Patent ID: 7661267
Filing Date: 2010-02-16
Classification: F23M,F23R

Abstract:
1. A system for damping thermo-acoustic instability in a combustor for a gas turbine, the combustor comprising at least one combustion chamber and at least one burner associated with said combustion chamber and mounted in a position corresponding to a front portion set upstream of said combustion chamber; the damping system comprising a plurality of Helmholtz resonators, said plurality of Helmholtz resonators comprising a casing defining a pre-set volume therein and a neck for hydraulic connection between said pre-set volume and said combustion chamber; said neck connected to one side of said combustion chamber distant from said front upstream portion of said combustion chamber provided with said at least one burner, said casing of said plurality of Helmholtz resonators comprises first and second cup-shaped tubular bodies, which are mounted in a telescopic way co-axially on one another, with respective concavities facing one another, by a threaded coupling; and a threaded fixing ring-nut, which is provided outside said combustion chamber on one of said first and second cup-shaped tubular bodies, in a single piece, with said neck and is configured to bear axially upon the other of said first and second cup-shaped tubular bodies.