Patent ID: 7424804
Filing Date: 2008-09-16
Classification: F23M,F23R

Abstract:
1. A premix burner for a gas turbine installation, comprising: a swirl generator for a combustion airstream flowing to the burner, and first and second perforated through-flow elements; wherein the swirl generator is arranged within the first perforated through-flow element; wherein the first perforated through-flow element is arranged in an inflow region for the combustion airstream, and the second perforated through-flow element is arranged at a defined distance upstream of the first perforated through-flow element so that the combustion airstream flows in series through the second and the first perforated through-flow elements; wherein distance between the first perforated through-flow element and the second perforated through-flow element, a degree of perforation of the first through-flow element, and an extent of the first through-flow element in a direction of through-flow are adapted to one another in such a manner that a complex acoustic impedance Z for characteristic pulsation frequencies of the burner at least approximately corresponds to a product of density of the combustion airstream and acoustic velocity in the combustion airstream.