Patent ID: 8978382
Filing Date: 2015-03-17
Classification: F23M,F23R

Abstract:
1. A combustion device for a gas turbine comprising: an interior portion; an inner wall having a plurality of first passages; an outer wall having a plurality of second passages configured to cool the inner wall, each of the plurality of second passages having an outlet opening into one of a plurality of third passages; and an intermediate layer disposed between the inner wall and the outer wall and defining a plurality of chambers, each chamber forming a Helmholtz damper and being connected to the interior portion by at least one of the plurality of first passages and being connected to at least one of the plurality of second passages by at least one of the plurality of third passages, wherein said second passages have a portion for cooling the inner wall which is closer to the interior portion of the combustion device than the plurality of chambers, and wherein a first flow path between at least one of the chambers and the interior portion via at least one of the plurality of first passages is separated from a second flow path between the outer wall and the at least one chamber via one of the plurality of second passages.