Combustor assembly for a turbine engine
A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.
1. A combustor assembly for a gas turbine engine including an outer casing, the gas turbine engine defining an axial direction and a radial direction, the combustor assembly comprising:
a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber;
a damper assembly that is coupled to the liner and includes a damper spring; and
an annular dome coupled to the damper assembly, wherein the damper spring is disposed between the annular dome and the liner;
wherein the damper spring is disposed between a first portion of the annular dome that is radially inward of the liner and a second portion of the annular dome that is radially outward of the liner;
wherein the damper spring is disposed on either the first portion of the annular dome or the second portion of the annular dome; and
wherein the damper assembly further comprises a bolt extending through the first portion of the annular dome, the second portion of the annular dome, the liner, and the damper spring.
2. The combustor assembly of claim 1 , wherein the annular dome includes an attachment extension directed toward the outer casing, and wherein the damper spring is disposed on the liner in operable connection with the attachment extension to damp radial oscillation of the liner and attachment extension.
3. The combustor assembly of claim 2 , wherein the annular dome is a single annular component and the first portion of the annular dome and the second portion of the annular dome define a slot that extends circumferentially around the axial direction.
4. The combustor assembly of claim 1 , wherein the damper spring includes an annular wave spring that spans a circumferential direction about the axial direction.
5. The combustor assembly of claim 1 , wherein the annular dome is formed integrally as a single component.
6. The combustor assembly of claim 1 , wherein the annular dome is a single annular component.
7. The combustor assembly of claim 1 , wherein the damper spring is an annular ring that spans a circumferential direction about the axial direction.
8. The combustor assembly of claim 1 , wherein the combustor assembly comprises a second damper assembly extending between the outer casing and the outer surface of the liner, the second damper assembly including a selectively separable support and a second damper spring, the second damper spring being disposed between the selectively separable support and the liner.
9. The combustor assembly of claim 1 , wherein the first portion of the annular dome and the second portion of the annular dome define a slot that extends circumferentially around the axial direction.
10. The combustor assembly of claim 1 , wherein the annular dome is a single annular component and the first portion of the annular dome and the second portion of the annular dome define a slot that extends circumferentially around the axial direction.
11. A gas turbine engine defining an axial direction and a radial direction and having an outer casing, the 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
a liner at least partially defining a combustion chamber extending between an aft end and a forward end generally along the axial direction within the outer casing, the liner including an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber;
a damper assembly that is coupled to the liner and includes a damper spring; and
an annular dome coupled to the damper assembly, wherein the damper spring is disposed between the annular dome and the liner;
wherein the damper spring is disposed between a first portion of the annular dome that is radially inward of the liner and a second portion of the annular dome that is radially outward of the liner;
wherein the damper spring is disposed on either the first portion of the annular dome or the second portion of the annular dome; and
wherein the damper assembly further comprises a bolt extending through the first portion of the annular dome, the second portion of the annular dome, the liner, and the damper spring.
12. The gas turbine engine of claim 11 , wherein the annular dome includes an attachment extension directed toward the outer casing, and wherein the damper spring is disposed on the liner in operable connection with the attachment extension to damp radial oscillation of the liner and attachment extension.
13. The gas turbine engine of claim 12 , wherein the annular dome is a single annular component and the first portion of the annular dome and the second portion of the annular dome define a slot that extends circumferentially around the axial direction.
14. The gas turbine engine of claim 11 , wherein the damper spring includes an annular wave spring that spans a circumferential direction about the axial direction.
15. The combustor assembly of claim 11 , wherein the annular dome is formed integrally as a single component.
16. The combustor assembly of claim 11 , wherein the annular dome is a single annular component.
17. The combustor assembly of claim 11 , wherein the damper spring is an annular ring that spans a circumferential direction about the axial direction.
18. The combustor assembly of claim 11 , wherein the combustor assembly comprises a second damper assembly extending between the outer casing and the outer surface of the liner, the second damper assembly including a selectively separable support and a second damper spring, the second damper spring being disposed between the selectively separable support and the liner.
19. The gas turbine engine of claim 11 , wherein the first portion of the annular dome and the second portion of the annular dome define a slot that extends circumferentially around the axial direction.
20. The gas turbine engine of claim 11 , wherein the annular dome is a single annular component and the first portion of the annular dome and the second portion of the annular dome define a slot that extends circumferentially around the axial direction.