Abstract: A combustor liner, a combustor, and a gas turbine engine are provided. The combustor liner includes a liner portion having a plurality of dilution holes extending through the liner portion. Each dilution hole includes a downstream edge in a direction of a flow of a first fluid through the combustion liner. The downstream edge includes a film cooling starter device. The film cooling starter device includes a plurality of cooling holes extending through the liner portion and spaced apart from the downstream edge in a downstream direction. The film cooling starter device also includes a support flange extending from the downstream edge into the combustion zone, and a lip extending away from the support flange in the downstream direction and spaced a predetermined distance from a surface of the liner portion.

Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

Abstract: An apparatus for dampening acoustic pressure oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor. The apparatus includes at least one resonating tube with a closed end, an open end, and a cavity therebetween. The cavity is in fluid communication with an interior of the combustor such that the gas flow may flow into and out of the cavity. The apparatus further includes a perforated plate positioned at the open end and including a plurality of apertures. The gas flow flowing into and out of the cavity travels through the apertures.

Abstract: A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

Abstract: An acoustic dampener comprises a first wall, orifice plate, and second wall. The first wall separates a first fluid source from a second fluid source. The first wall has a hole for allowing fluid communication between the first fluid source and a first cavity of the acoustic dampener. The office plate separates the first cavity of the acoustic dampener from a second cavity of the acoustic dampener. The second wall has a hole for allowing fluid communication between the first cavity of the acoustic dampener in the second cavity of the acoustic dampener. The second wall separates the second cavity of the acoustic dampener from the second fluid source. The second wall has a hole for allowing fluid communication between the second cavity of the acoustic dampener and the second fluid source. In one embodiment, the acoustic dampener is formed in a combustion chamber liner of a gas turbine engine.

Abstract: An acoustic dampener comprises a first wall, orifice plate, and second wall. The first wall separates a first fluid source from a second fluid source. The first wall has a hole for allowing fluid communication between the first fluid source and a first cavity of the acoustic dampener. The office plate separates the first cavity of the acoustic dampener from a second cavity of the acoustic dampener. The second wall has a hole for allowing fluid communication between the first cavity of the acoustic dampener in the second cavity of the acoustic dampener. The second wall separates the second cavity of the acoustic dampener from the second fluid source. The second wall has a hole for allowing fluid communication between the second cavity of the acoustic dampener and the second fluid source. In one embodiment, the acoustic dampener is formed in a combustion chamber liner of a gas turbine engine.