Abstract: A fuel injector assembly for a gas turbine engine includes a swirler and a fuel nozzle. The swirler has an outer wall having a SOW inner wall surface, an inner wall having a SIW inner wall surface and a SIW outer wall surface, an outer passage, and an inner passage. The SIW inner wall surface includes first and second sections. The first section extends between a first airflow inlet and the second section, and the second section extends between the first section and an inner wall distal end. The first section tapers radially inward, and the second section extends parallel the center axis. The outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall is axially recessed within the swirler from the distal outer wall end. The fuel nozzle projects into the inner passage.

Abstract: An apparatus is provided for a turbine engine. This turbine engine apparatus includes a combustor wall, and the combustor wall includes a panel, a deflector and a quench aperture that extends along an aperture centerline through the combustor wall to an aperture outlet into a combustion chamber. The panel extends axially along and circumferentially about an axis. The panel extends radially between a first panel side and a second panel side. The first panel side forms a peripheral boundary of the combustion chamber. The panel forms a downstream side of the aperture outlet at the first panel side. The deflector projects out from the panel at the first panel side into the combustion chamber. The deflector forms an upstream side of the aperture outlet.

Abstract: An assembly is provided for a turbine engine. This turbine engine assembly includes an air swirler structure, an injector nozzle and a nozzle guide. The air swirler structure includes a swirler wall, an inner passage and an air swirler passage. The swirler wall includes a flow guide surface. At least an inner portion of the flow guide surface has a frustoconical geometry. The inner passage extends axially along an axis within the air swirler structure to a swirler outlet. The air swirler passage extends radially into the air swirler structure, longitudinally along the flow guide surface and to the inner passage. The injector nozzle projects axially into the inner passage. The nozzle guide couples the injector nozzle to the air swirler structure. The nozzle guide is axially abutted against the swirler wall.

Abstract: A wall assembly for use in a combustor of a gas turbine engine, the wall assembly including: a support shell; a liner panel; and an annular grommet extending from the liner panel, the annular grommet defining a dilution passage and the annular grommet extends through an opening in the support shell when the support shell and the liner panel are secured to each other, the annular grommet having a top portion that defines a portion of a periphery of the dilution opening; and a backstop extending from the top portion of the annular grommet, the backstop defining another portion of the periphery of the dilution passage and the backstop extending through and above the opening in the support shell when the liner panel is secured to the support shell.

Abstract: An assembly is provided for a gas turbine engine. This assembly includes an air swirler structure, an injector nozzle and a nozzle guide. The air swirler structure includes an inner bore and an air swirler passage. The inner bore extends axially along an axis through the air swirler structure. The air swirler passage extends radially into the air swirler structure to the inner bore. The injector nozzle projects axially into the inner bore. The nozzle guide couples the injector nozzle to the air swirler structure. The nozzle guide includes a guide foot and an air purge passage radially outboard of the guide foot. The guide foot is configured to radially engage the injector nozzle. The air purge passage extends across the nozzle guide and axially to the inner bore.

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 fuel injector assembly for a gas turbine engine includes a swirler and a fuel nozzle. The swirler has an outer wall having a SOW inner wall surface, an inner wall having a SIW inner wall surface and a SIW outer wall surface, an outer passage, and an inner passage. The SIW inner wall surface includes first and second sections. The first section extends between a first airflow inlet and the second section, and the second section extends between the first section and an inner wall distal end. The first section tapers radially inward, and the second section extends parallel the center axis. The outer wall circumscribes the inner wall and extends axially along the center axis to a distal outer wall end, and the distal end wall is axially recessed within the swirler from the distal outer wall end. The fuel nozzle projects into the inner passage.

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.