Patent ID: 9557062
Date: 2017-01-31
CPC Classifications: F05D,F23M,F23R

Claim:
1. A damping device for a gas turbine combustor, comprising: a first inner wall on a side with a hot gas flow and arranged to be subjected to high temperatures; a second outer wall, arranged at a distance from the first inner wall; a plurality of cooling channels extending parallel between the first inner wall and the second outer wall; at least one damping volume between the inner wall and the outer wall; a first passage for supplying a cooling medium from a cooling channel of the plurality of cooling channels into the damping volume; a neck passage configured to connect the at least one damping volume to a combustion chamber; and an end plate fixed to the first inner wall, separating the damping volume from the combustion chamber, wherein said end plate is provided with the neck passage and includes at least one feed plenum for the cooling medium, at least one exit plenum for the cooling medium and cooling passages enabling a flow of cooling medium from the at least one feed plenum to a second plenum and to the at least one exit plenum in a cooling medium flow path direction, wherein the feed plenum, exit plenum, second plenum, and the cooling passages are formed within the end plate and are in serial flow communication to circulate cooling medium through the end plate, and the exit plenum exhaust cooling medium to the damping volume or combustion chamber.