GAS TURBINE ENGINE COMBUSTION CHAMBER

摘要

A gas turbine engine combustion chamber (28) which has primary, secondary and tertiary combustion zones (36,40,44) in flow series has a secondary fuel and air mixing duct (64) and a tertiary fuel and air mixing duct (76). The secondary mixing duct (64) has a secondary air intake (72) at its upstream end and the tertiary mixing duct (76) has a tertiary air intake (84) at its upstream end. The tertiary air intake (84) is arranged adjacent to the secondary air intake (72). A combined secondary and tertiary fuel system (88) is provided to supply fuel to the secondary and tertiary mixing ducts (64,76). The fuel system (88) comprises a manifold (90) arranged adjacent to the secondary mixing duct (64) but is spaced from the tertiary mixing duct (76) by the secondary mixing duct (64). The manifold (90) has apertures (98) to direct fuel towards the tertiary air intake (84) across the secondary air intake (72). Variations in fuel pressure cause the fuel to flow into the secondary air intake (72) or the tertiary air intake (84).