A noise attenuation panel for a structure within a propulsion system includes a first plurality of unit cells; and a second plurality of unit cells, the second plurality of unit cells merged within the first plurality of unit cells, the first plurality of unit cells including a first periodic structure having a first unit cell, a second unit cell, a third unit cell and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells.

A combustor for a gas turbine includes a dome, and a deflector connected to the dome to define a baffle cavity therebetween, the deflector having a deflector cold side adjacent to the baffle cavity and a deflector hot side adjacent to a combustion chamber. At least one dome-deflector connecting member connects the dome and the deflector to each other. The dome-deflector connecting member forms a flexible joint between the dome and the deflector.

A liner assembly for a combustor. The liner assembly includes a liner defining a combustion chamber of the combustor. The liner includes a looped section at a forward end of the liner. The looped section includes one or more bends such that the looped section forms a compliant joint and vibrations are dampened through the liner downstream of the looped section.

A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and a fence disposed between the forward and aft liner segments, wherein the fence extends in the circumferential direction, and wherein the fence extends into the combustion chamber along the radial direction.

A hollow plank of a combustor liner defining a combustion chamber including an inner wall having a plurality of inner openings and one or more inner holes, an outer wall having one or more outer openings and a plurality of outer holes, a plurality of lateral walls coupled to the inner wall and the outer wall to define a cavity, and a partition wall connected to the plurality of lateral walls and dividing the cavity into a first sub-cavity and a second sub-cavity. The one or more outer openings communicate with the first sub-cavity and communicate through a plurality of tubes with the second sub-cavity. The plurality of inner openings communicate with the second sub-cavity and communicate with the first sub-cavity through one or more bypass tubes. The first sub-cavity or the second sub-cavity, or both, are frequency tuned to reduce combustion dynamic frequencies.

A gas turbine combustor includes a vane, a plurality of supports, and a pressure dynamics damping hole. The vane is disposed at the outer circumferential side of the combustion liner. The plurality of supports are disposed at an inner side of the combustion casing for fixing the vane. The pressure dynamics damping hole is formed in the combustion liner at a position corresponding to the vane for communication with the combustion chamber.

A dual mode ramjet or scramjet engine used in the propulsion of an aircraft includes an inlet configured to receive and compress air, a combustion chamber connected to the inlet and configured to mix the compressed air with fuel to pressurize the dual mode ramjet or scramjet engine, and an acoustic attenuator having one or more resonator cavities integrated into the combustion chamber.

A fuel nozzle, a fuel nozzle module having the same, and a combustor are provided. The fuel nozzle includes a nozzle cylinder having a space through which fuel flows and a plurality of fuel holes through which the fuel flows in a surface, a shroud spaced apart from the nozzle cylinder and formed to surround the nozzle cylinder in a longitudinal direction of the nozzle cylinder, and a mixing flow path formed between the nozzle cylinder and the shroud to mix the fuel supplied through the plurality of fuel holes and compressed air supplied from a compressor.

A swirler with integrated damper may include a primary swirler vane having a primary air passage, a secondary swirler vane having a secondary air passage, and a damper within the primary swirler vane, the secondary swirler vane, or both the primary swirler vane and the secondary swirler vane. The damper may include a series of cavities. The damper is configured to absorb one or more frequencies present in an air flow through the primary air passage, the secondary air passage, or both the primary air passage and the secondary air passage.

A fuel nozzle, a fuel nozzle module having the same, and a combustor having the same, which can solve a problem of combustion instability due to a high-frequency resonance generated by fuel containing hydrogen are provided. The fuel nozzle includes a fuel flow path through which a fuel flows, and a plurality of fuel plenums including a plurality of micro-mixers including a mixing flow path through which a fluid in which the fuel and compressed air are mixed flows and a fuel supply hole for supplying the fuel to the mixing flow path, wherein the plurality of fuel plenums are formed in the fuel flow path to be spaced apart from each other.