초록 ▼

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 c

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.

대표청구항 ▼

1. A turbine engine with an acoustic clamping resonator system, comprising: a gas turbine engine combustor positioned downstream from a compressor and formed from at least one outer housing defining a combustor basket and at least one upstream wall that is attached to the at least one outer housing,

1. A turbine engine with an acoustic clamping resonator system, comprising: a gas turbine engine combustor positioned downstream from a compressor and formed from at least one outer housing defining a combustor basket and at least one upstream wall that is attached to the at least one outer housing, wherein at least one fuel nozzle of a fuel nozzle assembly extends into the combustor;at least one resonator positioned within the gas turbine engine combustor at the at least one outer housing and extending circumferentially within the combustor;wherein the at least one resonator is positioned radially outward from at least one outer wall of the fuel nozzle assembly;wherein the at least one resonator contacts the at least one upstream wall;wherein the at least one resonator is curved about an axis that is positioned orthogonal to the longitudinal axis of the gas turbine engine combustor forming a curved surface such that the curved surface faces radially inward toward the longitudinal axis;a resonator neck extending between the at least one resonator and the gas turbine engine combustor, wherein the resonator neck is arranged as a support member to coupe the resonator and an intersection of the at least one upstream wall and the outer housing defining the combustor basket; andwherein the resonator neck is a hollow member and forms a hole on the curved surface of the resonator. 2. The turbine engine with an acoustic damping resonator system of claim 1, wherein the at least one resonator is attached to the at least one outer housing of the combustor basket and to the at least one upstream wall. 3. The turbine engine with an acoustic damping resonator system of claim 1, wherein the at least one resonator is positioned at the at least one upstream wall and extends circumferentially within the combustor. 4. The turbine engine with an acoustic damping resonator system of claim 1, wherein the at least one resonator contacts the at least one upstream wall and the at least one outer housing defining the combustor basket. 5. The turbine engine with an acoustic damping resonator system of claim 1, wherein the at least one resonator is positioned at an intersection of the at least one upstream wall and an outer housing defining the combustor basket. 6. A turbine engine with an acoustic damping resonator system, comprising: a gas turbine engine combustor positioned downstream from a compressor and formed from at least one outer housing defining a combustor basket and at least one upstream wall that is attached to the at least one outer housing, wherein at least one fuel nozzle of a fuel nozzle assembly extends into the combustor;at least one resonator positioned within the gas turbine engine combustor at the at least one outer housing and extending circumferentially within the combustor; wherein the at least one resonator is positioned radially outward from at least one outer wall of the fuel nozzle assembly,wherein the at least one resonator contacts the at least one outer housing and the at least one upstream wall, and the at least one resonator is curved about an axis that is positioned orthogonal to the longitudinal axis of the gas turbine engine combustor forming a curved surface such that the curved surface faces radial inward toward the longitudinal axis;a resonator neck extending between the at least one resonator and the gas turbine engine combustor, wherein the resonator neck is arranged as a support member to couple the resonator and an intersection of the at least one upstream wall and the outer housing defining the combustor basket; andwherein the resonator neck is a hollow member and forms a hole on the curved surface of the resonator. 7. The turbine engine with an acoustic damping resonator system of claim 6, wherein the at least one resonator is positioned at the at least one upstream wall and extends circumferentially within the combustor. 8. The turbine engine with an acoustic damping resonator system of claim 6, wherein the at least one resonator is positioned at an intersection of the at least one upstream wall and the at least one outer housing defining the combustor basket, and wherein the at least one resonator is attached to the at least one outer housing and to the at least one upstream wall.