BURNER FOR A GAS TURBINE

摘要

Burner (1) for a gas turbine, comprising a pilot combustor (5), a supply module providing pilot fuel (20) and pilot air (21) into a pilot combustion room (23) enclosed by a pilot burner housing (22) comprising a tapered exit throat (24). Said burner (1) comprises an equalizer (6), with a plurality of holes through which a main flow of air (7) enters a cavity (8), a fuel injector (9) downstream the equalizer (6), wherein a burner axis (3) is defined by the center of the pilot combustion zone (23) and the center of the main combustion zone (14), a swirler (13) downstream the injector (9). To reduce space requirement the equalizer (6) is built in such a manner that the main air (7) flow enters the cavity (8) in a radial direction with regard to the burner axis (3), wherein a channel leads from the equalizer (6) to the swirler (13) arranged circumferentially around the pilot burner housing (22), said channel and said swirler being built so that the main air flow (7) from said equalizer is directed in an axial and circumferential direction.