Fuel injection system for a gas turbine combustor including radial fuel spray arms and V-gutter flameholders

Claim 1

A fuel injection system for a combustion chamber for a gas turbine engine, the combustion chamber having an end wall extending transversely with respect to a central axis of the combustion chamber and defining a combustion zone having a longitudinal axis extending substantially parallel to the central axis, the system comprising: a) a sleeve defining a passageway extending along the longitudinal axis of the combustion chamber, the sleeve having an outer surface and a downstream end extending into the combustion chamber; b) first fuel injection means to inject fuel into the passageway; c) second fuel injection means to inject fuel into the combustion chamber, the second fuel injection means comprising means defining a plurality of fuel injection arms, each having at least one substantially linear array of fuel injection holes, the arms extending radially away from the outer surface of the sleeve so as to be substantially angularly equidistant from each other, and located in a plane extending substantially perpendicular to the longitudinal axis of the combustion zone, the plane located axially between the end wall and the downstream end of the sleeve; and, d) a flameholder apparatus comprising a plurality of flameholder arms, each flameholder arm extending axially from the second fuel injection means to at least the downstream end of the sleeve, the flameholder arms extending radially away from the outer surface of the sleeve and circumferentially located between the angularly spaced apart fuel injection arms, wherein each flameholder arm comprises a generally "V"-shaped cross-sectional configuration with the apex of the "V"-shape facing toward and located adjacent to a plane of the end wall of the combustion chamber.