Patent ID: 6035645
Filing Date: 2000-03-14
Classification: F23R,Y02T

Abstract:
A dual-flow fuel injection system for a gas turbine engine, said fuel injection system comprising:a venturi (31) having central axis (23) and a wall with an inner wall surface (30);a fuel injector (43) having a primary fuel circuit (50) and a secondary fuel circuit (52), said primary fuel circuit (50) supplying a primary fuel flow (51) during all operational modes of the gas turbine engine, said secondary fuel circuit (52) supplying a secondary fuel flow (53) only when engine operating parameters exceed predetermined threshold values, said fuel injector (43) being arranged to inject said primary fuel flow (51) into said venturi (31) as a primary fuel cone, said primary fuel cone forming a cone angle (.beta.) with said central axis (23), said fuel injector (43) being arranged to inject said secondary fuel flow (53) into said venturi (31) as a secondary fuel cone, said secondary fuel cone forming a cone angle (.alpha.) with said central axis (23), said cone angle (.alpha.) of said secondary fuel cone being larger than said cone angle (.beta.) of said primary fuel cone;a first air swirler (32) mounted upstream of said venturi (31) so as to supply a first airflow inside said venturi (31); anda second air swirler (33) mounted downstream of said first air swirler (32) so as to supply a second airflow outside said venturi (31), said venturi (31) forming a boundary which separates said first and second airflows; andwherein said venturi (31) has a length and a shape such that said primary fuel flow (51) does not impact against said inner wall surface (30) of said venturi (31).