| 摘要 |
<p>The invention relates to a pilot combustor particularly for use in a burner (1) of a gas turbine engine and a method for burning a fuel in a pilot combustor zone (22) of a pilot combustor (5). It is one object of the invention to stabilze combustion under all load conditions. According to the invention a pilot combustor having rotationally symmetric walls (21) defining a combustion room with an exit (6) is provided with a rich concentration of fuel in air for buring said fuel for the creation of a flow of an non equilibrium unquenched concentration of radicals (32) elevated to a temperature above 2000 K in the combustion room and directed along a centre line of the pilot combustor (5) through a throat (33) at the exit (6) of the pilot combustor (5), wherein a quarl (29) is located downstream of the throat (33) of the pilot combustor (5). According to the method the pilot combustor (5) is arranged upstream of a burner (1) for providing a main lean partially premixed combustion process occurring in a shear layer (18) of a main flame (7) surrounding a main recirculation zone (20) of said burner (1) downstream of the pilot combustor (5) with a flow of an unquenched concentration of radicals (32) at non equilibrium level and elevated to a temperature above 2000 K.</p> |
