Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel swirler and an air swirler. The fuel swirler is configured to swirl fuel in a direction about the axis to provide swirled fuel. The fuel injector assembly is configured to inject the swirled fuel as an annular fuel flow along an axis. The air swirler is configured to swirl air in the direction about the axis to provide swirled air. The fuel injector assembly is configured to inject the swirled air as an annular air flow along the axis, adjacent and circumscribing the annular fuel flow.

Abstract: An assembly is provided which includes a swirler and a fuel nozzle. The swirler includes an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is radially between the inner wall and the outer wall. The inner passage is radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle includes a plurality of fuel outlets and a plurality of air outlets. The fuel outlets are axially aligned with the inner wall. The air outlets are axially upstream of and radially outboard of the fuel outlets.

Abstract: A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.

Abstract: A guide plate for a swirler assembly is disclosed. In various embodiments, the guide plate includes a guide plate flange configured for engagement with a swirler body having a plurality of primary swirler inlets; and a first plurality of purge holes extending through the guide plate flange and configured to introduce a first vectored purge flow into the swirler body.

Abstract: A combustor for a gas turbine engine includes an annular shell, an annular bulkhead connected to the shell, and a heat shield panel. The heat shield panel has a first surface facing a combustion chamber and a second surface opposite the first surface. The heat shield panel is mounted to the bulkhead and defines a cooling chamber between the bulkhead and the heat shield panel. The heat shield panel has a wall extending from the heat shield panel toward the bulkhead around at least a portion of a periphery of the heat shield panel. The wall includes a circumferential wall portion including at least one cooling air passage extending between the cooling chamber and a cavity defined between the circumferential wall portion and the shell. The at least one cooling air passage is configured to purge the cavity by directing a first cooling air stream from the cooling chamber into the cavity.