Acoustic resonator located at flow sleeve of gas turbine combustor

摘要

A system includes a compressor that compresses (12) incoming airflow, and a combustor assembly (14) mixing the compressed incoming airflow with fuel (66) and combusting the air and fuel mixture in a combustion zone (68). The combustor assembly (14) includes a hot side downstream of the combustion zone (68) and a cold side upstream of the combustion zone (68). The system also includes a turbine (16) receiving products of combustion from the combustor assembly (14). The combustor assembly (14) includes a resonator (40) positioned in the cold side of the combustor assembly (14) in an annular passage (56) between a flow sleeve (60) and a casing (59) of the combustor assembly (14).