Norster

Eric Norster, Newark GB

Patent application number	Description	Published
20100126174	GAS TURBINE COMBUSTION CHAMBER - A combustion chamber including: a flame tube having, in the direction of flow, a mixing zone for mixing a fuel with air to form a fuel-air mixture, as well as a primary combustion zone and a post-primary combustion zone, at least one opening being provided in the area of the mixing zone and in the area of the post-primary combustion zone in order to conduct compressed air into the flame tube, wherein supplied compressed air is used to cool the flame tube and, via the openings in the area of the mixing zone and in the area of the post-primary combustion zone, passes partly into the mixing zone and into the post-primary combustion zone.	05-27-2010

Patent application number	Description	Published
20110167832	Method for operating a premix burner, and a premix burner for carving out the method - A method for operating a premix burner for gaseous fuels having a multi-stage pilot gas system whose diffusion fuel is injected into a flame chamber of the premix burner as at least two partial streams with different orientations, and a premix burner for carrying out the method.	07-14-2011

Patent application number	Description	Published
20090120094	Impingement cooled can combustor - A can combustor includes a generally cylindrical housing having an interior, an axis, and a closed axial end. The closed axial end includes means for introducing fuel to the housing interior. A generally cylindrical combustor liner is disposed coaxially within the housing and configured to define with the housing respective radially outer passages for combustion air and for dilution air, and also respective radially inner volumes for a combustion zone and a dilution zone. The combustion zone is disposed axially adjacent the closed housing end, and the dilution zone is disposed axially distant the closed housing end. The can combustor also includes an impingement cooling sleeve coaxially disposed between the housing and the combustor liner and extending axially from the closed housing end for a substantial length of the combustion zone. The sleeve has a plurality of apertures sized and distributed to direct combustion air against the radially outer surface of the portion of the combustor liner defining the combustion zone, for impingement cooling. Essentially all of the combustion air flows through the impingement cooling apertures prior to admission to the combustion zone. A small portion of the impingement cooling air may be used for film cooling of the liner proximate the closed housing end.	05-14-2009