Gas turbine engine combustion chamber

A gas turbine engine combustion chamber comprising at least one combustion zone defined by at least one peripheral wall,

• means to define at least one fuel and air mixing duct for conducting a mixture of fuel and air to the at least one combustion zone, each mixing duct having an upstream end for receiving fuel and air and having a downstream end for delivering the fuel and air mixture into the at least one combustion zone, the at least one fuel and air mixing duct extending around the combustion chamber externally thereof,
• fuel injector means for injecting fuel into the at least one fuel and air mixing duct;
• a fuel manifold for supplying fuel to the fuel injector means, the fuel manifold extending around the at least one fuel and air mixing duct externally thereof, wherein the fuel manifold and the at least one fuel and air mixing duct have common boundary wall means including at least a portion extending in the direction of flow over said boundary wall means;
• said combustion chamber being enclosed by a combustor casing, a fuel supply pipe extending through an aperture in said casing and being in fluid flow communication with said fuel manifold, said fuel supply pipe being secured to said combustor casing, said fuel supply pipe having an inner end secured to said fuel manifold so that the combustor casing supports the fuel manifold, said fuel manifold being relatively moveable with respect to said combustion chamber.