| 摘要 |
The invention relates to a damping device for a gas turbine combustor with a near wall cooling system. It is an object of this invention to provide such a damping device for a combustion liner segment with significantly reduced cooling air mass flow requirements, which eliminates the drawbacks of expensive casting techniques. The damping device for a gas turbine combustor (1) according to the invention comprises a wall (4) with a first inner wall (5), particularly a combustor liner, and a second outer wall (6), arranged in a distance to each other, wherein said inner wall (5) is subjected to high temperatures on a side with a hot gas flow, a plurality of cooling channels (7) extending essentially parallel between the first inner wall (5) and the second outer wall (6), and at least one damping volume (9) bordered by cooling channels (7), furthermore comprising a first passage (11) for supplying a cooling medium from a cooling channel (7) into the damping volume (9) and a second passage (13) for connecting the damping volume (9) to the combustion chamber (3), characterized in that an end plate (10), fixed to the inner wall (5), separates the damping volume (9) from the combustion chamber (3), said end plate (10) is provided with the neck passage (13), and is additionally provided with at least one feed plenum (12, 15) for a cooling medium, at least one exit plenum (16) for a cooling medium and at least one cooling passage (14) enabling a flow of cooling medium from the at least one feed plenum (12) to another feed plenum (15) or to the at least one exit plenum (16). |
