Combustion liner with open cell foam and acoustic damping layers

Patent metadata

Field	Value
Publication number	US-9310079-B2
Application number	US-201113162103-A
Country	US
Kind code	B2
Filing date	Jun 16, 2011
Priority date	Dec 30, 2010
Publication date	Apr 12, 2016
Grant date	Apr 12, 2016

Abstract

The disclosure is directed to a gas turbine engine combustion liner and a gas turbine engine. The gas turbine engine combustion liner may include a thermally cooled wall section, an acoustically damped wall section, or a thermally cooled and acoustically damped wall section. Open cell foam or honeycomb may be disposed between inner and outer combustion liner walls. The walls, open cell foam, or honeycomb may be made of a composite material.

First claim

What is claimed is:

1. A combustion liner, comprising:
an outer combustion liner wall;
an inner combustion liner wall;
an open cell foam disposed between the outer combustion liner wall and the inner combustion liner wall, wherein at least one of the outer combustion liner wall and the inner combustion liner wall includes a plurality of openings extending therethrough; and
a plurality of cells exposed to the plurality of openings;
wherein the open cell foam is formed of a composite material, wherein the composite material of the open cell foam is a ceramic matrix composite.

2. The combustion liner of claim 1 , wherein the outer combustion liner wall, the inner combustion liner wall and the open cell foam are formed of one or more composite materials.

3. The combustion liner of claim 2 , wherein the one or more composite materials includes a ceramic matrix composite.

4. The combustion liner of claim 1 , wherein the outer combustion liner wall, the inner combustion liner wall and the open cell foam are formed as a unitary structure.

5. The combustion liner of claim 1 , wherein the inner combustion liner wall includes the plurality of openings; wherein the plurality of cells forms a honeycomb; and wherein the plurality of cells and the plurality of openings are configured to acoustically damp vibrations at one or more selected frequencies.

6. The combustion liner of claim 1 , wherein the outer combustion liner wall includes the plurality of openings in the form of cooling air supply openings; and wherein the open cell foam is configured to distribute cooling air received from the cooling air supply openings.

7. The combustion liner of claim 6 , wherein the inner combustion liner wall includes another plurality of openings configured to discharge cooling air received from the open cell foam.

8. The combustion liner of claim 1 , wherein the open cell foam varies in nature as between different locations about the combustion liner; wherein the open cell foam is configured to distribute cooling air at one or more locations on the combustion liner; and further comprising a honeycomb formed by the plurality of cells configured to form at least part of an acoustic damper configured to acoustically damp vibrations at one or more selected frequencies at another one or more locations on the combustion liner.

9. The combustion liner of claim 8 , wherein the combustion liner includes a layer of the open cell foam and a layer of the at least part of the acoustic damper at a same location of the combustion liner.

10. The combustion liner of claim 8 , further comprising an intermediate wall disposed between the honeycomb and the open cell foam.

11. A combustion liner, comprising:
an outer combustion liner wall having a cooling air supply opening therein;
a porous open cell foam disposed in fluid communication with the cooling air supply opening; and
an inner combustion liner wall,
wherein the open cell foam is configured to distribute cooling air received from the cooling air supply opening;
wherein the inner combustion liner wall includes a plurality of openings; further comprising a honeycomb disposed between the inner combustion liner wall and the outer combustion liner wall; wherein the honeycomb includes a plurality of cells in fluid communication with the plurality of openings; wherein the plurality of cells and the plurality of openings are configured to acoustically damp vibrations at one or more selected frequencies in the combustion liner;
wherein the open cell foam includes a ceramic matrix composite.

12. The combustion liner of claim 11 , wherein the inner combustion liner wall includes a plurality of openings configured to discharge cooling air received from the open cell foam.

13. The combustion liner of claim 11 , further comprising an intermediate wall disposed between the open cell foam and the honeycomb.

14. The combustion liner of claim 11 , wherein the outer combustion liner wall, the open cell foam, the honeycomb and the inner combustion liner wall are formed integrally as a unit.

15. The combustion liner of claim 11 , wherein the outer combustion liner wall, the open cell foam and the inner combustion liner wall are formed integrally as a unit.

16. The combustion liner of claim 11 , wherein the outer combustion liner wall is a structural wall configured to support the balance of the combustion liner.

17. A gas turbine engine, comprising:
a compressor;
a combustor in fluid communication with the compressor; and
a turbine in fluid communication with the compressor; and
wherein the combustor includes a combustion liner having an outer combustion liner wall; and inner combustion liner wall; and an open cell foam including a ceramic matrix composite for cooling the combustion liner disposed between the outer combustion liner wall and the inner combustion liner wall; and means for acoustically damping vibrations disposed between the outer combustion liner wall and the inner combustion liner wall.

18. A combustion liner, comprising:
an acoustically damped wall section and a thermally cooled wall section;
wherein the acoustically damped wall section includes:
an outer combustion liner wall;
an inner combustion liner wall; and
a honeycomb disposed between the outer combustion liner wall and the inner combustion liner wall, wherein at least one of the outer combustion liner wall and the inner combustion liner wall includes a plurality of openings extending therethrough,
wherein the honeycomb includes a plurality of cells in fluid communication with the plurality of openings; and wherein the plurality of cells and the plurality of openings are configured to acoustically damp vibrations at one or more selected frequencies in the combustion liner;
wherein the honeycomb is formed of a composite material, wherein the composite material is a ceramic matrix composite; and

the thermally cooled wall section includes an open cell foam disposed between the outer combustion liner wall and the inner combustion liner wall;
wherein the acoustically damped wall section and the thermally cooled wall section vary with location along the outer combustion liner wall and/or the inner combustion liner wall.

19. The combustion liner of claim 18 , wherein the outer combustion liner wall, the inner combustion liner wall and the honeycomb are formed of one or more composite materials.

20. The combustion liner of claim 19 , wherein the one or more composite materials includes a ceramic matrix composite.

21. The combustion liner of claim 18 , wherein the outer combustion liner wall, the inner combustion liner wall and the honeycomb are formed as a unitary structure.

Assignees

• Uskert Richard Christopher
• Rolls Royce Nam Tech Inc

Inventors

• Uskert Richard Christopher

Classifications

• F23R2900/03042

  Film cooled combustion chamber walls or domes · CPC title

• F23R2900/00014

  Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators · CPC title

• F23R3/002

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

• F23M2900/05004

  Special materials for walls or lining · CPC title

• F23M20/005

  Noise absorbing means · CPC title