A burner for a gas turbine, having a burner lance and/or burner hub, a burner passage which at least partially surrounds the burner lance and/or burner hub, and a fuel supply arrangement having at least one fuel nozzle and at least one fuel channel. The burner allows pollutant emissions to be reduced and offers a high degree of operational safety. The fuel supply arrangement has a fluidic oscillator that has an interaction chamber, the interaction chamber having at least one inlet and, lying opposite, one outlet region that has at least one outlet channel, one end of at least one feedback line terminating into the interaction chamber in the region of the inlet, the other end thereof terminating into the outlet region or into an outlet channel, and each end of the feedback line being sealed off from the interaction chamber by a flexible membrane.

A system for attenuating acoustic energy in machines is provided. The system may include an inner tube disposed about a central axis, an outer tube disposed about the inner tube and the central axis, and a middle tube disposed about the central axis and between the inner tube and the outer tube. The system may also include a first annular ring extending radially from the outer tube and configured to couple the outer tube to the middle tube. The system may further include a second annular ring extending radially from the inner tube and configured to couple the inner tube to the outer tube, such that an acoustic resonator may be formed by the first annular ring, the second annular ring, a portion of the inner tube, a portion of the outer tube, and a portion of the middle tube.

A gas turbine combustor includes: an external cylinder (31); an inner cylinder (32) provided inside the external cylinder (31) to form an air passage (30) between the external cylinder (31) and the inner cylinder (32); a pilot nozzle (35) provided in a center part of the inner cylinder (32) along a direction of a combustor axis (S); a plurality of main nozzles (36) provided on an inner peripheral surface of the inner cylinder (32) along a circumferential direction thereof so as to surround the pilot nozzle (35), the plurality of main nozzles (36) premixing fuel with combustion air introduced to the air passage (30) and ejecting the fuel into the inner cylinder (32); and a top hat nozzle (41) provided inside the air passage (30) across a circumferential direction to mix fuel with the combustion air prior to reaching the plurality of main nozzles (36).

In a damping device according to the present invention, a damping device 63 is mounted on a bypass pipe 61 that supplies an amount of high-pressure air to a combustor transition piece 33. The damping device 63 includes a fluid introducing unit 71 that forms a fluid introduction space B by covering an outer peripheral portion of the bypass pipe 61, a plurality of acoustic boxes 73a and 73b that forms resonance spaces Da and Db with the base portions connected to the fluid introducing unit 71 and the end portions extending along the outer peripheral portion of the bypass pipe 61 in the circumferential direction, and partition plates 74a and 74b that form resonance ducts Ea and Eb of a predetermined length by partitioning the resonance spaces Da and Db.

An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system is disclosed. The acoustic damping resonator system (14) may be formed from one or more resonators (16) formed from a resonator housing (18) positioned within the gas turbine engine combustor (12) at an outer housing (20) forming a combustor basket (22) and extending circumferentially within the combustor (12). In at least one embodiment, the resonator housing (18) may include one or more resonator chambers (18) that provide enhanced cooling with reduced risk of cracking and other damage. The resonator housing (18) may include resonator exhaust orifices (26) that are positioned closer to an area of maximum temperature within the combustor (12), thereby enabling the resonator (16) to reduce the temperature gradient within the combustor (12). The resonator housing (18) may be sized and configured to reduce stress found in conventional systems by increasing distances between resonator exhaust orifices (26) and between resonator inlet impingement orifices (30), among others.

An acoustic damping device is provided that includes a resonating tube defining a resonating cavity with a predetermined characteristic length and a tube end defining a cavity opening, as well as a case configured to reversibly secure the tube end in fluidic communication with a fluid volume enclosed by a liner. The cavity opening is connected with the resonating cavity. The case includes a vented ferrule adpressed over a perforated region of the liner. The vented ferrule defines a ferrule opening that is aligned with the perforated region of the liner and the cavity opening to form the fluidic communication between the fluid volume and the resonating cavity.

A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.

The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

A burner having a pre-mixing passage delimited radially outwardly by a wall, a burner lance and a plurality of fuel injectors arranged in the pre-mixing passage, the injectors extending from the burner lance in the direction of the wall and having fuel nozzles. The fuel supply arrangement has at least one fluidic oscillator that has an interaction chamber, an inlet to the interaction chamber connected to a fuel channel of the fuel supply arrangement, a first outlet channel of the interaction chamber extending at least to a first fuel nozzle and a second outlet channel extending at least to a second fuel nozzle, the fluidic oscillator has one feedback line for each outlet channel, one end of the feedback line terminating into the respective outlet channel downstream of the at least one fuel nozzle, and the other end thereof terminating into an inlet region of the interaction chamber.

A tail pipe (50) comprises: a pipe (51); an acoustic attenuator (61) that forms an acoustic space (Ss) on the outer peripheral side of the pipe (51); and a cooling air jacket (65) that forms a cooling air space (Sa) isolated from the outer space (So), which is the space on the outer peripheral side of the pipe (51). The pipe (51) has: a first air flow path (56) that is formed between the outer peripheral surface (55o) and the inner peripheral surface (55i); and an acoustic hole (59) that penetrates from the acoustic space (Ss) to a combustion space (Sc), which is a space on the inner peripheral side of the pipe (51c). The first air flow path (56) has: an inlet (56i) that faces into the cooling air space (Sa) and guides the air in the cooling air space (Sa) into the first air flow path (56); and an outlet (56o) that faces into the acoustic space (Ss) and guides the air passing through the first air flow path (56) into the acoustic space (Ss).