Abstract: A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

Abstract: A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

Abstract: A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (12), and a plurality of mains (16) disposed in the carrier. Some of the mains (labeled with the letter X) include a body having a different structural feature relative to the respective bodies of the remaining mains. The mains with the different structural feature may be selectively grouped in the carrier to form at least one set of such mains effective to damp predefined vibrational modes in the combustor.

Abstract: Apparatus and method for a combustion turbine engine are provided. A pre-mixing passage (24) has an upstream inlet arranged to receive a flow of air to be mixed with fuel. A fuel-injecting lance (12) is disposed in the pre-mixing passage. At least a first fuel ejection orifice (40) is disposed at a first axial location of the fuel-injecting lance. At least a second ejection orifice (42) is disposed at a second axial location of the fuel-injecting lance. A spacing between the first and second axial locations is arranged to effect oscillatory interference patterns in pockets comprising mixtures of air and fuel that flow towards a downstream outlet of the pre-mixing passage. The oscillatory interference patterns may be effective to promote homogeneity in the mixtures of air and fuel and dampen thermoacoustic oscillations in a flame (46) formed upon ignition of the mixtures of air and fuel.

Abstract: An acoustically dampened gas turbine engine (10) having a gas turbine engine combustor (12) with an acoustic damping resonator system (10) is disclosed. The acoustic damping resonator system (10) 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 (24) 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).

Abstract: A combustor and a method involving burner mains structurally configured to damp vibrational modes that can develop under high-frequency combustion dynamics are provided. The combustor may include a carrier (12), and a plurality of mains (16) disposed in the carrier. Some of the mains (labeled with the letter X) include a body having a different structural feature relative to the respective bodies of the remaining mains. The mains with the different structural feature may be selectively grouped in the carrier to form at least one set of such mains effective to damp predefined vibrational modes in the combustor.

Abstract: 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).

Abstract: An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.

Abstract: A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.

Abstract: An acoustically dampened gas turbine engine having a gas turbine engine combustor with an acoustic damping resonator system is disclosed. The acoustic damping resonator system may be formed from one or more resonators positioned within the gas turbine engine combustor at an outer housing forming a combustor basket and extending circumferentially within the combustor. The resonator may be positioned in a head region of the combustor basket. In one embodiment, the resonator may be positioned in close proximity to an intersection between the outer housing and an upstream wall defining at least a portion of the combustor. The acoustic damping resonator system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.

Abstract: A combustor assembly in a gas turbine engine includes a liner defining a combustion zone, at least one fuel injector for providing fuel, and a flow sleeve. An inner surface of the flow sleeve defines an outer boundary for an air flow passageway. Upon the air reaching a head end of the combustor assembly at an end of the air flow passageway the air turns 180 degrees to flow into the combustion zone where it is burned with the fuel. The combustor assembly further includes an inlet assembly positioned radially between the liner and the flow sleeve. The inlet assembly defines an inlet to the air flow passageway and includes a plurality of overlapping conduits that are arranged such that the air entering the air flow passageway passes through radial spaces between adjacent conduits.

Abstract: An acoustically dampened gas turbine engine having a combustor with an acoustic damping system is disclosed. The acoustic damping system may be formed from an acoustic damping body having at least one orifice configured to receive a combustor nozzle assembly. The acoustic damping body may be positioned in a head region of a combustor basket and may include one or more orifices in the acoustic damping body. The acoustic damping system may mitigate longitudinal mode dynamics thereby increasing an engine operating envelope and decreasing emissions.

Abstract: A can-annular gas turbine engine including a casing defining an annulus for receiving air flow from a compressor. A combustor basket is supported within the casing, and a swirler assembly is located within the basket and includes an air inlet and an outlet located in a combustion chamber. The swirler assembly is configured to discharge a fuel/air mixture from the outlet downstream into the combustion chamber. An acoustic filter is provided comprising a Herschel-Quincke tube having a first open end at the annulus and a second open end adjacent to the swirler assembly within the combustion chamber. Components of acoustic pressure oscillations travel along two paths of different lengths from one end of the Herschel-Quincke tube to the opposite end of the tube where out of phase components of the pressure oscillations interact to attenuate the pressure oscillations.

Abstract: A can-annular gas turbine engine including a casing defining an annulus for receiving air flow from a compressor. A combustor basket is supported within the casing, and a swirler assembly is located within the basket and includes an air inlet and an outlet located in a combustion chamber. The swirler assembly is configured to discharge a fuel/air mixture from the outlet downstream into the combustion chamber. An acoustic filter is provided comprising a Herschel-Quincke tube having a first open end at the annulus and a second open end adjacent to the swirler assembly within the combustion chamber. Components of acoustic pressure oscillations travel along two paths of different lengths from one end of the Herschel-Quincke tube to the opposite end of the tube where out of phase components of the pressure oscillations interact to attenuate the pressure oscillations.