Combustor inlet flow conditioner

1. A combustor, comprising:

an end cover;

a fuel nozzle assembly including at least one fuel nozzle mounted to the end cover and having an outer band that extends in an axial direction;

a combustion liner downstream of the fuel nozzle assembly;

a flow sleeve circumferentially surrounding the combustion liner;

an inlet flow conditioner circumferentially surrounding a portion of the fuel nozzle assembly, wherein the inlet flow conditioner extends axially from a forward end of the liner to an inner surface of the end cover, wherein the inlet flow conditioner comprises:

an outer sleeve comprising an aft end, the aft end of the outer sleeve axially overlapping a forward end of the flow sleeve;

an inner sleeve radially spaced between the outer sleeve and the outer band, the inner sleeve comprising an aft end, the aft end of the inner sleeve axially overlapping the forward end of the combustion liner;

a plurality of apertures defined in the inner sleeve;

a flow distribution plenum defined between the inner sleeve of the inlet flow conditioner and the outer sleeve of the inlet flow conditioner, wherein the inner sleeve and the end cover define a head end volume of the combustor, wherein the plurality of apertures provide for fluid flow between the flow distribution plenum and the head end volume, wherein an inlet to the at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume; and

a plurality of diffuser vanes that extend radially from the inner surface of the outer sleeve to the outer surface of the inner sleeve proximate to an aft end of the inlet flow conditioner, wherein the plurality of diffuser vanes is disposed upstream from the flow distribution plenum relative to a flow direction of compressed air traveling therethrough.

2. A gas turbine, comprising:

a compressor;

a turbine; and

a combustor disposed downstream from the compressor and upstream from the turbine, the combustor comprising:

an end cover;

a fuel nozzle assembly including at least one fuel nozzle mounted to the end cover and having an outer band that extends in an axial direction;

a combustion liner downstream of the fuel nozzle assembly;

a flow sleeve circumferentially surrounding the combustion liner;

an inlet flow conditioner circumferentially surrounding a portion of the fuel nozzle assembly, wherein the inlet flow conditioner extends from a forward end of the liner to an inner surface of the end cover, wherein the inlet flow conditioner comprises:

an outer sleeve comprising an aft end, the aft end of the outer sleeve axially overlapping a forward end of the flow sleeve, an outer surface of the flow sleeve slideably and sealingly engaged with an inner surface of the outer sleeve;

an inner sleeve radially spaced between the outer sleeve and the outer band, the inner sleeve comprising an aft end, the aft end of the inner sleeve axially overlapping the forward end of the combustion liner, an inner surface of the combustion liner slideably and sealingly engaged with an outer surface of the inner sleeve;

a plurality of apertures defined in the inner sleeve;

a flow distribution plenum defined between the inner sleeve of the inlet flow conditioner and the outer sleeve of the inlet flow conditioner, wherein the inner sleeve and the end cover define a head end volume of the combustor, wherein the plurality of apertures provide for fluid flow between the flow distribution plenum and the head end volume, wherein an inlet to the at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume; and

a plurality of diffuser vanes that extend radially from the inner surface of the outer sleeve to the outer surface of the inner sleeve proximate to an aft end of the inlet flow conditioner, wherein the plurality of diffuser vanes is disposed upstream from the flow distribution plenum relative to a flow direction of compressed air traveling therethrough.

3. The combustor as in claim 2 , wherein the at least one fuel nozzle is fluidly coupled to the end cover via a fluid conduit, wherein the fluid conduit is disposed within the head end volume.

4. The combustor as in claim 3 , wherein the plurality of apertures comprises a first subset of apertures circumferentially aligned with the fluid conduit, a second subset of apertures and a third subset of apertures, wherein the first subset of apertures is disposed circumferentially between the second subset of apertures and the third subset of apertures and wherein the second subset of apertures and the third subset of apertures are circumferentially offset from the fluid conduit.

5. The combustor as in claim 4 , wherein the apertures of the first subset of apertures are larger than the apertures of the second subset of apertures and the third subset of apertures.

6. The combustor as in claim 4 , wherein the apertures of the first subset of apertures are uniform in diameter.

7. The combustor as in claim 4 , wherein a diameter of each aperture of the second subset of apertures is less than or equal to a diameter of each aperture of the third subset of apertures.

8. The combustor as in claim 2 , wherein the plurality of diffuser vanes is configured to reduce non-uniformity of compressed air flowing from a compressor into the flow distribution plenum upstream from the head end volume.

9. The combustor as in claim 2 , further comprising a flange that extends radially between the inner sleeve and the outer sleeve at a forward end of the inlet flow conditioner, wherein the flange is coupled to the end cover by a series of pins that extend into the end cover, whereby the flange is in contact with the inner surface of the end cover and at least partially sealed against the inner surface of the end cover.

10. The combustor as in claim 9 , wherein both the inner sleeve and the outer sleeve extend from the forward end of the liner to the flange.