Patent ID: 6513329
Filing Date: 2003-02-04
Classification: F23C,F23D,F23R

Abstract:
A fuel injector for a gas turbine engine combustor, comprising:a forward endplate and an aft endplate longitudinally spaced from the forward end plate, the aft endplate having a fuel injector discharge port extending therethrough, the discharge port having an aft extremity that defines a fuel injector discharge plane; at least two cylindrical-arc scrolls extending longitudinally between the forward endplate and the aft endplate and cooperating with the endplates to bound a mixing chamber, each scroll defining a surface of partial revolution about a respective scroll centerline, the scroll centerlines being parallel to and equidistantly offset from a longitudinally extending fuel injector axis so that each adjacent pair of scrolls defines an entry slot parallel to the axis for admitting a stream of primary combustion air into the mixing chamber, at least one of the scrolls including a longitudinally distributed array of fuel injection passages for injecting a primary fuel into the primary combustion air stream; and a centerbody having a longitudinally extending centerbody axis, a base, a bluff tip and a shell having a radially outer surface that extends longitudinally from the base to the tip, the centerbody being coaxial with the fuel injector axis and defining a radially inner boundary of the mixing chamber, the tip being substantially longitudinally aligned with the discharge plane, the centerbody having a fuel conduit extending therethrough and in communication with at least one fuel discharge opening in the tip for injecting a combustible fluid into the combustor.