Patent ID: 6530223
Filing Date: 2003-03-11
Classification: F23R

Abstract:
A combustor for a gas turbine engine having a longitudinal axis therethrough, comprising:(a) an outer liner having a forward end and an aft end; (b) an inner liner having a forward end and an aft end; (c) a pilot dome formed upstream of said outer liner forward end so as to define a first combustion zone radially oriented to said longitudinal axis; (d) a dome plate having an outer portion connected to an upstream end of said pilot dome and an inner portion connected to said inner liner forward end, wherein a main combustion zone is defined by said dome plate, said outer liner, and said inner liner substantially perpendicular to said first combustion zone; (e) a plurality of circumferentially spaced fuel air mixers positioned with respect to a corresponding segment of said pilot dome so as to provide a fuel air mixture into said first combustion zone; wherein said fuel air mixture through said pilot dome is provided continuously into said first combustion zone during operation of said combustor.