Abstract: A combustor for a gas turbine engine, including: a heat shield panel attached to a combustor liner, the combustor liner having a plurality of primary apertures extending through the combustor liner and the heat shield panel having a plurality of apertures extending therethrough; an intermediary layer located between the combustor liner and the heat shield panel, the intermediary layer being spaced from the combustor liner and the intermediary layer being spaced from the heat shield panel, the intermediary layer including a plurality of secondary apertures extending through the intermediary layer, the plurality of apertures, the plurality of primary apertures and the plurality of secondary apertures each being in fluid communication with each other; and a plurality of pins extending upwardly and away from a surface of the intermediary layer towards a surface of the combustor liner.

Abstract: An air-debris separator includes a center body, an inner wall, an outer wall, a separation passage, a first outlet passage and a second outlet passage. The center body extends longitudinally along a longitudinal centerline. The inner wall and the outer wall extend longitudinally along and circumferentially about the center body. The separation passage extends longitudinally within the air-debris separator to the first outlet passage and the second outlet passage. The separation passage is radially between the center body and the outer wall. The separation passage includes a convergent section and a radial outer diameter that decreases as the convergent section extends longitudinally towards the first outlet passage and the second outlet passage. The first outlet passage is radially between the center body and the inner wall. The second outlet passage is formed by and radially between the inner wall and the outer wall.

Abstract: An assembly for a combustor for a gas turbine engine, including: a plurality of heat shield panels attached to at least one combustor liner, each one of the plurality of heat shield panels including a panel portion and a first forward rail and a second rearward rail each extending from an outer surface of the panel portion, the panel portion including an inner surface opposite of the outer surface, the panel portion also includes a forward end and a rearward end, the forward end of the panel portion is axially forward of the rearward end of an adjacent heat shield panel of the plurality of heat shield panels such that a gap is defined between the outer surface of the panel portion of one heat shield panel of the plurality of heat shield panels and an inner surface of the panel portion of an adjacent heat shield panel of the plurality of heat shield panels, the panel portion also includes a plurality of apertures extending from the outer surface to the inner surface; and a plurality of cooling pins extending u

Abstract: An assembly for a combustor for a gas turbine engine, including: a plurality of heat shield panels attached to at least one combustor liner, each one of the plurality of heat shield panels including a panel portion and a first forward rail and a second rearward rail each extending from an outer surface of the panel portion, the panel portion including an inner surface opposite of the outer surface, the panel portion also includes a forward end and a rearward end, the forward end of the panel portion is axially forward of the rearward end of an adjacent heat shield panel of the plurality of heat shield panels such that a gap is defined between the outer surface of the panel portion of one heat shield panel of the plurality of heat shield panels and an inner surface of the panel portion of an adjacent heat shield panel of the plurality of heat shield panels, the panel portion also includes a plurality of apertures extending from the outer surface to the inner surface; and a plurality of cooling pins extending u

Abstract: A combustor wall includes a panel, a boss, a wall aperture and multiple cooling apertures. The panel extends axially along and circumferentially about an axial centerline. The panel extends radially between a first panel surface and a second panel surface. The first panel surface forms a peripheral boundary of a combustion chamber. The boss projects out from the second panel surface. The boss extends circumferentially around and forms an outer peripheral boundary of the wall aperture. The wall aperture extends along a wall aperture centerline through the combustor wall to the first panel surface. The cooling apertures are arranged circumferentially about the wall aperture. Each of the cooling apertures extends along a cooling aperture centerline through the panel and/or the boss to the wall aperture. The cooling aperture centerline of a first of the cooling apertures is angularly offset from the wall aperture centerline by a first acute angle.

Abstract: A combustor panel is disclosed herein. The combustor panel includes a top side, a bottom side opposite the top side, a feature coupled to the top side and extending orthogonally away from the top side, the feature defining a first space on the bottom side beneath the feature, a first plurality of cooling holes extending in a first direction from the top side to the bottom side, a second plurality of cooling holes extending in a second direction from the top side to the bottom side, the second direction being rotated about 1° to about 60° counter-clockwise from the first direction, and a third plurality of cooling holes extending in a third direction from the top side to the bottom side, the third direction being about rotated 1° to about 60° clockwise from the first direction.

Abstract: A combustor panel is disclosed herein. The combustor panel includes a top side, a bottom side opposite the top side, a feature coupled to the top side and extending orthogonally away from the top side, the feature defining a first space on the bottom side beneath the feature, a first plurality of cooling holes extending in a first direction from the top side to the bottom side, a second plurality of cooling holes extending in a second direction from the top side to the bottom side, the second direction being rotated about 1° to about 60° counter-clockwise from the first direction, and a third plurality of cooling holes extending in a third direction from the top side to the bottom side, the third direction being about rotated 1° to about 60° clockwise from the first direction.

Abstract: A combustor for a gas turbine engine, including: a heat shield panel attached to a combustor liner, the combustor liner having a plurality of primary apertures extending through the combustor liner and the heat shield panel having a plurality of apertures extending therethrough; an intermediary layer located between the combustor liner and the heat shield panel, the intermediary layer being spaced from the combustor liner and the intermediary layer being spaced from the heat shield panel, the intermediary layer including a plurality of secondary apertures extending through the intermediary layer, the plurality of apertures, the plurality of primary apertures and the plurality of secondary apertures each being in fluid communication with each other; and a plurality of pins extending upwardly and away from a surface of the intermediary layer towards a surface of the combustor liner.

Abstract: A combustor wall includes a panel, a boss, a wall aperture and multiple cooling apertures. The panel extends axially along and circumferentially about an axial centerline. The panel extends radially between a first panel surface and a second panel surface. The first panel surface forms a peripheral boundary of a combustion chamber. The boss projects out from the second panel surface. The boss extends circumferentially around and forms an outer peripheral boundary of the wall aperture. The wall aperture extends along a wall aperture centerline through the combustor wall to the first panel surface. The cooling apertures are arranged circumferentially about the wall aperture. Each of the cooling apertures extends along a cooling aperture centerline through the panel and/or the boss to the wall aperture. The cooling aperture centerline of a first of the cooling apertures is angularly offset from the wall aperture centerline by a first acute angle.