Loading patent…
AssigneeAlstom (Switzerland) Ltd
InventorsEphraim Gutmark, Christian Oliver Paschereit
Estimating the term…
A method and a device are described for the controlled damping of combustion-driven oscillations in a turbomachine with a burner system providing at least one burner, into which is introduced, via at least one burner nozzle arranged centrally in the burner, fuel which is intermixed with combustion inflow air flowing into the burner, to form a fuel/air mixture which is ignited in a combustion chamber following the burner system. The invention is distinguished in that the fuel nozzle is designed in the form of a burner lance, at the lance end of which fuel discharge into the burner takes place, and in that the burner lance projects into the burner in the amount of at least one third of the axial burner length.
A method for the reduction of combustion-driven oscillations in combustion systems, in particular in combustion chambers of turbomachines, equipped with at least one burner, into which at least one combustion air stream is introduced tangentially into a burner interior and, at the same time with the formation of a swirl flow oriented coaxially to the burner axis, is intermixed intensively with an injected gaseous and/or liquid fuel, and this swirl flow induces, at a cross-sectional jump at the burner outlet, a backflow zone which stabilizes the flame front acting there, characterized in that a disturbance body (3) is arranged in the axis of rotation of the swirl flow (6) for the fluidic stabilization of the backflow zone, and an additional fuel discharge into the swirl flow (6) takes place from this central disturbance body (3).
A premixing burner for the reduction of combustion-driven oscillations within a combustion system, in particular a combustion chamber (4) of a turbomachine, essentially comprising a swirl generator consisting of two semimonocoque conically widening part bodies (1a) and (1b) which are arranged axially parallel, and offset to one another, in such a way that they form tangential gaps in two overlap regions located mirror-symmetrically opposite one another, said gaps serving as inlet ducts for the combustion air (7) into the burner interior (2), furthermore comprising at least one central fuel nozzle within the interior (2) enclosed by the part bodies (1a) and (1b), characterized in that the central fuel nozzle is designed in the form of a coaxially oriented burner lance (3) and projects into the burner interior (2) up to at least one third of the axial length of the latter, and the burner lance (3) is equipped, at least in its downstream end region, with means for the discharge of at least one fluid into the burner interior (2).
Dependencies are inferred from the claim text.