A panel for use with a shell as a combustor liner in a combustor section of a gas turbine engine includes a panel body having an outer surface defining a plurality of effusion holes for receiving the compressed gas to also be received in the combustion chamber of the combustor section. The panel further includes a flow guide extending from the outer surface of the panel body and configured to receive the compressed gas from an impingement hole of the shell and to direct the compressed gas over the outer surface of the panel body towards the plurality of effusion holes.

A gas turbine engine component includes a first surface and a second surface. The component further includes a dilution hole defined by the first surface and the second surface. The component further includes a first effusion hole and a second effusion hole each having an inlet defined by the second surface and an outlet defined by the first surface such that the outlet of the first effusion hole is located nearer to the dilution hole than the outlet of the second effusion hole.

A combustor for a gas turbine engine includes a combustion chamber defined between an inner shell and an outer shell. The combustor further includes a bulkhead extending between the inner shell and the outer shell. The bulkhead includes a plurality of impingement cooling rings. Each impingement cooling ring of the plurality of impingement cooling rings includes a plurality of impingement cooling holes extending through the bulkhead. The combustor further includes a heat shield panel mounted to the bulkhead so as to define an impingement cooling chamber between the bulkhead and the heat shield panel. The heat shield panel further includes a radial portion between a perimeter and an opening, with respect to an opening center axis, which is free of penetrations. The plurality of impingement cooling holes of each of the plurality of impingement cooling rings are directed toward the radial portion of the heat shield panel.

An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.

A trapped vortex combustor for use in a gas turbine engine includes an outer vortex chamber wall and a dome attached to, or formed integrally with, the outer vortex chamber wall. The dome, the outer vortex chamber wall, or both define at least in part an outer trapped vortex chamber and a channel. The channel extends along the circumferential direction at a forward end of the outer vortex chamber wall, the channel configured to receive an airflow through or around the outer vortex chamber wall, the dome, or both and provide such airflow as a continuous annular airflow to the inner surface of the outer vortex chamber wall. The dome further defines a fuel nozzle opening, with all openings in the dome outward of the fuel nozzle opening along the radial direction, excepting any effusion cooling holes having a diameter less than about 0.035 inches, being in airflow communication with the channel.

A cooling hole arrangement for a combustor panel including a first group of cooling holes, each of the first cooling holes extending from a first inlet to a first outlet. Also included is a second group of cooling holes, each of the second cooling holes extending from a second inlet to a second outlet, each of the first cooling holes and the second cooling holes spaced from an edge of the combustor panel in an axial direction to be arranged substantially parallel to the edge of the combustor panel. At least a portion of the first inlet of each first cooling holes is axially overlapped with a portion of the second inlet of the second cooling holes. The first outlet of each of the first cooling holes is closer to the edge of the combustor panel than the second outlet of the second cooling holes is to the edge.

An effusion cooling hole for a component associated with a gas turbine engine extends along a longitudinal axis. The effusion cooling hole includes an inlet section spaced apart from a first surface of the component. The inlet section includes a face orientated transverse to the first surface and defines an inlet through the face that has a first diameter. The effusion cooling hole includes an outlet at a second surface of the component and downstream from the inlet section. The effusion cooling hole includes a diverging section downstream from the inlet section and upstream from the outlet. The diverging section is defined substantially external to a thickness of the component, and the effusion cooling hole transitions from the first diameter to a second diameter at the diverging section. The effusion cooling hole includes an intermediate section that fluidly connects the diverging section to the outlet.

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.

A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel.

A combustor for a gas turbine engine includes a liner having a first surface, a second surface opposite the first surface, and defining a plurality of effusion cooling holes. At least one of the effusion cooling holes includes an inlet section and a converging section downstream of the inlet section. The at least one of the effusion cooling holes includes a metering section downstream of the converging section. The at least one of the effusion cooling holes includes an outlet section downstream of the metering section. The outlet section is proximate to the second surface. The inlet section, the converging section, the metering section and the outlet section extend along a longitudinal axis, with the inlet section asymmetrical relative to the longitudinal axis and the metering section symmetrical relative to the longitudinal axis.