Patent ID: 8516819

Claim:
A gas turbine combustor Helmholtz resonator comprising: a cavity at least partly between a combustor base plate transverse wall and a transverse wall of a top plate structure, wherein the top plate structure additionally comprises an outer shell wall adapted to contact a liner of the combustor, wherein the outer shell wall is oriented transverse to the top plate transverse wall and wherein the outer shell wall extends to the base plate transverse wall to enclose the cavity; a plurality of base plate transverse wall openings through the base plate transverse wall and into the cavity; at least two top plate transverse wall apertures through the top plate transverse wall and defining a resonator throat, having a length, and communicating with a combustion zone downstream of the top plate structure transverse wall; and a flow-directing structure between a main swirler assembly and the top plate structure transverse wall that separates a flow path from the cavity, wherein the top plate structure additionally comprises an inward conical member adapted to conform to a pilot cone of the combustor, and wherein the cavity is also partly between the inward conical member and the base plate transverse wall.