Patent ID: 6101814
Filing Date: 2000-08-15
Classification: F23D,F23R,Y02T

Abstract:
A combustor can for a turbine engine, comprising:a liner comprising a set of eleven axially adjacent louvers, the liner having a centerline, a forward end with a fuel injector port extending therethrough and an aft end terminating at a trailing edge, the liner circumscribing a combustion zone and having an effective axial length;a first array of dilution holes penetrating the liner about midway along the effective axial length of the liner and penetrating through the sixth of the eleven louvers;a second array of dilution holes penetrating the liner a predetermined distance aft of the first array and penetrating through the seventh of the eleven louvers, each hole of the second hole array being substantially circumferentially aligned with a hole of the first hole array; anda third array of dilution holes penetrating the liner aft of the second array and a predefined distance aft of the first array and penetrating through the tenth of the eleven louvers, the holes of the third array being nonequiangularly circumferentially distributed and irregularly sized.