A GAS TURBINE ENGINE COMBUSTION CHAMBER

摘要

A combustion chamber (44) which has a primary combustion zone (52) and a secondary combustion zone (56) is provided with a plurality of secondary fuel and air mixing ducts (88) arranged around the primary combustion zone (44). The secondary fuel and air mixing ducts (88) are defined by a pair of annular walls (92, 90) and by a plurality of walls (94) extending radially between the annular walls (90, 92). Each secondary fuel and air mixing duct (88) has an aperture (104) to direct a fuel and air mixture into the secondary combustion zone (56). The apertures (104) have the same flow area. Each secondary fuel and air mixing duct (88) has one or more fuel injectors (100) to inject fuel into the upstream end of the secondary fuel and air mixing duct (88) where air enters through an inlet (98). This arrangement ensures that the fuel/air ratio emitted from each aperture (104) is within 3.0 % of the mean fuel/air ratio of all the apertures (104) even though the air flow to the secondary fuel and air mixing ducts (88) is non uniform.