Patent ID: 6105360
Filing Date: 2000-08-22
Classification: F05D,F23R

Abstract:
A gas turbine engine combustion chamber comprising a lean burning primary combustion zone, a lean burning secondary combustion zone downstream of the primary combustion zone, a pilot fuel injector to supply fuel into the primary combustion zone, at least one primary premixing duct to supply a first mixture of fuel and air into the primary combustion zone, at least one secondary premixing duct to supply a second mixture of fuel and air into the secondary combustion zone, wherein the primary premixing duct has air inlet means to supply air into the primary premixing duct and primary fuel injector means to supply fuel into the primary premixing duct, the secondary premixing duct has air inlet means to supply air into the secondary premixing duct and secondary fuel injector means to supply fuel into the secondary premixing duct, a catalytic combustion zone downstream of the secondary combustion zone and a homogeneous combustion zone downstream of the catalytic combustion zone.