Combustor for a gas turbine

摘要

The present invention provides a combustor (12) for a gas turbine (10). The combustor (12) comprises an annular passage (25) defined by a combustor liner (20) and an outer shell (22). The annular passage (25) forms a first portion of a flow-path (26) for air, to provide cooling of said combustor liner (20). The annular passage (25) is upstream of a burner (36) and in serial flow communication with said burner (36). The proposed combustor (12) further includes a perforated structure (32) connecting the combustor liner (20) and the outer shell (22). The structure (32) is perforated with a multiplicity of openings (33) adapted to provide an outlet of air from said annular passage (25) to said burner (36) with a predetermined pressure drop.