Patent ID: 8234872

Claim:
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; and an 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.