12, 2019
Priority date	Jan 19, 2017
Publication date	Mar 8, 2022
Grant date	Mar 8, 2022

Abstract

Combustor assemblies for gas turbine engines are provided. For example, a combustor assembly comprises a combustor dome, a first heat shield having an edge, a second heat shield having an edge, and a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield. In another embodiment, the seal has a first contact portion contacting the edge of the first heat shield, a second contact portion contacting the edge of the second heat shield edge, and a connecting portion connecting the first portion and the second portion. The first contact portion and the second contact portion project away from the connecting portion. Methods for sealing between adjacent heat shields of a combustor assembly also are provided.

First claim

What is claimed is:

1. A method for sealing between adjacent heat shields in a combustor assembly, the combustor assembly comprising a combustor dome, a first heat shield having an edge, and an adjacent second heat shield having an edge, the method comprising:
providing a seal that extends from the edge of the first heat shield to the edge of the adjacent second heat shield such that the seal spans a gap between the first heat shield and the adjacent second heat shield,
wherein each heat shield is formed from a ceramic matrix composite (CMC) material such that each heat shield is a CMC heat shield,
wherein the seal comprises a plunger having a first leg and a second leg, the first leg received within a first groove defined in the combustor dome of the combustor assembly and the second leg received within a second groove defined in the combustor dome, the plunger positioned in contact with the first heat shield and the adjacent second heat shield.

2. The method of claim 1 , further comprising forming each CMC heat shield, wherein forming each CMC heat shield comprises:
laying up a plurality of plies of the CMC material;
processing the plurality of plies to form a green state CMC heat shield;
firing the green state CMC heat shield; and
densifying the fired CMC heat shield to produce the CMC heat shield.

3. The method of claim 2 , wherein laying up the plurality of plies of the CMC material comprises laying up additional plies along each edge of each CMC heat shield such that the edges of each CMC heat shield are built up to be thicker than a body of the CMC heat shield.

4. A combustor assembly for a gas turbine engine, comprising:
a combustor dome defining a first groove and a second groove;
a first heat shield having an edge;
a second heat shield having an edge; and
a seal extending from the edge of the first heat shield to the edge of the second heat shield such that the seal spans a gap between the first heat shield and the second heat shield, the seal comprising a plunger having a first leg received within the first groove and a second leg received within the second groove, the plunger positioned in contact with the first heat shield and the second heat shield.

5. The combustor assembly of claim 4 , wherein the seal defines a plurality of openings to allow a flow of purge air therethrough.

6. The combustor assembly of claim 4 , wherein the first heat shield defines an interface surface along the edge of the first heat shield and the second heat shield defines an interface surface along the edge of the second heat shield, and wherein a first portion of the seal is positioned against the interface surface of the first heat shield and a second portion of the seal is positioned against the interface surface of the second heat shield.

7. The combustor assembly of claim 4 ,
further comprising:
a channel defined between the plunger and the combustor dome;
a spring positioned within the channel, the plunger positioned on the spring such that the spring urges the plunger into contact with the first and second heat shields.

8. A combustor assembly for a gas turbine engine, comprising:
a combustor dome defining a first groove and a second groove;
a first heat shield having an edge;
a second heat shield having an edge; and
a seal extending from the edge of the first heat shield to the edge of the second heat shield, the seal having a plunger comprising:
a first contact portion contacting the edge of the first heat shield,
a second contact portion contacting the edge of the second heat shield edge,
a connecting portion connecting the first portion and the second portion,
a first leg received within the first groove, and
a second leg received within the second groove,
wherein the first contact portion and the second contact portion project away from the connecting portion.

9. The combustor assembly of claim 8 , wherein the plunger is formed in a shape of a heat shield perimeter.

10. The combustor assembly of claim 8 , wherein the connecting portion is in contact with a spring.

Assignees

• Gen Electric

Inventors

• Stieg Michael Alan
• Proano Cadena Valeria
• Dziech Aaron Michael
• Radwanski Michael Todd
• Corsmeier Donald Michael

Classifications

• F05D2240/55

  Seals · CPC title

• F23R3/002 Primary

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

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F23R3/10

  for primary air (F23R3/06, F23R3/045 take precedence) · CPC title