Combustor assembly for a turbine engine

Patent metadata

Field	Value
Publication number	US-10168051-B2
Application number	US-201514842867-A
Country	US
Kind code	B2
Filing date	Sep 2, 2015
Priority date	Sep 2, 2015
Publication date	Jan 1, 2019
Grant date	Jan 1, 2019

Abstract

A combustor assembly for a gas turbine engine is provided. The combustor assembly generally includes an annular dome and a liner. The liner at least partially defines a combustion chamber and includes the forward end received within a slot defined by the annular dome. A mounting assembly attaches the forward end of the liner to the annular dome. The mounting assembly includes a pin extending through the slot and the forward end of the annular dome. The mounting assembly also includes a grommet positioned in an opening in the forward end of the liner. The grommet is also positioned around the pin to protect the liner during operation of the gas turbine engine.

First claim

What is claimed is:

1. A combustor assembly for a gas turbine engine, the combustor assembly comprising:
an annular dome including an enclosed surface defining a slot;
a liner at least partially defining a combustion chamber and extending between an aft end and a forward end, the forward end of the liner received within the slot of the annular dome; and
a mounting assembly including a pin extending through the slot and an opening in the forward end of the liner, the mounting assembly further including a metal grommet positioned in the opening in the forward end of the liner around the pin to protect the liner;
wherein the mounting assembly further includes a bushing, wherein the bushing is positioned around the pin within the slot, and wherein the grommet is positioned around the bushing and configured to slide along the bushing;
wherein the liner is comprised of a ceramic matrix composite material, and wherein the annular dome is comprised of a metal material;
wherein the grommet includes an inner collar positioned adjacent to an inner surface of the liner, an outer collar positioned adjacent to an outer surface of the liner, and a body between the inner collar and the outer collar, and wherein at least one of the inner collar or the outer collar is attached to the body by swaging.

2. The combustor assembly of claim 1 , wherein the annular dome includes a base plate and a yolk, wherein the base plate and the yolk extend substantially parallel to one another, and wherein the enclosed surface of the dome includes a surface of the base plate and a surface of the yolk such that the slot is defined between the base plate and the yolk.

3. The combustor assembly of claim 2 , wherein the pin of the mounting assembly extends through the yolk of the annular dome, the forward end of the liner, and the base plate of the annular dome.

4. The combustor assembly of claim 1 , wherein the liner is an outer liner and wherein the annular dome is an outer annular dome.

5. The combustor assembly of claim 1 , wherein the liner is an inner liner and wherein the annular dome is an inner annular dome.

6. The combustor assembly of claim 1 , wherein the outer collar is swaged onto the body of the grommet adjacent to an outside surface of the liner.

7. The combustor assembly of claim 1 , wherein the mounting assembly defines an axial direction and a radial direction, wherein the grommet includes a body defining an inner surface and an outer surface, wherein the grommet further includes an upper portion at one end along the axial direction and a lower portion at an opposite end along the axial direction, and wherein the inner surface of the body tapers outwardly generally along the radial direction at the upper portion and at the lower portion.

8. The combustor assembly of claim 7 , wherein at least a top third of the inner surface of the grommet tapers outwardly along the radial direction.

9. The combustor assembly of claim 7 , wherein at least a bottom third of the inner surface of the grommet tapers outwardly along the radial direction.

10. A gas turbine engine comprising:
a compressor section;
a turbine section mechanically coupled to the compressor section through a shaft; and
a combustor assembly disposed between the compressor section and the turbine section, the combustor assembly including
an annular dome including an enclosed surface defining a slot;
a liner at least partially defining a combustion chamber and extending between an aft end and a forward end, the forward end of the liner received within the slot of the annular dome; and
a mounting assembly including a pin extending through the slot and an opening in the forward end of the liner, the mounting assembly further including a metal grommet positioned in the opening in the forward end of the liner around the pin to protect the liner;
wherein the mounting assembly further includes a bushing, wherein the bushing is positioned around the pin within the slot, and wherein the grommet is positioned around the bushing and configured to slide along the bushing;
wherein the liner is comprised of a ceramic matrix composite material, and wherein the annular dome is comprised of a metal material;
wherein the grommet includes an inner collar positioned adjacent to an inner surface of the liner, an outer collar positioned adjacent to an outer surface of the liner, and a body between the inner collar and the outer collar, and wherein at least one of the inner collar or the outer collar is attached to the body by swaging.

11. The gas turbine of claim 10 , wherein the annular dome includes a base plate and a yolk, wherein the base plate and the yolk extend substantially parallel to one another, and wherein the enclosed surface of the dome includes a surface of the base plate and a surface of the yolk such that the slot is defined between the base plate and the yolk.

12. The gas turbine of claim 11 , wherein the pin of the mounting assembly extends through the yolk of the annular dome, the forward end of the liner, and the base plate of the annular dome.

13. The gas turbine of claim 10 , wherein the mounting assembly defines an axial direction and a radial direction, wherein the grommet includes a body defining an inner surface and an outer surface, wherein the grommet further includes an upper portion at one end along the axial direction and a lower portion at an opposite end along the axial direction, and wherein the inner surface of the body tapers outwardly generally along the radial direction at the upper portion and at the lower portion.

Assignees

• Gen Electric

Inventors

• Bloom Nicholas John
• Stieg Michael Alan
• Towle Brian Christopher

Classifications

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title

• F02C3/14

  characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) · CPC title

• F23R3/50

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

• F23R3/002

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

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title