Patent ID: 8938968
Filing Date: 2015-01-27
Classification: F23C,F23D,F23R

Abstract:
1. Burner of a gas turbine, comprising: a tubular body with an inlet for entrance of a gas flow; at least one side vortex generator located downstream of the inlet; a lance projecting into the tubular body and having a terminal portion extending parallel to a longitudinal axis of the burner which is provided with at least one nozzle group for injecting fuel into the tubular body, the at least one nozzle group laying in an injection plane perpendicular to an axis of a terminal portion of the lance downstream of the lance; an outlet downstream of said lance configured to supply a mixture of gas and fuel formed in the tubular body to a combustion chamber, wherein a ratio x/L between an axial distance x between a trailing edge of the at least one side vortex generator and the injection plane, and a length L of the tubular body is less than approximately 0.1052; and wherein a trailing edge of an intermediate portion of the lance, which is inside the tubular body and extends perpendicularly to the longitudinal axis of the burner, is downstream of tips of all the at least one side vortex generators, wherein each of the tips is a downstream edge of a corresponding side vortex generator of the at least one side vortex generators.