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A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular wall configured to direct an air flow in both an axial direction and a radial direction relative to an a

A system includes an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor. The air flow conditioner comprises a perforated annular wall configured to direct an air flow in both an axial direction and a radial direction relative to an axis of the turbine combustor. In addition, the air flow conditioner is configured to uniformly supply the air flow into air inlets of one or more fuel nozzles.

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1. A system, comprising: a turbine engine, comprising: a combustor, comprising: a combustion chamber;a liner disposed about the combustion chamber;a sleeve disposed about the liner;an air supply path between the liner and the sleeve;an air chamber;a divider disposed axially between the combustion ch

1. A system, comprising: a turbine engine, comprising: a combustor, comprising: a combustion chamber;a liner disposed about the combustion chamber;a sleeve disposed about the liner;an air supply path between the liner and the sleeve;an air chamber;a divider disposed axially between the combustion chamber and the air chamber relative to a longitudinal axis of the combustor;a fuel nozzle extending through the divider, wherein the fuel nozzle has an air inlet in the air chamber and an outlet in the combustion chamber; andan air flow conditioner disposed in the air chamber in line with the air supply path into the air chamber, wherein the air flow conditioner comprises a first perforated turning wall extending circumferentially about the longitudinal axis in a radially overlapping position relative to the air supply path, the first perforated turning wall comprises a first plurality of openings configured to pass a first portion of an air flow from the air supply path in an upstream direction away from the combustion chamber, and the first perforated turning wall is angled inwardly from the air flow path toward the longitudinal axis in the upstream direction to turn a second portion of the air flow from the air supply path inwardly toward a central region of the air chamber. 2. The system of claim 1, wherein the first perforated turning wall comprises a first perforated annular wall disposed about the longitudinal axis of the combustor, and the first perforated annular wall decreases in diameter along the longitudinal axis in the upstream direction away from the combustion chamber. 3. The system of claim 2, wherein the first perforated annular wall comprises one or more perforated conical walls disposed about the longitudinal axis. 4. The system of claim 2, wherein the first perforated annular wall curves in a convex or concave manner along the longitudinal axis. 5. The system of claim 2, wherein the air flow conditioner comprises a perforated cylinder having a second perforated annular wall disposed about the longitudinal axis of the combustor, and the second perforated annular wall has a generally constant diameter along the longitudinal axis. 6. The system of claim 5, wherein the first and second perforated annular walls are concentric with one another. 7. The system of claim 1, wherein the fuel nozzle comprises an inlet flow conditioner at the air inlet, the inlet flow conditioner comprises nozzle perforations, and the inlet flow conditioner is separate from the air flow conditioner. 8. The system of claim 1, wherein the air flow conditioner is configured to uniformly supply the air flow into the air inlet of the fuel nozzle. 9. The system of claim 1, comprising a plurality of fuel nozzles extending through the divider, wherein the air flow conditioner is configured to uniformly distribute the air flow among the plurality of fuel nozzles. 10. A system, comprising: an air flow conditioner configured to mount in an air chamber separated from a combustion chamber of a turbine combustor, wherein the air flow conditioner comprises a first perforated annular turning wall having a first plurality of openings, the first perforated annular turning wall is configured to radially overlap with an air supply path between a combustor liner and a flow sleeve of the turbine combustor, the first plurality of openings is configured to pass a first portion of an air flow from the air supply path in an upstream direction away from the combustion chamber, and the first perforated annular turning wall is angled inwardly from the air flow path toward a longitudinal axis of the turbine combustor in the upstream direction to turn a second portion of the air flow from the air supply path inwardly toward a central region of the air chamber, and the air flow conditioner is configured to distribute the air flow into air inlets of one or more fuel nozzles. 11. The system of claim 10, wherein the first perforated annular turning wall decreases in diameter along the longitudinal axis in the upstream direction away from the combustion chamber. 12. The system of claim 11, wherein the first perforated annular turning wall comprises one or more perforated conical walls disposed about the longitudinal axis. 13. The system of claim 11, wherein the first perforated annular turning wall curves in a convex or concave manner along the longitudinal axis. 14. The system of claim 11, wherein the air flow conditioner comprises a perforated cylinder concentric with the first perforated annular turning wall and the longitudinal axis, and the perforated cylinder has a generally constant diameter along the longitudinal axis. 15. The system of claim 10, wherein the air flow conditioner is configured to mount in the air chamber at an axial position that is axially offset from the air inlets of the one or more fuel nozzles. 16. The system of claim 10, comprising the turbine combustor and the one or more fuel nozzles, wherein the fuel nozzles extend through a divider between the air chamber and the combustion chamber. 17. A system, comprising: a turbine combustor, comprising: a combustion chamber;a liner extending around the combustion chamber;a sleeve extending around the liner;an air supply path between the liner and the sleeve; anda head end upstream from the combustion chamber relative to a flow of combustion products, wherein the head end comprises:a fuel nozzle disposed in the head end; andan air flow conditioner disposed in the head end, wherein the air flow conditioner comprises a first perforated turning wall that radially overlaps the air supply path, the first perforated turning wall comprises a first plurality of openings, and the first perforated turning wall is angled inwardly from the air flow path toward a longitudinal axis of the turbine combustor in an upstream direction away from the combustion chamber. 18. The system of claim 17, wherein the fuel nozzle has a base mounted to an end cover of the head end, the fuel nozzle has an intermediate portion mounted to a cap of the head end, the fuel nozzle has the inlet in an air chamber between the end cover and the cap, and the air flow conditioner is disposed adjacent to the cap. 19. The system of claim 17, wherein the first plurality of openings of the first perforated turning wall is configured to pass a first portion of an air flow from the air supply path in the upstream direction away from the combustion chamber, and the first perforated turning wall is angled inwardly from the air flow path toward the longitudinal axis in the upstream direction to turn a second portion of the air flow from the air supply path inwardly toward a central region of the head end. 20. The system of claim 17, wherein the first perforated turning wall comprises a first perforated annular wall that decreases in diameter along the longitudinal axis in the upstream direction away from the combustion chamber. 21. The system of claim 17, wherein the fuel nozzle comprises an air inlet at a first axial position relative, to the longitudinal axis of the turbine combustor, wherein the air flow conditioner is disposed at a second axial position relative to the longitudinal axis, wherein the first axial position is different from the second axial position. 22. The system of claim 17, wherein the air flow conditioner comprises a second perforated wall that is concentric with the first perforated turning wall. 23. A system, comprising: an air flow conditioner configured to mount in a head end air chamber of a turbine combustor in line with an air supply path radially between a combustor liner and a flow sleeve, wherein the air flow conditioner comprises a first perforated turning wall that radially overlaps the air supply path, the first perforated turning wall comprises a first plurality of openings, the first perforated turning wall is angled inwardly from the air flow path toward a longitudinal axis of the turbine combustor in an upstream direction away from a combustion chamber, a second perforated wall is disposed in a concentric arrangement relative to the first perforated turning wall and the longitudinal axis of the turbine combustor, and the first perforated turning wall is angled related to the second perforated wall. 24. The system of claim 23, wherein the first perforated turning wall has a first diameter that decreases in the upstream direction away from the combustion chamber when mounted in the head end air chamber. 25. The system of claim 24, wherein the second perforated wall has a second diameter that is generally constant. 26. The system of claim 23, comprising the turbine combustor, a turbine engine, or a combustion thereof, having the air flow conditioner.