A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a combustion chamber, a compressed air passage fluidly coupled to the combustion chamber, and a swirler. At least one acoustic resonator can be provided in the combustor.

A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.

A combustor for a gas turbine is described. The combustor comprises a combustor liner, a metering plate attached to an end of the combustor liner and a combustor casing at least partially surrounding the combustor liner. An end cover is further connected to the combustor casing. The combustor liner is connected to the combustor casing by means of a retainer arranged between the metering plate and the end cover, and attached to the metering plate and to the end cover.

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 fuel nozzle assembly includes a fuel plenum body including a forward plate, an aft plate, an outer band extending between the forward plate and the aft plate and a fuel plenum defined within the fuel plenum body. A plurality of tubes extends through the forward wall, the fuel plenum and the aft wall and each tube defines a premix flow passage through and downstream from the fuel plenum body. Each tube is rigidly connected to the aft plate. A damping plate is disposed downstream from the aft plate. At least one tube of the plurality of tubes extends through a corresponding tube opening defined by the damping plate. The damping plate includes a plurality of spring members fixedly connected to the damping plate. At least one spring member of the plurality of spring members is engaged with an outer wall of the at least one tube.

[Problems to be Solved] An exhaust duct (4) for assembly into a combustion apparatus has: a burner (1) to eject air-fuel mixture downward; and a combustion box (3) disposed on a lower side of the burner (1). The exhaust duct includes: a riser duct section (42) elongated in a vertical direction and having, at a lower portion thereof, an inlet port (41) connected to an exhaust port (35) for combustion gas which is opened in a lower portion of the combustion box (3); and a flat horizontal duct section (43) bent at an upper end of the riser duct section (42) so as to be elongated forward. By restraining the resonance of an upper wall part (431) and a lower wall part (432) of the horizontal duct section (43), noises due to resonance sounds are reduced.

[Solving Means] The natural frequencies in an upper wall part (431) and the lower wall part (432) of the horizontal duct section (43) are varied from each other. For example, the lower wall part (432) is fixed to a burner body (11) in order to vary the natural frequencies of the upper wall part (431) and of the lower wall part (432) from each other.

The invention relates to a burner arrangement for using in a single combustion chamber or in a can-combustor comprising a center body burner located upstream of a combustion zone, an annular duct with a cross section area, intermediate lobes which are arranged in circumferential direction and in longitudinal direction of the center body. The lobes being actively connected to the cross section area of the annular duct, wherein a cooling air is guided through a number of pipes within the lobes to the center body and cools beforehand at least the front section of the center body based on impingement cooling. Subsequently, the impingement cooling air cools the middle and back face of the center body based on convective and/or effusion cooling. At least the back face of the center body includes on the inside at least one damper.

This transition piece comprises a pair of side plates which face each other across an axis, a plate inside the curve which, with reference to the axis, is arranged inside the curve where the downstream portion curves relative to the upstream portion on the axis, and a plate outside the curve which, with reference to the axis, is arranged outside the curve on the side opposite of the aforementioned inside the curve. The plate inside the curve, the plate outside the curve and the pair of side plates each has multiple passage groups which are configured from multiple cooling passages that allow flow of a cooling medium and that extend in the axis direction and are arranged side-by-side in the circumferential direction, and one or more headers which allow flow of the cooling medium and which extend in the circumferential direction. The number of the one or more headers of the plate inside the curve is less than the number of the one or more headers in the plate outside the curve and the pair of side plats.

A combustor includes an annular dome and a plurality of dampers integral with the annular dome. Each of the plurality of dampers includes an adjustable damper cover and a damper portion defining a cavity having a volume. The damper cover is mounted to the damper portion integrated with the annular dome and is movable to adjust the volume of the cavity to adjust a frequency of each of the plurality of dampers to reduce an acoustic amplitude of the combustor.

An engine assembly includes a combustor wall with a first skin, a second skin, a core and a sound attenuation passage. The first skin forms a peripheral boundary of a combustion volume on a first side of the combustor wall. The second skin forms a peripheral boundary of a plenum on a second side of the combustor wall. The core includes a plurality of resonator elements between the first skin and the second skin. A first resonator element includes a first base and a plurality of first protrusions projecting out from the first base. Each first protrusion includes a first bore fluidly coupled with a first cavity within the first base. The sound attenuation passage extends within the core and is fluidly coupled with the combustion volume through an attenuation passage aperture in the first skin. The sound attenuation passage is fluidly decoupled from the plenum by the second skin.